WesWorld

Aircraft used by the Luftwaffe (both historical and not)

* designates a design that is not historical, and that will be further described later.

Fighters of the Luftwaffe:

1930-
Heinkel He-51
Arado Ar-68

1934-
BFW Bf-109A*

1935-
Focke-Wulf Fw-187A*
BFW Bf-109B*

1937-
BFW Bf-109F*
Heinkel He-100A*
Focke-Wulf Fw-190A*
Heinkel He-100B*

1938-
Focke-Wulf Fw-187C*


Bombers of the Luftwaffe

1930-
Dornier Do-23
Junkers K-51

1932 -
Dornier Do-17

1933 -
Henschel Hs-123
Blohm & Voss Ha-137

1934-
Heinkel He-111B*
Fokker Fo-91*

1935 -
BFW Bf-110B*
Junkers Ju-87B
Heinkel He-111E*

1937 -
Junkers Ju-87D
Junkers Ju-88A


Seaplanes of the Luftwaffe
1930-
Dornier Do-15

1932-
Heinkel He-59
Heinkel He-60

1934-
Dornier Do-18


Carrier Aircraft of the Luftwaffe:

1934-
Heinkel He-51T*

1937-
BFW Bf-109T*
Junkers Ju-87C


Recon Aircraft of the Luftwaffe

1935-
BFW Bf-109 B-6*

1937-
Focke-Wulf Fw-187R*
Focke-Wulf Fw-189


Liaison Aircraft of the Luftwaffe

1936-
BFW Bf-108
Fieseler Fi-156

Non-historical Fighters of the Luftwaffe

BFW Bf-109A

The WW Bf-109A is very similar to the real-world Bf-109D equipped with a DB-600 engine, but the armament is different in that where the Bf-109D had 4 or 5 7.92mm MG-17s, the WW Bf-109A has 2 15mm MG-151s in the wing roots and 2 7.92m MG-17s above the engine. Began joining the Luftwaffe in early 1934.


BFW Bf-109B

The WW Bf-109B is very similar to the real-world Bf-109E equipped with a DB-601Aa engine, but the armament is different in that where the Bf-109E had 2 7.92mm MG-17s above the engine and 2 20mm MG-FFs in the outer wings, the WW Bf-109B has 2 15mm MG-151s in the wing roots and 2 7.92m MG-17s above the engine. Began joining the Luftwaffe in late 1934.


BFW Bf-109F

The WW Bf-109F is very similar to the real-world Bf-109F equipped with a DB-601N engine, but the armament is different in that where the Bf-109F had 2 7.92mm MG-17s above the engine and 1 15mm MG-151 or 1 20mm MG-151/20s in the engine, the WW Bf-109F has 2 15mm MG-151s in the wing roots and 2 7.92m MG-17s above the engine. Began joining the Luftwaffe in 1937.


Focke-Wulf Fw-187A

The WW Fw-187A is similar to the real-world Fw-187, though it's equipped with a pair of DB-601Aa engines vs the Jumo 210s or DB-600s of the real aircraft. Standard radiator cooling is also used, rather than the evaporative cooling used on the Fw-187 V6. The WW aircraft is a single-seat aircraft, is armed with 4 15mm MG-151s and 2 7.92mm MG-17s in the nose of the aircraft, has a range of 1,200 nm, and a top speed of 361 kts at 15,000 feet.


Focke-Wulf Fw-187C

The WW Fw-187C is similar to the WW Fw-187A, though it's equipped with a pair of DB-601EM engines vs DB-601Aas of the preceeding aircraft. Like it's predecessor, it is a single-seat aircraft, is armed with 4 20mm MG-201s and 2 11mm MG-111s in the nose of the aircraft, is fitted with self-sealing fuel tanks and 10mm armor protecting the pilot, has a range of 1,200 nm, and a top speed of 396 kts at 18,000 feet.


Heinkel He-100A

The WW He-100A is similar to the real-world He-100D equipped with a DB-601N engine, but slightly larger in all dimensions. The armament is different in that where the He-100D had 2 7.92mm MG-17s in the wing roots and 1 20mm MG-FF/M in the engine, the WW He-100A has 2 15mm MG-151s in the wing roots and 2 7.92m MG-17s above the engine. Began joining the Luftwaffe in 1937.


Focke-Wulf Fw-190A

The WW Fw-190A is similar to the real-world Fw-190A, with the first model accepted for service (the Fw-190 A-4) being armed with 2 7.92mm MG-17s in the nose decking, and 4 15mm MG-151s (two in the wing roots and two more outboard of the propellor). Begin joining the Luftwaffe in late 1937.


Heinkel He-100B

The WW He-100B is similar to the He-100A but equipped with a DB-601EM engine, and fitted with 10mm cockpit armor, self-sealing fuel tanks, and an ETC-250 rack for a 250 kg bomb or a 300 liter drop tank. In the B-2 model, the nose 7.92m MG-17s above the engine have been replaced by 11mm MG-111s. The B-6 version replaces the 15mm MG-151s in the wing roots with 20mm MG-201s. Began joining the Luftwaffe in late 1937 (B-2) and fall 1938 (B-6).

