WesWorld

Technical Description

Low wing cantilever monoplane in three portions, comprising a rectangular centre-section built integral with the fuselage and two tapering outer sections. Structure of light metal consisting of two spars and the usual number of ribs, the whole covered with a stressed skin of smooth duralumin sheet. Ailerons on outer sections. Hydraulically operated slotted flaps in inner sections. Ailerons droop when flaps are lowered.

Fuselage is an oval section metal structure tapering to a point aft. Structure consists of three main bulkheads, a number of secondary frames, interconnected by longerons and ‘U’-section stringers.

Monoplane type tail unit. All surfaces elliptical. Cantilever tailplane and fin. Trimming tabs in all movable surfaces. Metal structure with smooth sheet covering.

Retractable type undercarriage. Each unit consists of two oleo legs and two backwardly-sloping hinged members which, when broken inwardly, raise the wheels aft into the tails of the engine nacelles. Low pressure tyres and Cannstadt brakes.

Two Junkers Jumo 211F twelve-cylinder inverted Vee liquid-cooled engines each rated at 1,350 hp for takeoff and 1,060 hp at 5,000 metres in nacelles at extremities of centre-section. Three-bladed VDM controllable pitch full-feathering airscrews. Four self-sealing fuel tanks, two inboard and two outboard of nacelles. Total fuel capacity 4,275 litres.

Normal crew of five, three in nose compartment and two aft of wings. Pilot on port side of the nose section, observer/navigator on the starboard side. Bomb-aimer’s station in the extreme nose of the aircraft. After cabin contains position for the wireless operator, who also operates the dorsal gun, and a second air-gunner operating the ventral gun. Defensive armament comprises one 7.92mm MG81 machinegun with 400 rounds on flexible mount in the extreme nose, one 15mm MG151 machinegun with 400 rounds in power-operated mount in dorsal position and two 7.92mm MG81 machineguns with 400 rounds per gun on a flexible mount in the ventral position. Internal bomb cell for up to eight 250 kg bombs; alternatively two 1,000 kg bombs can be carried on external mounts beneath the centre-section of the wing. Equipment includes long and short wave transmitting and receiving sets, direction-finding loop and blind approach receiver.

Span 22.6 metres; Length 16.6 metres; Height 4.2 metres. Wing area 87.6 square metres. Empty weight 7,720 kg, normal loaded weight 12,680 kg. Maximum permissible overloaded weight 14,975 kg.

Maximum speed 400 kph at 5,200 metres. Climb to 5,200 metres 20 minutes. Service ceiling 8,400 metres. Range with maximum fuel 2,800 kilometres.

(With thanks to Vukovlad for the original airwork on which the drawing is based)

Technical Description

Rigidly-braced high wing monoplane. Wing is of two-spar wooden construction with plywood covering from leading edge to main spar, the remainder, including the control surfaces, being covered with fabric. Ailerons fitted with trimming and geared tabs; flaps inboard from ailerons. Lift spoilers on upper surfaces of wings forward of outer portions of flaps.

Fuselage is a rectangular section structure of welded steel tube covered with fabric. Read section of fuselage is hinged at the top just aft of the trailing edge of the wings for loading and unloading of freight.

Monoplane type tail unit with twin fins and rudders. One piece rectangular tailplane is carrier between the extremities of the two all-wood booms that extend aft from the wing. The fins are integral with the boom. Elevators and rudders have geared and trimming tabs.

The craft is fitted with a tricycle undercarriage that is jettisoned once it is airborne behind its towing aircraft. Landing is made upon skids, the forward one of which is retractable.

Crew of two in forward section of the fuselage. The rear section of the fuselage from the bulkhead aft of the crew compartment is available for troops or freight. Entrance doors for troops in side of fuselage forward of the main landing skids. For freight loading the rear portion of the fuselage hinges upward to provide an opening the full cross-section of the body.

Wing span 24.5 metres; length 15.8 metres; height 4.4 metres. Wing area 64.4 metres

Empty weight 3,200 kg; loaded weight 7,100 kg.

