Czechoslovakian Aircraft Industry
Aero (Aero Tovarna Letadel Dr. Kabes)
Head Office and Works: Praha-Vysocany
Current Types:
Aero A.104, a two-seat biplane light bomber and reconnaissance aircraft. It is the final derivative of the A.100, and is essentially an Ab.101 with an enclosed cockpit. Two different prototypes flew in 1937 and 100 were built for the Czech Air Force during 1938.
Length: 10.80 m (35 ft 5 in)
Wingspan: 15.50 m (50 ft 10 in)
Wing area: 35.40 m² (380 ft²)
Loaded weight: 3,100 kg (6,800 lb)
Powerplant: 860hp Avia-built Hispano-Suiza 12Ydrs
Maximum speed: 330 km/h (210 mph)
Range: 1,000 km (630 miles)
Service ceiling: 9,000 m (30,000 ft)
Rate of climb: 6.8 m/s (1,340 ft/min)
Wing loading: 88 kg/m² (18 lb/ft²)
Power/mass: 0.21 W/kg (0.13 hp/lb)
Armament: one fixed forward-firing and one dorsal-mounted 7.92 mm ZB-30 MG and 200kg (440lbs) of bombs
Aero A.300, a three-seat monoplane light bomber first flown in 1938 as a much refined development of the A.304 and put into production for the Czech Air Force during 1939.
Length: 13.50 m (44 ft 3 in)
Wingspan: 19.20 m (63 ft 0 in)
Height: 3.40 m (11 ft 2 in)
Wing area: 46 m² (495 ft²)
Empty weight: 3,955 kg (8,721 lb)
Max takeoff weight: 6,040 kg (13,318 lb)
Powerplant: two 818hp Bristol Mercury IX 9-cylinder radials
Maximum speed: 470 km/h (294 mph)
Range: 900 km (563 miles)
Service ceiling: 8,300 m (27,224 ft)
Armament: three 7.92 mm ZB-30 MGs (one nose-mounted, another in a dorsal turret and ventral position) and up to 1,000 kg (2,200lbs) of bombs
Aero A.340, a two-seat twin-engined fighter-bomber. It has a mid-set monoplane and twin tailfins and the engine nacelles are designed to minimise drag with encased propeller hubs to aid cooling with an annular radiator. A tailwheel undercarriage is fitted and the two crewmen sit back-to-back in tandem. The first prototype flew in May 1941 with the second prototype following six months later. Service entry with the Czech Air Force began during late 1942 and 154 aircraft were ordered.
Length: 12.8 m (42 ft 0S in)
Wingspan: 13.33 m (43 ft 9 in)
Height: 3.95 m (12 ft 11½ in)
Wing area: 31.3 m² (337 ft²)
Empty weight: 6,200 kg (13,669 lb)
Loaded weight: 9,450 kg (20,833 lb)
Powerplant: two 1,450hp Minerva-Avia 105 V-12s
Maximum speed: 528 km/h (330 mph) at 6,000 m (22,960 ft)
Cruise speed: 480 km/h (300 mph)
Range: 2,000 km (1,240 miles)
Service ceiling: 10,500 m (34,500 ft)
Rate of climb: 545 m/min (1,790 ft/min)
Climb to 6,000 m (19,700ft): 11 min
Armament: two fixed forward-firing 7.92 mm wz.30 MGs in the lower nose and two fixed forward-firing 20mm Orkileon MG FF cannons in the wingroots, one dorsal-mounted 7.92 mm wz.30 MG and up to 1,000kg (2,200lbs) of bombs mounted on ventral and underwing bomb racks
Aero A.350, a tri-engined airliner seating 32 passengers with a galley, toilet and baggage space. The monoplane wing is mounted low and is a single-piece unit bolted to the fuselage at four points. The wing houses fuel tanks with a capacity of 4,700 litres (1,034 gal), the nacelles have NACA-type cowlings and the engines are fitted as ‘power-eggs’ and the engines have three-bladed propellers. A sturdy tailwheel undercarriage is fitted. The flight crew of four are sat forward in the square-section fuselage with the passenger cabin behind and the baggage compartment in the tail. A door is fitted in the rear portside. The prototype first flew on 18 August 1941. Production will be carried out with assistance of Letov. CSA ordered 15 with delivery from late-1942.
Length: 24.60 m (80 ft 8½ in)
Wingspan: 34.20 m (112 ft 2¾ in)
Height: 5.74 m (18 ft 10¼ in)
Wing area: 128.20 m² (1,379.90 ft²)
Empty weight: 12,500 kg (27,563 lb)
Max takeoff weight: 19,600 kg (43,216 lb)
Powerplant: three 986hp BMW Bramo 323 R-2 Fafnir 9-cylinder radials
Maximum speed: 370 km/h (230 mph) at 5,050 m (16,565 ft)
Cruise speed: 240 km/h (149 mph)
Range: 1,800 km (1,118 miles)
Service ceiling: 6,000 m (19,686 ft)
Aero A.145, a twin-engined all-metal three/ four passenger light aircraft. The development began during 1943 by the technical designers Jiři Bouzek, Ondřej Němec and František Vik. The rear bench carries up to three passengers or can be folded away to stow freight or luggage. The pilot is seated ahead of the passengers and an optional seat beside the pilot can carry a fourth passenger. The first flight was on 27 July 1944. Orders have been placed by the Czech airline CSA and several private companies for use as air-taxis and business aircraft.