Non-historical Bombers of the Luftwaffe

Heinkel He-111B

The WW Heinkel He-111B is similar to the historical He-111E, except it still has the elliptical wings. It is powered by a pair of 1050 hp Jumo-211s, armed with 2 7.92mm MG-15s and 2 15mm MG-151s, and can carry a bomb load of up to 2000 kg.


Heinkel He-111E

The WW Heinkel He-111E is similar to the historical He-111H. It replaces the He-111B in production in mid-1935, as it is both slightly faster than the older aircraft and cheaper to build. It is powered by a pair of 1100 hp Jumo-211s, armed with 2 7.92mm MG-15s and 2 15mm MG-151s, and can carry a bomb load of up to 2000 kg.


Fokker Fo-91

The WW Fokker Fo-91 is the Fokker T.V, re-engined with BMW-132Ks of 870 hp, armed with 2 7.92mm MG-15s and 2 15mm MG-151s, and outfitted to carry 1 H4D torpedo.


BFW Bf-110B

The WW Bf-110B is similar to the historical BFW Bf-110 C-4. but fitted with a centerline ETC 1000 rack capable of carrying 1 H4D torpedo or 4 250 kg bombs. Internal armament consists of 2 15mm MG-151s and 2 7.92mm MG-17s in the nose, and a flexible MG-81 in the rear cockpit. The B-3 version, introduced late in 1935, is fitted with an extended tail housing a rescue dinghy, since many of the Bf-110B's missions are over water.


BFW Bf-110C

The WW Bf-110C is developed from the WW BFW Bf-110 B-1. but fitted new DB-601N engines. It is equipped with a centerline ETC 1000 rack capable of a H4D torpedo, 2 500 kg bombs, 4 250 kg bombs, 8 70 kg bombs, or 8 50 kg bombs. Internal armament consists of 2 15mm MG-151s and 4 7.92mm MG-81s in the nose, and a flexible twin 7.92mm MG-81Z in the rear cockpit. The Bf-110C is developed from the Bf-110B with lessons learned from the Lithuanian conflict of 1935.


Junkers Ju-88A

The Ju-88 A-1, powered by the Jumo-211D, is the historical Ju-88 A-1. In WW Luftwaffe service, it is armed an armament of 2 15mm HMGs in the dorsal and ventral positions and a 7.92mm MG-81Z MG in the nose and a bombload of up to 2,500 kg (only 500 kg internally).

Non-Historical Carrier Aircraft of the Luftwaffe

Heinkel He-51T

A version of the He-51 fighter for use in carrier training, equipped with an arrester hook and strengthened fuselage for carrier landings.


BFW Bf-109T

The WW Bf-109T is based on the WW Bf-109F, but equipped with folding wings, arrester hook, and other carrier-operation equipment. Began joining the Luftwaffe in 1937.

Non-Historical Recon Aircraft of the Luftwaffe

BFW Bf-109 B-6

A photo-recon conversion of a WW Bf-109B, armed with 2 7.92m MG-17s above the engine and a RB21/18 camera in the fuselage. Began joining the Luftwaffe in late 1935.


Focke-Wulf Fw-187R

A high-altitude photo-recon conversion of the WW Fw-187, armed with 4 7.92mm MG-81s in the nose and provision for 2 RB75/30, RB50/30 or RB20/30 cameras behind the cockpit. Powered by special high-altitude DB-601NS engines, to allow it to fly above many threats at speeds many aircraft struggle to achieve when it's introduced in late 1936. Began joining the Luftwaffe in 1937.

Technical Description

Low-wing cantilever monoplane with dihedral and taper from roots to tip. All metal structure with a main spar at 35-40 degrees of the chord and an auxiliary spar. Main spar has a duralumin sheet web with flanges built up of L-shaped extrusions. Widely spaced ribs with intercostal chordwise stiffeners of modified U-section. Frise-type ailerons with combined balance and electrically operated trim tabs. Flaps between ailerons and fuselage.

Fuselage is of all metal semi-monocoque structure. Z-section frames are pierced to clear the continuous U-section stringers to which the stressed skin is riveted.

Cantilever monoplane type tail unit. Dihedral tailplane with fins and rudders at the extremities. Tailplane incidence adjustable on the ground. Elevators have combined trim and balance tabs. Rudders have trim and balance tabs as well as horn balances. Trimming of all control tabs by electric motors incorporated into the tab linkage.

Retractable type undercarriage. Main wheels are raised backwards into the engine nacelles. Fixed tail unit.

Two Argus As411 twelve-cylinder inverted Vee air-cooled engines each rated at 600 hp at 610 metres. Total fuel capacity 1,200 litres.

Accommodation for a crew of two in the glazed nose. As a military wireless or navigation trainer accommodation is provided for up to five trainees at stations with all necessary equipment. As a light civil air transport up to eight passengers with 200 kg of baggage may be carried. Complete electrical equipment with engine driven generator and storage batteries for navigation, instrument and landing lights, electric fuel gauges, and variable pitch airscrew. Oxygen equipment fitted in military variants.

Span 21.30 metres, length 11.90 metres, height 4.25 metres, wing area 46.00 square metres. Weight empty 3,950 kg, weight loaded 5,590 kg.