Maximum towing speed 240 kph.

The first production Fw223 helicopter has been delivered from the Focke Wulf Delmenhorst factory and has been assigned to Transportstaffel 40, the Luftwaffe’s first operational helicopter unit, at Mühldorf, Bavaria. The Fw223 has been the subject of a lengthy development programme that saw a number of setbacks and changes in requirements. At the present time the aircraft will be produced in two configurations – the Fw223C, a search and rescue variant, fitted with a steel winch cable; and the Fw223D – a freight variant for resupplying mountain troops. An initial quantity of twenty-five aircraft has been ordered.

The surviving units were withdrawn from service in the spring of 1946.



General characteristics:

Crew: 2
Length: 12.25 m (fuselage length)
Span over Rotors: 24.50 m
Height: 4.36 m
Empty weight: 3,180 kg
Gross weight: 3,860 kg
Max takeoff weight: 4,315 kg
Fuel capacity: 490 litres internal plus 300 litres external tank
Powerplant: One Bramo 323D-2 nine-cylinder radial, 1,000 hp (take-off)
Main rotor diameter: 2× 12.00 m
Main rotor area: 226.00 sq. m

Performance:

Maximum speed: 176 kph at 2,000 m
Cruising speed: 134 kph at 2,000 m
Range: 437 km (internal fuel)
Ferry range: 700 km (with auxiliary fuel)
Endurance: 2 hr 20 min
Service ceiling: 4,875 m
Rate of climb: 4.1 m/s (vertical rate of climb), 5.6 m/s (with forward speed)

Service History

The prototype Fw58 V-1 made its first flight in 1935 as a six-seat light transport intended for service with Lufthansa, and as the civil Fw58A is was successful in garnering orders from Lufthansa for eight aircraft, as well as being exported to Czechoslovakia and Hungary. A militarised variant, the Fw58B, was ordered by the Luftwaffe for the staff transport role, and were also employed as air ambulances. The Luftwaffe’s Fliegerforschutzverband used the type to carry out spraying operations in the middle Danube district, protecting seed potatoes against spring frosts by smoke spraying. The principal production version was the Fw58C aircrew trainer, which became standard equipment of the Luftwaffe’s training establishments and was successfully exported to Bulgaria and Brazil, among other nations. In the training role the Fw58 could be fitted with a gunner’s station in the nose and could be outfitted for bombing, navigation or wireless training. Production of the type was continuing in 1940, by which time some 1,230 machines of all types had been produced, including 110 machines for export.

Technical Description

Low wing cantilever monoplane in three sections. Rectangular centre-section and two outer sections with back-swept leading edges and straight trailing edges. Structure consists of a single duralumin girder spar to which is attached the metal-covered leading edge. Metal ribs connect the main spar to the auxiliary spar to which are hinged the Frise ailerons and camber-changing flaps. The portion aft of the main spar is fabric covered. Ailerons and flaps are metal-framed and covered with fabric.

Fuselage is a rectangular structure of welded chrome-molybdenum steel tubing with a light subsidiary fairing structure of duralumin with fabric covering. Conical metal nose may be detached and replaced with a gunner’s cockpit.

Monoplane type tail unit. Duralumin framework with fabric covering. Adjustable tailplane mounted in advance of the fin, which is built integral with the fuselage. Statically and aerodynamically balanced elevators and rudders. Elevators and rudder provided with controllable trimming tabs.

Retractable type undercarriage. Each triangulated unit consists of a hinged fork, the legs of which are sprung to two oleo-pneumatic shock absorbers. The Vee-struts to which the forks are hinged are mounted on a transverse tube and are raised aft by an oleo-pneumatic jack screw. When the units are in the fully-raised position within the tails of the engine nacelles hinged doors close the aperture. Low pressure wheels and brakes. Orientable tail wheel.