Maximum speed at 3,000 metres 364 kph, cruising speed 340 kph. Climb to 1,000 metres, 3.3 minutes. Service ceiling 7,500 metres. Cruising range 1,800 kilometres.

Technical Description

Low wing cantilever monoplane. Wing in one piece, the front spar being continuous and passing through the fuselage, to which it is attached at three points – two on the upper flange and one on the lower. The rear spar is in two sections, the roots being attached to the sides of the fuselage by normal pin joints. Two spar wing structure with widely-spaced flange plate former ribs, span-wise Z-section stringers and a stressed metal skin. The spars are built up of flanged plates which, inboard from the ailerons, are reinforced by L-section extrusions and progressively thickened end caps to form I-section members. Outboard of ailerons the spars have single integral flanges. The front spar from the points of attachment of the undercarriage to the upper attachments to the fuselage is cranked inward, the undercarriage when retracted lying ahead of the front spar. The gun and undercarriage bays have specially strengthened ribs. Metal framed, fabric covered ailerons. Electrically operated all metal split trailing-edge flaps between ailerons and fuselage.

Fuselage is an all-metal monocoque structure built-up of bulkheads, flanged formers, Z-section stringers and a smooth stressed skin covering. The front inverted U-shaped bulkhead attaches to the upper flange of the front spar and on the front face of the bulkhead and spar are five attachment points for the engine mounting – three on the spar and two on the bulkhead. All other bulkheads and frames conform to the cross-section of the fuselage. The extreme rear section is integral with the fin and is detachable from the main structure. Large detachable panel in the underside of the fuselage extending from the engine bay to rear of cockpit for installation and removal of fuel tanks.

Cantilever monoplane type tail unit. Fin integral with the rear fuselage. Electrically operated adjustable single-spar tailplane and fin and fabric covered control surfaces. Fixed perforated trim tabs in rudder and elevators. Fin-rear fuselage assembly houses the electric tailplane incidence gear and spring for lowering the tail wheel.

Retractable type undercarriage. Main cantilever oleo-legs are hinged ahead of the front spar and retract inwardly, fairing plates on legs and wheels and on the undersurface of the wings closing the apertures when the wheels are raised. Electrical retraction. The tail wheel is also partially retracted by a cable connected to the starboard oleo-leg. Tail wheel has spring centering and centre-lock, the latter operating when the control column is pulled hard back.

One BMW 801D fourteen-cylinder two-row radial air-cooled geared and supercharged engine in low-drag cowling with induced fan cooling, rated at 1,700 hp for takeoff and 2,100 hp with MW50 boost at altitude. The whole engine unit, complete with oil coolers, is attached to the front bulkhead and spar by five bolts. Protected fuel tanks beneath the cockpit floor. Oil tank (42 litres) in fuselage. Reverse flow oil coolers in armoured annual ring which forms the cowl leading edge. VDM airscrew with electric pitch change and metal blades.

Pilot’s cockpit over trailing edge of wing with clear view canopy and tail fairing, the whole of which slides aft to give access to the cockpit and which may be jettisoned complete in an emergency. Pilot’s seat is armoured and is further backed by an armoured bulkhead and headrest, the latter forming part of the jettisonable cockpit canopy. Bullet proof windscreen. The wireless aerial lead is in the roof the canopy. The canopy cannot be opened in the air except to be jettisoned. Armament comprises two 13mm MG131 with 220 rounds of ammunition in the forward fuselage decking and two 20mm MG201 with 150 rounds of ammunition per gun , located in the wing roots and synchronised to fire through the propeller arc. Attachment points in the outer wing panels for two 100 kg bombs; attachment point beneath the centre fuselage for one 120-litre jettisonable auxiliary fuel tank.

Wing span 10.5 metres; length 8.84 metres; height 3,96 metres. Wing area 18.3 metres. Take-off weight with armament and normal fuel 4,430 kg; maximum permissible take-off weight 4,900 kg.

Maximum speed without MW boost 643 kph at 5,500 metres; with MW boost 653 kph at 6,300 metres. Climb to 10,000 metres without MW boost 26.5 minutes, with MW boost 16.5 metres. Service ceiling 10,300/11,400 metres. Cruising range with normal fuel 1,520 km at 477 kph at 7,000 metres. Endurance 3 hours 20 minutes.

Technical Description

Low wing cantilever monoplane. Wings taper sharply in chord and thickness. All-wood structure with plywood covering over leading edge to rear spar and fabric covering thence to trailing edge. Narrow-chord ailerons over half of trailing edge. Split flaps between ailerons and fuselage.

Fuselage is an oval section structure. Forward portion of chrome-molybdenum steel tubing with metal panels and after portion a wooden monocoque.

Cantilever monoplane-type tail unit. Tail-plane and fin have wooden framework and plywood covering. Rudder and elevators have a wood frame and plywood covering. Trimming tabs on elevators adjustable in the air. Trimming tab on rudder adjustable on the ground only.

Fixed cantilever type undercarriage. Single legs have steel-spring shock absorbers with oil damping. Fairings on legs. Swiveling tail wheel.

One 105 hp Hirth HM504 four-cylinder inline inverted air-cooled engine. Fuel tank in fuselage.

Enclosed cabin seating two side-by-side with dual controls. Adjustable seats arranged for seat-type parachutes. Large baggage compartment behind cabin.

Span 10.6 metres; length 7.75 metres; height 2.1 metres. Wing area 18.5 sq. metres. Weight empty 480 kg, disposable load 270 kg, weight loaded 750 kg. Wing loading 55 kg/sq. metre, power loading 7.14 kg/hp.

Maximum speed 215 kph; cruising speed 195 kph; landing speed 70 kph. Climb to 1,000 metres 5.3 minutes, to 2,000 metres 12 minutes, to 3,000 metres 20.8 minutes. Service ceiling 5,000 metres. Range 800 km. Duration – four hours.

Technical Description

High-wing braced monoplane. Rectangular outer wings hinged to the upper fuselage longerons and braced to the lower longerons by steel tube Vee-struts. Two-spar wooden construction. Fixed light metal slot along entire leading edge. Entire trailing edge hinged, outer portions acting as statically balanced and slotted ailerons and inner portions as slotted camber-changing flaps.

Rectangular welded steel tube fuselage, covered with fabric.

Braced monoplane type tail unit. Fin built integral with fuselage. Adjustable type tailplane. Balanced rudder and elevators. Fixed dependent slat below hinge-line of elevators. Tail surfaces have wooden framework with fabric covering.

Split type undercarriage. Consists of two compression legs, incorporating long-stroke steel spring oil-damped shock absorbers, the upper ends attached to the apices of two pyramids on the side of the fuselage, with the lower ends hinged to the centre-line of the underside of the fuselage by steel-tube Vees. Low pressure wheels and hydraulic brakes. Tail skid has steel-spring oil-damped shock absorber.

One 240hp Argus As10C eight-cylinder inverted Vee air-cooled engine on welded steel-tube mounting. Two fuel tanks (145 litres) in wing roots. An additional 200 litre tank may be carried in the fuselage instead of two passengers.

Enclosed cabin seating pilot and one or two passengers in tandem. Entire sides and roof of cabin glazed. Side windows are built out with lower panels sloping in acutely to give good downward vision. Door on starboard side. Provision for wireless, camera and night-flying equipment.

Wingspan 14.25 metres; width folded 4.75 metres; Length 9.9 metres; Height 3.05 metres; Wing area 26 sq. metres; Weight empty 930 kg; weight loaded 1,320 kg.

Maximum speed at sea level 175 kph; cruising speed 96-128 kph; landing speed 51 kph. Climb to 915 metres 4 minutes. Service ceiling 5,000 metres. Maximum range at sea level (crew of three) 385 kilometers at 96 kph; maximum range at sea level (crew of one and 350 litres fuel) 1,010 kilometers at 96 kph.

Technical Description

Mid-wing cantilever monoplane. Centre-section in one piece carries the four engines. Tapering outer wings with dihedral and rounded tips. All metal single-spar stressed-skin structure. Split trailing edge flaps extend outboard as far as the ailerons, which also droop when the flaps are lowered. Double trim tabs on ailerons, inner tabs geared and spring loaded and outer tabs adjustable from the cockpit. Hot air leading-edge de-icing.

Fuselage is an all-metal stressed skin structure built up of four heavy longerons, bulkheads and vertical stiffeners. Nose section contains the flight deck.

Cantilever monoplane type tail unit. Single spar tailplane. All surfaces are metal covered. All control surfaces have two trim tabs, one spring loaded and the other controllable from the cockpit. Hot air de-icing on tailplane leading edge.

Retractable type undercarriage. Each main unit consists of a single leg and twin wheels on a levered suspension system. The legs and wheels retract backwards and when raised are completely enclosed in the inboard engine nacelles. Retractable tail wheel.

Four Daimler Benz DB603E twelve-cylinder inverted Vee liquid-cooled engines with turbo-superchargers, rated at 1,750 hp for takeoff and 1,850 hp at 5,000 metres. Four-bladed VDM controllable pitch propellers. Annual radiators at the front of each engine nacelle. Seven fuel tanks – four in the wings and three in the fuselage – with a total capacity of 8,220 litres.

Flight deck provides seating for pilot, observer and bomb-aimer in the nose of the aircraft. Beneath and behind the flight deck are stations for two wireless operator-air gunners sitting back to back. Station for an air gunner in an enclosed dorsal turret immediately aft of the flight deck, together with a mid-upper position reached via a tunnel above the bomb cell; position for a fifth air gunner in the tail of the aircraft. Equipment includes armour, heating and ventilation, oxygen, 24-volt electrical system, wireless, blind approach equipment etc. Defensive armament comprises one flexible 15mmm MG151 machinegun with 400 rounds of ammunition in each station of the ventral gondola beneath the flight deck. Two 13mm MG131 machineguns with 500 rounds of ammunition per gun in the upper turret, and two similar weapons in the mid upper turret. One 20mm MK201 cannon with 220 rounds of ammunition in the tail position. Offensive bomb load of up to 6,000 kg, comprising two 2,500 kg, six 1,000 kg or twelve 500 kg bombs.

Span 44.2 metres; Length 22.3 metres; Height 6.7 metres. Empty weight 21,920 kg; weight loaded 36,100 kg.

Maximum speed 570 kph at 5,000 metres, economical cruising speed 460 kph at 5,000 metres. Climb to 5,000 metres 25 minutes. Service ceiling 8,000 metres. Maximum range 5,500 kilometres.