Two 240 hp Argus As10C eight-cylinder inverted Vee air-cooled engines on welded chrome-molybdenum steel tube mountings cantilevered from the main spar of the centre-section. Two welded aluminium fuel tanks (340 litres total capacity) in the centre-section aft of the main spar, on either side of the fuselage. Oil tanks (17 litres capacity) in each engine nacelle.

Gunner’s or bomb aimer’s training station in the nose. Pilots’ enclosed cockpit over the leading edge of the wing seats two side-by-side with complete dual controls. Behind the pilots’ cockpit is a wireless compartment, aft of which is a further compartment with side windows and bomb trap with sights for bombing instruction. An after gun position can be installed above this compartment.

Span 21 metres, length 14.1 metres, height 4.2 metres. Wing area 47 square metres. Empty weight 1,970 kg, loaded weight 2,900 kg. Wing loading 6.1 kg per horsepower.

Maximum speed at 1,000 metres 254 kph, cruising speed at 2,000 metres 238 kph, landing speed 76 kph. Climb to 1,000 metres 3 minutes 8 seconds, to 3,000 metres 14 minutes. Ceiling 5,400 metres. Range 835 kilometers.

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 be 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 tat 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 801ML fourteen-cylinder two-row radial air-cooled engines each rated at 1,580 hp for takeoff and 1,380 hp at 5,000 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 arranged thusly – centre-section tank 1,045 litres, two inner wing tanks each 795 litres, two oil tanks outboard of engines each 200 litres and two outer wing tanks each 160 litres. Carbon-dioxide gas may be released into tank compartments in emergency. VDM three-bladed fully-feathering airscrews.

Crew of four housed in cabin forward of the wing. Pilot on port side with spectacle-type control column which slides into dashboard on rack and pinion for elevator control. Bomb-aimer in nose or seated beside pilot. Wireless operator behind pilot. Rear gunner aft. Cabin heating by exhaust pipe muffs. Hot air sprays from cabin heating are fitted to the pilot’s windscreen and to all transparent nose panels. Pilot’s seat is fully armour-plated and there is armour plate to the sides of the gun turret. Twin 7.92mm MG81 machineguns with 1,000 rounds on flexible mount in the nose; one 15mm MG151 machinegun with 1,000 rounds in dorsal turret and one 15mm MG151 with 1,000 rounds in the lower rear position. Stowage for a maximum of 2,250 kg of ordnance in the fuselage bomb cell. Provision for fitting two external bomb racks under wings outboard of the engines.

Span 19 metres; Length 17 metres. Gross wing area 56.6 square metres; net wing area 48.5 square metres. Weight loaded 15,590 kg.

Maximum speed at sea level 464 kph, at 6,710 metres 528 kph. Initial climb rate 216 metres/minute. Service ceiling (fully loaded) 7,320 metres, service ceiling (light) 8,235 metres. Range with maximum fuel 3,840 kilometres.

Technical Description

Low wing cantilever monoplane; straight leading edge, tapering trailing edge, with squared off wing tips. All metal structure with flush-riveted smooth stressed skin. Split flaps between ailerons and fuselage.

Fuselage is of oval section, an all-metal structure with flush-riveted stressed skin covering.

Cantilever monoplane type tail unit. All metal framework with metal-covered fixed surfaces and fabric covered elevators and rudder.

Retractable type undercarriage. Main wheels raised inwardly into underside of the wings by hydraulic action. Retractable tail wheel.

One Daimler-Benz DB601N twelve-cylinder inverted Vee liquid cooled engine rated at 1,200 hp for take off and 1,175 hp at 5,000 metres. Self-sealing fuel tanks in the wings and fuselage. VDM adjustable pitch airscrew.

Pilot’s cockpit is located over the rear wing spar. Pilot is provided with 8mm armour plate at the rear of the cockpit. Armament comprises two 7.92mm MG 17 with 400 rounds of ammunition per gun in the forward fuselage decking synchronised to fire through the propeller arc and two 20mm MG 201 with 150 rounds of ammunition per gun, located in either wing outboard of the propeller arc. Full wireless installation and oxygen equipment fitted.

Span 11.88 metres, length 8.84 metres, wing area 20 square metres. Weight empty 2,629 kg, weight loaded 3,469 kg.

Maximum speed 600 kph at 5,000 metres, 535 kph at sea level. Climb to 5,000 metres 7 minutes. Service ceiling 9,750 metres. Range 1,230 kilometres.

Technical Description

Low wing cantilever monoplane. Wing in two sections, each attached directly to the fuselage. Each wing section is tapered throughout its length and has a small squared tip. Aspect ratio 7.3:1. Ratio of root thickness to chord is 0.185. Structure consists of a single spar at 39% of chord from the leading edge, former ribs at 25mm intervals except where nacelle and landing gear gap occurs, and lateral stringers placed 305mm apart, the whole covered with a stressed metal skin. Wings are attached to the fuselage at three points – at the leading edge and at the top and bottom booms of the main spar. Hydraulically operated slotted flaps (20% of the chord) and slotted ailerons with external mass-balanced weights. Landing flaps may be lowered at 250 kph.

Fuselage is an oval all-metal stressed skin structure in two halves with longitudinal joints top and bottom. Each half is made up of a number of longitudinal stringers and a series of vertical panels. Every other panel has its edges flanged to form ‘Z’ frames and these frames are holed to let the stringers pass through. The flanged panels have their edges treated so that the alternate plain panels may be flush riveted to give a completely smooth outer surface. The longitudinals have a single row of rivets to the outer skin only. Each half of the fuselage is butt-jointed top and bottom to a double-width longitudinal.

Cantilever monoplane type tail unit with fins and rudders at extremities. All metal framework with metal-covered fixed surfaces and fabric covered control surfaces. Trimming tabs in elevators and rudders.

Retractable type undercarriage. Wheels are toed-out and retract backwards into engine nacelles. Hinged doors close apertures when wheels are raised. Hydraulic retraction. Fixed tail wheel.

Two Daimler Benz DB-601N engines rated at 1,200 hp for takeoff on cantilever mountings attached to wing spars. Radiators outboard of the nacelles forward of the flaps. They extend upwards into the depth of the wing and are ducted with electrically operated exit flaps. Oil coolers under noses of nacelles, with manually operated exit flaps. VDM three-bladed controllable pitch full feathering airscrews. Four fuel tanks, two on each side of the fuselage, fore and aft of the wing spar. Normal fuel capacity 1,270 litres. There is provision for jettisonable streamline tanks outboard of the nacelles. Oil tank behind each engine holds 43 litres.

Crew of two – pilot and wireless operator/air gunner – seated in a cockpit covered by a long canopy. Fixed forward armament comprises four 7.92mm MG81 machineguns with 225 rounds per gun and two 15mm MG 151 machineguns with 225 rounds per gun located in the nose of the aircraft; twin flexible 7.92mm MG81 machineguns with 225 rounds per gun located in the rear of the cockpit for the use of the air gunner. The aircraft is fitted with an ETC rack beneath the central fuselage for the carriage of one H4D torpedo, two 500 kg or four 250 kg bombs, or up to eight 50 kg bombs.

Span 16.2 metres; Length 12.3 metres; Height 3.9 metres; Wing area 37.17 square metres. Normal loaded weight 7,000 kg.

Maximum speed 530 kph at 5,000 metres, 460 kph at sea level. Maximum cruise speed 480 kph at 5,000 metres, 420 kph at sea level. Normal range 770 km at 420 kph at sea level, 850 km at 480 kph at 5,000 metres. Service ceiling 10,000 metres.

Technical Description (Interim)

Enclosed cabin for a crew of three. Navigator/observer’s station in the extreme nose of the aircraft; pilot’s station in the front of the main flight deck, with station for wireless operator/air gunner in the rear. All stations provided with extensive transparent canopy. Provision for one flexible forward-firing 7.92mm MG81 machinegun with 225 rounds in the observer’s station and one flexible aft-firing 7.92mm MG81 machinegun with 225 rounds in the wireless operator’s station. Ordnance carried can include one 750 kg aerial torpedo and two 250 kg bombs, one 1,000 kg aerial mine and two 250 kg bombs or five 250 kg bombs.