Technical Description

Shoulder-wing cantilever monoplane. Wing of single-spar stressed-skin construction built as a single unit, the spar being continuous through the fuselage. Straight leading edge but sharp sweep-forward on the trailing edge outboard of the nacelles, increasing at the inner ends of the ailerons. Fowler flaps between ailerons and nacelles, and nacelles and fuselage. Ailerons are aerodynamically and mass-balanced and have geared tabs. Part of the tab on the port wing is adjustable for trimming.

Fuselage of rectangular section with rounded corners. Stressed skin metal structure in two sections. The front section forms the nose and cockpit, and the rear or main section houses the three self-sealing fuel tanks. Aft of the rear tank is the electrical and wireless equipment, the master compass and emergency seat, access to which is through a trap door under the fuselage. The extreme end of the fuselage houses the trailing aerial.

Cantilever monoplane type tail unit with twin fins and rudders. Tailplane is one unit and is provided with moderate dihedral. Two fins and rudders are slightly toed in.

Retractable tricycle type undercarriage. Each main unit consists of a single oleo leg and twin wheels and is raised backward into the engine nacelle. Nose wheel also retracts backward and the wheel turns through ninety degrees to lie flat in the fuselage. Hydraulic retraction.

Two 1,900 hp Daimler-Benz DB603G twelve-cylinder inverted Vee liquid cooled engines driving three-bladed constant speed airscrews. Annular radiators surround the airscrew shafts. The nacelles are unusually long and are faired to points well aft of the trailing edge of the wings. Armour plate at the rear of each engine. Three self-sealing fuel tanks in the fuselage: the front tank holds 1,100 litres, the centre tank 500 litres and the read tank 1,000 litres.

Crew of two seated in the nose of the aircraft. Emergency seat in rear fuselage. Entrance to the nose cockpit is through the roof. Full armour plating.

Four 20mm MG201 cannon in a detachable fairing under the fuselage with 300 rounds per gun, and two 20mm MG201 cannon with 200 rounds per gun in the wing roots.

Span 18.5 metres; Length 15.6 metres; Height 4.4 metres. Wing area 44.4 metres. Empty weight 11,200 kg; loaded weight 15,300 kg.

Maximum speed at 7,000 metres 670 kph; normal cruising speed 540 kph. Absolute ceiling 12,700 metres, initial climb rate 10.9 metres/second. Range at maximum continuous speed 1,520 kilometres; range at economical cruising speed 2,140 kilometres.

Technical Description

High wing cantilever monoplane. All metal structure. Wing in three sections, comprising a centre section which carries the engine nacelles and tail booms at its extremities and supports the central fuselage; and two outer sections. Ailerons and flaps on outer section.

The central fuselage, of all metal construction, accommodates the flight deck and main hold. Two all-metal booms extending aft from engine nacelles carry the tail unit. Booms are interchangeable.

Monoplane type tail unit with twin fins and rudders. Fins are integral with the tail-booms, tailplane unites the two booms. All-metal structure with metal covered fixed surfaces and fabric covered rudders and elevators. Thermal anti-icing for tailplane and fins.

Retractable tricycle type undercarriage. Main wheels raised into undersides of engine nacelle extensions, nose wheel into nose of central fuselage. Single main wheels each sprung by two oleo shock absorber units, nose wheel by half fork unit. Electric retraction. Hydraulic wheel brakes.

Two 2,100 hp Brandenburgische Motorenbau 328 eighteen cylinder air-cooled engines in interchangeable nacelles. Four bladed VDM constant speed full feathering airscrews. Fuel tanks carried in the wing centre section between spars. Capacity 5,000 litres.

Pilot's compartment seats two side by side in nose of central fuselage. Navigator and wireless operator's positions behind pilots, with flight engineer’s folding seat on rear bulkhead. Main hold has unobstructed cargo space for its entire length. Main loading doors at rear of compartment hinge outward to full cross section of hold. Doors can be removed for paradropping of large loads. Smaller doors for personnel use at front and rear of hold. Adjustable ramps permit vehicles and other heavy loads directly into hold. Floor is parallel to ground and is at the height of a standard truck floor to permit rapid loading operations under all conditions. Tie down fittings located at centre of 50cm squares over the entire floor area. Provision for up to forty-eight troop seats, thirty-six paratroops or 7,000 kg of cargo.

Span 32.76 metres, length 21.94 metres, height 6.09 metres. Weight empty 8,400 kg; maximum takeoff weight 20,500 kg.

Maximum speed 420 kph at 4,500 metres, cruising speed 320 kph at 4,500 metres. Service ceiling 7,800 metres. Range with 7,000 kg payload 2,000 kilometres, maximum range 3,700 kilometres.