Two BMW 132K nine-cylinder radial air cooled engines rated at 970 hp.

Span 22.2 metres; Length 17.3 metres; Height 6.6 metres; Wing area 87.5 square metres. Empty weight 5,300 kg; maximum mixed attack payload 1,500 kg; normal loaded weight 9,100 kg; maximum loaded weight 10,400 kg.

Maximum speed at 3,400 metres 355 kph; cruising speed at 3,400 metres 295 kph; alighting speed 115 kph. Initial rate of climb 235 metres/minute; service ceiling 5,500 metres. Normal range 2,000 kilometres; maximum range 3,350 kilometres.

(Compliments to Marek for the original artwork on which the drawing is based)

Technical Description

High wing semi-cantilever monoplane. Centre-section carrying the three engines is supported above the hull by inverted Vee struts and braced by sloping parallel struts to the patent Dornier sea wings, which give lateral stability on the water and increase the area of the lifting surface in flight. Cantilever tapering outer wing sections. Wing structure of metal, covered with fabric, except in the slipstream of the engines, where the wing is metal covered. Auxiliary surfaces hinged slightly below trailing edge of wings act as ailerons and landing flaps.

Semi-circular hull with characteristic Dornier undersurfaces and patent sea wings. Vee bottom forward, becoming flatter at the first step. Rear step fairs into a vertical knife edge. All metal structure with smooth, flush-riveted outer skin.

Braced monoplane type tail unit with twin fins and rudders. Metal structure with metal-covered fixed surfaces and fabric-covered movable surfaces. Statically and aerodynamically balanced rudders with servo flaps. Statically balanced elevators.

Three Brandenburgische Motorenwerke 323 nine-cylinder radial air cooled engines rated at 1,000 hp for takeoff, mounted in line along the leading edge of the centre-section. Three-bladed controllable pitch airscrews. NACA cowlings. Fuel tanks fitted in the sea wings.

Normal crew of six. Pilots’ compartment seats two side-by-side, with navigator’s and wireless operator’s positions behind. Within the hull below the centre-section is the living and sleeping accommodation for the crew. Aft of the wing is the mid-upper gunner’s position, and in the extreme tail a second gunner’s position, both equipped with rotating turrets. The boat is fully equipped for extended cruises away from its base. Four fixed 7.92mm MG81 machineguns with 500 rounds of ammunition per gun located in the nose of the aircraft, one 20mm MG201 cannon with 330 rounds of ammunition located in the mid-upper position and two 7.92mm MG81 machineguns with 500 rounds of ammunition per gun located in the tail position. Shackles under the wing for up to four 100 kg bombs, four depth charges or two sea mines.

Span 27 metres; Length 22 metres; Height 5.45 metres. Wing area 108 square metres. Weight loaded 13,500 kg.

Maximum speed 304 kph; cruising speed 260 kph at 2,000 metres; alighting speed 109 kph. Climb to 1,000 metres 7.5 minutes, to 2,000 metres 14.5 minutes. Service ceiling 5,300 metres. Maximum range 3,300 kilometres.

Technical Description

High wing braced monoplane. Wings are carried above the fuselage by a steel cabane and braced to the fuselage by Vee struts. Two spar metal structure. Built up of girder spars, pressed metal ribs in three portions riveted to the spars and duralumin sheet covering except for a strip of fabric on the underside of the wing. Detachable sheet metal panel on the underside of the wing behind the front spar for internal inspection. Metal framed ailerons with fabric covering. Ailerons are aerodynamically and statically balanced and have trimming tabs adjustable on the ground. Hydraulically operated camber-changing flaps between ailerons and fuselage.

Oval light metal fuselage. Stressed skin monocoque terminating at its forward end in four main longerons that carry the attachment points for centre section struts, engine bearers and undercarriage. Forward portion covered with detachable metal panels.

Braced monoplane type tail unit. Tail plane mounted at the base of the fin and braced to the fuselage by single struts. Light metal fin works with fixed surfaces covered by metal, with elevators and rudders covered by fabric. Control surfaces are aerodynamically and statically balanced and are fitted with trimming tabs.

Single leg cantilever type undercarriage. Springing accomplished partly by tyres and party by annular spring units provided in the fuselage. Steel legs and axles enclosed in light metal fairings, which incorporate hinged foot rests for servicing the engine. Hydraulic wheel brakes. Swiveling and sprung tail wheel with centre lock.

One Brandenburgische Motorenwerke Fafnir 323A-1 nine cylinder radial air-cooled engine rated at 850 hp for takeoff and 830hp at 4,000 metres. NACA cowling with controllable gills. Three bladed VDM controllable pitch airscrew. Fuel tank (540 litres) in fuselage in front of pilot. Oil tank (36 litres) in engine compartment.

Pilot and observer seated in tandem cockpits behind the trailing edge of the wing. Transparent canopy over cockpit, fixed over pilot, sliding over observer. Adjustable pilot's seat and rotating and folding observer's seat. One fixed 7.92mm MG17 firing through the airscrew and one flexible .7.92mm MG15 for the observer. 500 rounds of ammunition for the fixed gun and 1,000 rounds of ammunition for the flexible gun. Transmitting and receiving wireless in observer's cockpit with windmill generator and fixed as well as trailing antennas. Topographic camera installation behind observer and stowage for hand camera in cockpit. Fixed camera can be replaced by two bomb containers each carrying five 10-kg bombs. Provision for installation of smoke screen apparatus in place of camera or bomb containers. Complete electrical equipment with engine driven generator and storage batteries for navigation, instrument and landing lights, electric fuel gauges, camera or bomb container, and variable pitch airscrew. Oxygen equipment fitted.

Span 14.48 metres, length 10.84 metres, height 37.3 metres, wing area 31.59 square metres. Weight empty 2,034 kg, crew with parachutes 200 kg, fuel and oil 444 kg, military load 414 kg. Weight loaded 3083 kg.

Maximum speed at sea level 310 kph, speed at 3,000 metres 354 kph. Landing speed 95 kph. Climb to 2,000 metres, 3.5 minutes, to 4,000 metres, 7.2 minutes. Service ceiling 8,500 metres. Cruising range at 4,000 metres, 1,100 kilometres.

Technical Description

Low wing cantilever monoplane; centre-section carrying the two engine nacelles is built integrally with the fuselage. Two tapering outer sections; straight leading edge and swept forward trailing edge from roots to tip. Two spar all-metal construction with stressed-skin covering. Entire trailing edge hinged, the outer sections acting as slotted ailerons and the inner section as slotted flaps.

Fuselage is a triangular cross-section structure with the wing centre-section built into its broad base. Nose-section of spot welded 12mm armour plate, the remainder of light metal stressed skin construction. Total weight of nose armour 1,080 kg.

Cantilever monoplane type tail unit. All metal structure. Tailplane incidence adjustable on the ground.

Retractable type undercarriage. The single-leg main units retract hydraulically backwards into the engine nacelles, a portion of the wheels protruding slightly from the nacelles when raised. Non-retractable tail wheel.

Two Brandenburgische Motorenwerke Fafnir 323A-1 nine cylinder radial air-cooled engines rated at 850 hp for takeoff and 830hp at 4,000 metres. Self-sealing fuel tanks in wings and fuselage; the two wing tanks having a capacity of 205 litres and the fuselage tank 200 litres. Lower halves of the engines protected by 5mm armour plate.