Technical Description

Low wing cantilever monoplane. Wing in one piece, the front spar being continuous and passing through the fuselage, to which it is attached at three points – two on the upper flange and one on the lower. The rear spar is in two sections, the roots being attached to the sides of the fuselage by normal pin joints. Two spar wing structure with widely-spaced flange plate former ribs, span-wise Z-section stringers and a stressed metal skin. The spars are built up of flanged plates which, inboard from the ailerons, are reinforced by L-section extrusions and progressively thickened end caps to form I-section members. Outboard of ailerons the spars have single integral flanges. The front spar from the points of attachment of the undercarriage to the upper attachments to the fuselage is cranked inward, the undercarriage when retracted lying ahead of the front spar. The gun and undercarriage bays have specially strengthened ribs. Metal framed, fabric covered ailerons. Electrically operated all metal split trailing-edge flaps between ailerons and fuselage.

Fuselage is an all-metal monocoque structure built-up of bulkheads, flanged formers, Z-section stringers and a smooth stressed skin covering. The front inverted U-shaped bulkhead attaches to the upper flange of the front spar and on the front face of the bulkhead and spar are five attachment points for the engine mounting – three on the spar and two on the bulkhead. All other bulkheads and frames conform to the cross-section of the fuselage. The extreme rear section is integral with the fin and is detachable from the main structure. Large detachable panel in the underside of the fuselage extending from the engine bay to rear of cockpit for installation and removal of fuel tanks.

Cantilever monoplane type tail unit. Fin integral with the rear fuselage. Electrically operated adjustable single-spar tailplane and fin and fabric covered control surfaces. Fixed perforated trim tabs in rudder and elevators. Fin-rear fuselage assembly houses the electric tailplane incidence gear and spring for lowering the tail wheel.

Retractable type undercarriage. Main cantilever oleo-legs are hinged ahead of the front spar and retract inwardly, fairing plates on legs and wheels and on the undersurface of the wings closing the apertures when the wheels are raised. Electrical retraction. Tail wheel has spring centering and centre-lock, the latter operating when the control column is pulled hard back.

One Junkers Jumo 213A-1 twelve-cylinder inverted Vee liquid cooled engine rated at 1,770 hp (2,240 hp with MW50 boost). The whole engine unit, complete with oil coolers, is attached to the front bulkhead and spar by five bolts. Protected fuel tanks beneath the cockpit floor. Oil tank (42 litres) in fuselage. Reverse flow oil coolers in armoured annual ring which forms the cowl leading edge. VDM airscrew with electric pitch change and metal blades.

Pilot’s cockpit over trailing edge of wing with clear view canopy and tail fairing, the whole of which slides aft to give access to the cockpit and which may be jettisoned complete in an emergency. Pilot’s seat is armoured and is further backed by an armoured bulkhead and headrest, the latter forming part of the jettisonable cockpit canopy. Bullet proof windscreen. The wireless aerial lead is in the roof the canopy. The canopy cannot be opened in the air except to be jettisoned. Armament comprises two 13mm MG131 with 475 rounds of ammunition in the forward fuselage decking and two 20mm MG201 with 250 rounds of ammunition per gun , located in the wing roots and synchronised to fire through the propeller arc. Attachment point beneath the centre fuselage for one 120-litre jettisonable auxiliary fuel tank.

Wing span 10.5 metres; length 10.2 metres; height 3.35 metres. Wing area 18.3 metres. Loaded weight 4,270 kg; maximum permissible take-off weight 4,840 kg.

Maximum speed without MW boost 685 kph at 6,600 metres; with MW boost 710 kph at 11,000 metres. Climb to 11,000 metres with MW boost 8.1 minutes. Service ceiling 11,400 metres. Cruising range with normal fuel 835 km at 477 kph at 6,000 metres.

Technical Description

Low wing cantilever monoplane. Wing in one piece, the front spar being continuous and passing through the fuselage, to which it is attached at three points – two on the upper flange and one on the lower. The rear spar is in two sections, the roots being attached to the sides of the fuselage by normal pin joints. Two spar wing structure with widely-spaced flange plate former ribs, span-wise Z-section stringers and a stressed metal skin. The spars are built up of flanged plates which, inboard from the ailerons, are reinforced by L-section extrusions and progressively thickened end caps to form I-section members. Outboard of ailerons the spars have single integral flanges. The front spar from the points of attachment of the undercarriage to the upper attachments to the fuselage is cranked inward, the undercarriage when retracted lying ahead of the front spar. The gun and undercarriage bays have specially strengthened ribs. Metal framed, fabric covered ailerons. Electrically operated all metal split trailing-edge flaps between ailerons and fuselage.

Fuselage is an all-metal monocoque structure built-up of bulkheads, flanged formers, Z-section stringers and a smooth stressed skin covering. The front inverted U-shaped bulkhead attaches to the upper flange of the front spar and on the front face of the bulkhead and spar are five attachment points for the engine mounting – three on the spar and two on the bulkhead. All other bulkheads and frames conform to the cross-section of the fuselage. The extreme rear section is integral with the fin and is detachable from the main structure. Large detachable panel in the underside of the fuselage extending from the engine bay to rear of cockpit for installation and removal of fuel tanks. The lower part of the engine cowling and the engine covers are fabricated from 6mm armour plate, and additional armour is fitted to the ventral fuselage, the total weight of armour being approximately 380 kg

Cantilever monoplane type tail unit. Fin integral with the rear fuselage. Electrically operated adjustable single-spar tailplane and fin and fabric covered control surfaces. Fixed perforated trim tabs in rudder and elevators. Fin-rear fuselage assembly houses the electric tailplane incidence gear and spring for lowering the tail wheel.