Pilot seated in the nose of the aircraft. Windscreen with bullet-resistant armoured class 75mm thick in a 6mm armoured frame. Internal armament comprises two 7.92mm MG17 with 500 rounds of ammunition per gun and two 20mm MG201 with 125 rounds per gun located in the nose of the aircraft. Attachment points beneath the fuselage and wing for a variety of ordnance including: one 250 kg SC250 bomb beneath the fuselage and two 50 kg SC50 or forty-eight 2 kg SD2 bombs beneath the wing or four 50 kg SC 50 and ninety-six 2 kg SD2 bomblets beneath the fuselage and wings. Provision for installation of smoke-screen apparatus in place of ordnance. Oxygen equipment fitted.


Span 13.50 metres, length 10.10 metres, wing area 28.30 square metres. Weight empty 3,980 kg, weight loaded 5,000 kg.

Maximum speed 408 kph at 3,000 metres. Climb to 3,000 metres 7 minutes. Service ceiling 9,000 metres. Range 560 kilometres.

Technical Description (Interim)

Enclosed cabin for student pilot and instructor in tandem. Can be fitted with one 7.92mm MG17 with 220 rounds for weapons training.

Argus As410 twelve-cylinder inverted Vee air-cooled engine rated at 465 hp.

Length: 9.1 metres; Wingspan 11 metres; Height 2.6 metres. Wing area 17.1 square metres; Empty weight 1,285 kg, maximum take-off weight 1,700 kg.

Maximum speed 330 kph; cruising speed 295 kph. Service ceiling 7,100 metres. Range 990 kilometres.

Service History

The Bf108 “Taifun” (Typhoon) four-seat sport aircraft appeared in 1934 as an entrant in the fourth Challenge de Tourisme Internationale. It was the first aircraft of its size to utilise all metal stressed-skin construction, and its wing featured a patented single-spar design, trailing-edge slots and automatic leading-edge slots that opened on approaching the stall. The aircraft proved most pleasant to fly, was fast, safe and had excellent low-speed qualities. During the latter part of the 1930s featured in many international air races, and in July 1939 set a new altitude class record of 9,075 metres.

In addition to the units manufactured for private customers, the type was adopted by the Luftwaffe as a liaison aircraft, being assigned both to operational units at home, as well as being allocated to German air attaches stationed abroad. It is operated in considerable numbers by the Luftwaffe, and it has been exported to numerous other countries for both civil and military use. It continues in low-level production at this time primarily to meet export requirements.


Technical Description (interim)

One 240 hp Argus As10C air-cooled inline engine.

Span 10.62 metres; Length 8.29 metres; Wing area 16.40 sq. metres. Empty weight 880 kg; Fuel and oil 172 kg; Pilot and three passengers 300 kg; Loaded weight 1,352 kg.

Maximum speed 303 kph; cruising speed 265 kph; landing speed 85 kph. Initial climb rate 360 metres/minute, take off distance 240 metres; landing distance 230 metres; service ceiling 5,000 metres. Maximum range 1,000 kilometres.

Technical Description

Low-wing cantilever monoplane. Wings have constant taper in thickness but in plan form the portion of the wing between the fuselage and the engine nacelles is of almost constant chord whereas portions outboard have a double taper. All-metal two spar structure with flush riveted stressed skin covering. Entire trailing edge is hinged, the outer portions acting as ailerons and the inner sections as landing flaps. Slatted diving brakes hinged beneath front spar and outboard of engine nacelles. Hot air leading edge deicing.

Oval metal monocoque fuselage built up of a number of Z-section frames and top-hat stringers to which is riveted the smooth stress-bearing skin.

Cantilever monoplane-type tail unit. All-metal framework with metal covered fixed surfaces and fabric covered elevators and rudders. Rubber pulsating overshoe type de-icers on tailplane leading edge.

Retractable type undercarriage. Wheels are retracted backwards and turn through ninety degrees to lie flat in lower portions of engine nacelles. Electrically retracted tail wheel.