Retractable type undercarriage. Main cantilever oleo-legs are hinged ahead of the front spar and retract inwardly, fairing plates on legs and wheels and on the undersurface of the wings closing the apertures when the wheels are raised. Electrical retraction. The tail wheel is also partially retracted by a cable connected to the starboard oleo-leg. Tail wheel has spring centering and centre-lock, the latter operating when the control column is pulled hard back.

One BMW 801D fourteen-cylinder two-row radial air-cooled geared and supercharged engine in low-drag cowling with induced fan cooling, rated at 1,700 hp for takeoff. The whole engine unit, complete with oil coolers, is attached to the front bulkhead and spar by five bolts. Protected fuel tanks beneath the cockpit floor. Oil tank (42 litres) in fuselage. Reverse flow oil coolers in armoured annual ring which forms the cowl leading edge. VDM airscrew with electric pitch change and metal blades.

Pilot’s cockpit over trailing edge of wing with clear view canopy and tail fairing, the whole of which slides aft to give access to the cockpit and which may be jettisoned complete in an emergency. Pilot’s seat is armoured and is further backed by an armoured bulkhead and headrest, the latter forming part of the jettisonable cockpit canopy. Bullet proof windscreen. The wireless aerial lead is in the roof the canopy. The canopy cannot be opened in the air except to be jettisoned. Armament comprises two 13mm MG131 with 220 rounds of ammunition in the forward fuselage decking and two 20mm MG201 with 150 rounds of ammunition per gun , located in the wing roots and synchronised to fire through the propeller arc. Attachment point beneath the centre section of the wing for one bomb up to 1,000 kg weight or for one 240-litre jettisonable auxiliary fuel tank; attachment points beneath each wing outer panel for bombs and air-to-ground rockets.

Wing span 10.5 metres; length 8.84 metres; height 3.96 metres. Wing area 18.3 metres. Empty weight 3,330 kg; normal loaded weight 4,410 kg; maximum take-off weight 4,930 kg.

Maximum speed 635 kph at 5,500 metres; 550 kph at sea level. Initial climb rate 640 metres/second; service ceiling 10,600 metres. Normal range 800 kilometres.

Technical Description

Shoulder wing cantilever monoplane. Structure in three sections, the centre-section which incorporates a portion of the fuselage and the two outer sections with semi-circular wing tips. Two-spar wing structure. All but a few former ribs are girder trusses, solid plate ribs being used at points of stress only. Smooth outer stress-bearing skin riveted to spars and former ribs. Slotted ailerons on outer sections. Electrically operated split flaps. Maximum flap angle 55 degrees. Ailerons and flaps are linked so that the ailerons droop when the flaps are lowered. Leading edge of the outer wing-section is double skinned and intervening space fed with hot air through lagged pipes in leading edge. Air enters at bottom of the sandwich between each nose rib and passes forward and upward around the leading edge and escapes into wing just forward of the front spar flange and finally to the atmosphere through apertures at the aileron hinges.

Fuselage is an all-metal structure in three sections, comprising the nose section accommodating the crew, the section which is integral with the wing centre-section section and the rear fuselage. Main structure is built up of a number of formers and stringers to which the stressed skin is riveted.

Cantilever monoplane type tail unit with twin fins and rudders. Tailplane and fins each have two spars and the entire unit, including the movable surfaces, is covered with a metal skin. Fins are fitted with fixed slats, the trailing-edges of the slats being on the inside of the fins. Rudders have very narrow horn balances, used mostly for mass balancing, and trimming tabs extending the full length of the trailing edge. Tailplane incidence is automatically changed when the landing flaps are lowered. It can also be adjusted manually.

Retractable type undercarriage. Each unit comprises two oleo legs and a single wheel and is electrically retracted rearwards into the engine nacelle. Electrically operated retractable tail wheel.

Two BMW 802A eighteen-cylinder two-row radial air-cooled engines each rated at 2,560 hp for takeoff and 1,575 hp at 11,800 metres on welded steel-tube mountings at the extremities of the centre-section. Five self-sealing fuel tanks and two oil tanks in the wings between the spars. Carbon-dioxide gas may be released into tank compartments in emergency. VDM four-bladed fully-feathering airscrews.

The crew of three is located in a pressurised cabin forming the forward section of the fuselage. The bomb aimer sits in the forward portion of the cabin, and his position is provided with duplicate controls for the aircraft; the pilot sits in the second position, while the wireless operator air gunner sits behind the pilot. Equipment includes armour, heating and ventilation, oxygen, 24-volt electrical system, wireless, blind approach equipment etc. Defensive armament comprises two 13mm MG131 machineguns with 500 rounds of ammunition per gun in a remote-controlled turret in the rear ventral position. Offensive armament comprises up to 3,300 kg of bombs carried in a single bomb cell.

Span 25.5 metres; Length 18.25 metres; Weight loaded 22,970 kg.

Maximum speed 665 kph at 6,800 metres. Range with 5,280 litres of fuel and bomb load of 3,300 kg 2,600 kilometres at 510 kph. Initial climb rate 493 metres per minute; service ceiling 11,800 metres.

Type: Three-seat light helicopter.

Rotor System: Three-blade main rotor. Blades have steel-tube spar, with plastic-bonded plywood covering. Fully-articulated hub with adjustable friction dampers. Main rotor blade area (each) 1.28 sq.m . Main rotor disc area 70 sq.m. Two tail rotors, inclined at 45° to horizontal, at extremities of tail stabilisers. Tail rotor blades of plastic-bonded plywood. Tail rotor disc area (total) 4.3 sq.m.

Rotor Drive: Main rotor drive via two-stage cam-wheel. Tail rotor drive via hollow steel-tube shaft and two bevel-gears. Main rotor/engine rpm ratio 1:10. Tail rotor/engine rpm ratio 1:6.75.

Fuselage: Uncovered steel-tube girder fuselage.

Landing Gear: Tricycle type. Shock-absorption by torsion spring and Borgward hydraulic damper. Wheel track 1.93m. Wheel base 1.80m.

Power Plant: One 260 hp Hirth air-cooled engine. Fuel tank aft of rear fire-wall, with capacity of 180 litres. Oil capacity 15 litres.

Accommodation: Normal seating for two persons. Alternative loads can include pilot with one internal and one external litter casualty, agricultural spraying or dusting equipment, or up to 300 kg of freight slung from an under-fuselage hook.

Technical Data:

Main rotor diameter: 9.40 metres, length of fuselage: 8.30 metres, height to top of main rotor head: 3.05 metres, tail rotor diameter: 1.66 metres.

Weight Empty: 800 kg, weight loaded: 1200 kg.

Maximum speed: 160 kph; cruising speed: 140 kph. Rate of climb at sea level: 240 metres/minute, vertical rate of climb at sea level: 60 metres/minute; Absolute ceiling: 4,500 metres, hovering ceiling: 600 metres, endurance: 3.0 hours.


Design History

Work on the Fa300 began in November 1941 in the wake of the Ivry-sur-Seine gathering of rotary wing designers. Inspired by the paper delivered by Igor Sikorsky Doctor Heinrich Focke and Gern Achgelis began work on a single-rotor design with tail rotors to provide stability. By May 1942 a prototype had been constructed, which, while successful in a technical sense, required considerable improvement before it could be considered a viable alternative to the Flettner Fl282 or to the Focke Achgelis Fa223. Work was further disrupted by the departure from the Focke-Achgelis collective of Raoul Hafner, who chose to continue the collective’s work on twin rotor designs.

In June 1943 the Luftwaffe placed orders for four machines for purposes of evaluation, two of which will be used to evaluate the design’s potential as a search-and-rescue aircraft while the second pair will be tested by the Heer for army-cooperation tasks.

General characteristics:

Crew: 1
Length: 10.60 m
Wingspan: 12.60 m
Height: 3.50 m
Wing area: 21.7 square metres
Empty weight: 3,795 kg
Loaded weight: 6,473 kg
Maximum takeoff weight: 7,130 kg
Powerplant: Two Junkers Jumo 004 B-1 turbojets, 898 kg thrust each
Aspect ratio: 7.32

Performance:

Maximum speed: 900 kph
Range: 1,050 km
Service ceiling: 11,450 m
Rate of climb: 1,200 m/min (At max weight of 7,130 kg)

Armament:

Guns: Four 30 mm MK 108 cannons

Technical Data

Crew: 2
Length: 8.98 metres
Wingspan: 10.40 metres
Height: 2.90 metres
Wing area: 17.35 square metres
Empty weight: 1,970 kg
Gross weight: 2,930 kg
Fuel capacity: 600 litres
Powerplant: One Bramo 323 Fafnir 9-cylinder radial engine rated at 800 hp

Maximum speed: 444 kph
Cruise speed: 381 kph
Stall speed: 104 kph
Range: 1,323 kilometres
Service ceiling: 10,250 metres
Rate of climb: 10.83 metres/second

Can be fitted with two light machineguns in pods beneath the outer wings and up to four 25 kg bombs for weapons training.

Crew: 1

Length: 12.64 metres
Wingspan 14.41 metres
Height: 4.29 metres
Wing area: 26.4 metres
Empty weight: 5,200 kg
Maximum takeoff weight: 9,800 kg

Powerplant: Two Junkers Jumo 004B Orkan axial-flow turbojet engines each rated at 8.83 kN thrust; Two Walter HWK 109-500A-1 jettisonable RATO pods, each rated at 4.90 kN can be fitted for takeoff

Maximum speed: 742 kph at 6,000 metres
Cruising speed: 700 kph at 6,000 metres
Maximum range (clean): 1,600 kilometres
Maximum range (500 kg ordnance load): 1,400 kilometres
Range with maximum ordnance load (1,500 kg): 1,100 kilometres
Service ceiling: 10,000 metres
Climb to 6,000 metres (with 500 kg load): 12.8 minutes
Climb to 8,000 metres (with 1,500 kg load): 21.6 minutes
Climb to 6,000 metres (with 1,500 kg load): 17.5 minutes
Climb to 8,000 metres (with 1,500 kg load): 34.1 minutes
Initial rate of climb: 13 metres/second

Defensive armament: two fixed aft-firing 20mm cannon with two hundred rounds per gun

Offensive armament: Up to 1,500 kg of ordnance stores on external racks