Two Junkers Jumo 211J twelve-cylinder inverted Vee-type liquid cooled engines each rated at 1,340 hp for takeoff and 1,060 hp at 5,340 metres. Circular nacelles with circular frontal radiators incorporating both water and oil cooling elements. There are five self-sealing fuel tanks – four in the wings – two of 324 litres inboard of the engine nacelles and two of 405 litres outboard of the nacelles, and a fifth tank of 1,125 litres in the fuselage bay between the wing spars. Provision is made for fitting another fuselage tank of 690 litres in the after bomb cell. All tanks are provided with solenoid-operated air pressure valves and discharge pipes for jettisoning the contents. VDM controllable pitch full-feathering airscrews.

Provision for a crew of four grouped closely together in portion of the fuselage forward the front spar. Pilot on left with bomb aimer alongside but at a lower level. Upper rear gunner’s position immediately behind the pilot and wireless operator’s position behind the bomb aimer but low down to enable him to operate lower rear gun. All crew positions armoured. Two forward-firing 15mm MG151 machineguns with 400 rounds per gun operated by the pilot, two 15mm MG151 machineguns with 400 rounds per gun in dorsal turret and one 7.92mm MG81 with 400 rounds in lower rear position. Internal bomb cells for two 250 kg bombs or bomb carriers for ten 50 kg bombs. Two external bomb carriers under each inner wing for bombs of up to 1,000 kg or for larger types of incendiary bomb containers or for fuel tanks.

Span 20 metres; Length 14.4 metres; Height 4.8 metres; Wing area 54.5 square metres. Normal loaded weight 12,122 kg; maximum permissible take-off weight 14,075 kg.

Maximum speed 472 kph at 5,340 metres. Climb to 5,430 metres 23 minutes. Service ceiling at mean weight 8,235 metres. Range with maximum fuel 3,040 kilometres; range with maximum bomb load of 3,000 kg 1,040 kilometres.

Technical Description

Low-wing cantilever monoplane. Rectangular centre-section between tail booms and supporting the crew nacelle on the centre-line. Tapering outer wings outside tail booms. All-metal structure with stressed-skin covering. Centre section has three spares, the main and rear spars passing through the nacelle which is rigidly attached to the centre-section. The undersurface between the main and rear auxiliary spare has detachable inspection panels. Outer sections also have three spars and have detachable leading and trailing edge sections. They are attached to centre-section by bolds along the wing contour between the main and front spars as well as at the main spar. Electrically operated fabric-covered split trailing edge flaps between ailerons and tail booms and across centre-section.

Crew nacelle is an all-metal structure extensively provided with transparent panels, riveted to centre section.

Two interchangeable oval all-metal booms are attached at the front to extensions of the engine nacelles and at the rear to the fin assembly by circumferential bolts.

Two finds of stressed-skin construction at ends of booms support between them the all-metal tailplane. Rudders and elevators have metal frames and fabric covering. Statically and aerodynamically balanced rudders and elevators. Electrically controlled trimming tabs.

Retractable type undercarriage. Main wheels are raised backwards into engine nacelles and apertures closed by hinged doors when wheels are retracted. Tail wheel retracted laterally into well in underside of tailplane. Hydraulic retraction but tail wheel lowers under its own weight with assistance of rubber hinges.

Two 450hp Argus As410A-1 twelve-cylinder inverted Vee air-cooled engines. Two-bladed Argus automatic controllable pitch airscrews. Two fuel tanks, one in the rear of each engine nacelle.

Crew of three in central nacelle. Two 7.92mm MG17 machineguns with 400 rounds per gun in wing roots, two 7.92mm MG81 machineguns with 225 rounds per gun in dorsal position. Provision for four 50 kg bombs on underwing racks.

Span 18.4 metres; Length 12 metres. Wing area 38 square metres. Weight empty with equipment 2,690 kg; weight loaded 3,410 kg; maximum take off weight 3,950 kg.

Maximum speed 344 kph at 2,440 metres. Maximum cruise speed 317 kph at 2,440 metres. Climb to 4,000 metres 8.3 minutes. Service ceiling 8,400 metres. Range 690 kilometres.