Length: 7.54 m (24 ft 9 in)
Wingspan: 12.25 m (40 ft 2 in)
Height: 2.30 m (7 ft 7 in)
Wing area: 17.09 m² (184 ft²)
Empty weight: 960 kg (2,112 lb)
Loaded weight: 1,510 kg (3,322 lb)
Max takeoff weight: 1,600 kg (3,527 lb)
Powerplant: two 105hp Walter Minor-III 4-cylinder inlines
Maximum speed: 265 km/h (165 mph)
Range: 1,600 km (1,000 miles)
Service ceiling: 4,400 m (14,400 ft)
Rate of climb: 300 m/min (984 ft/min)
Aero A.45, a single-engined two-seat military reconnaissance aircraft for the artillery spotting role. The design features a high-wing monoplane with a fuselage that terminates immediately aft of the crew cabin, with the tailplane mounted on a boom attached to the wing. The tailwheel is mounted at the rear of the fuselage. The wing has leading-edge slots for good STOL capability. This arrangement maximises the observer's field of view. Another unusual feature is provision for a towing point to allow it to be towed by another, longer-range aircraft to enable it to be transported to a combat zone outside of its own range without having to stop and refuel. The first fight was on April 14 1946, it was evaluated against the Praga E.55. The Czech Air Force plans to begin operating the type during early 1948.
Length: 7.1 m (23 ft 4 in)
Wingspan: 10.5 m (34 ft 5 in)
Height: 2.46 m (8 ft 1 in)
Wing area: 15.1 m2 (163 sq ft)
Empty weight: 460 kg (1,014 lb)
Gross weight: 730 kg (1,609 lb)
Powerplant: one 105hp Walter Minor 4-III
Maximum speed: 171 km/h (106 mph)
Service ceiling: 4,370 m (14,337 ft)
Rate of climb: 2.333 m/s (459.3 ft/min)
Ae-148, a passenger aircraft seating 12 passengers and powered by two 550/700hp Walter M-446V-12 engines. First flown during1946.
Aero A.345, a twin-engined all-metal three/ four passenger light aircraft. This aircraft is an improved Ae-145 with increased power engines, longer span wings, retractable tailwheel and a modernised cabin. The first flight was 16 June 1947.
Length: 7.54 m (24 ft 9 in)
Wingspan: 12.60 m (46 ft 7 in)
Height: 2.30 m (7 ft 7 in)
Wing area: 17.09 m² (184 ft²)
Empty weight: 960 kg (2,112 lb)
Loaded weight: 1,510 kg (3,322 lb)
Max takeoff weight: 1,600 kg (3,527 lb)
Powerplant: two 125hp Walter Minor-IV 4-cylinder inlines
Maximum speed: 270 km/h (168 mph)
Range: 1,600 km (1,000 miles)
Service ceiling: 4,400 m (14,400 ft)
Rate of climb: 300 m/min (984 ft/min)
Ae-160, a passenger aircraft seating 15 to 17 passengers and powered by four 320hp Walter M-436 V-6 engines. Maximum speed is 350 km/h (220mph). The first of two prototypes first flew 23 May 1948.
Avia (Avia Akciova Spolecnost Pro Prumysl Letecky)
Head Office and Works: LetHany
The company was founded by Pavel Beneš, Miroslav Hajn, Jaroslav František Koch and Václav Malý in 1919 and became part of Škoda in 1928. During the 1930s the factory became the biggest aircraft producer in Czechoslovakia and moved to LetHany. In August 1931 the Dutch firm of Fokker took over Skoda’s share of Avia. Avia gained access to the Fokker design team and modern construction methods and Fokker primarily uses Avia-built versions of Bristol or Gnome-Rhone radials and Hispano-Suiza in-lines.
Current Types:
Avia B.135, a single-seat single-engined fighter first flown in 1935 and produced for the Czech Air Force and offered for export.
Length: 8.50 m (27 ft 11 in)
Wingspan: 10.85 m (35 ft 8 in)
Height: 2.60 m (8 ft 6 in)
Wing area: 17.0 m² (183 ft²)
Empty weight: 2,063 kg (4,548 lb)
Gross weight: 2,547 kg (5,615 lb)
Powerplant: one Avia-built 860hp Hispano-Suiza 12Ycrs
Maximum speed: 535 km/h (332 mph)
Range: 550 km (340 miles)
Service ceiling: 8,500 m (27,890 ft)
Rate of climb: 13.5 m/s (2,660 ft/min)
Armament: one fixed-forward firing 20 mm Orkileon MG FF cannon firing through the propeller hub and two 7.92 mm wz.30 MGs above the engine
Fokker-Avia B-137, a single-seat single-engined fighter first flown in 1937, the Bulgarian manufacturer DAR has a production-licence.
Length: 9.07 m (29.78 ft)
Wingspan: 11.42 m (37.47ft)
Wing Area: 202 ft2
Empty Weight: 2,156 kg (4,754 lbs)
Maximum Weight: 2,590 kg (5,732lbs)
Engine: one 1,100hp Minerva-Avia 105
Stresses: 362 IAS, 10G
Rate of climb: 17 m/s (3,364 ft/min) (light)
Maximum speed: 601 km/h (374mph) at 4,000 m (13,123 ft)
Max Range: 804 km (500 miles)
Service ceiling: 12,039 m (39,500 feet)
Armament: one fixed-forward firing 20 mm Orkileon MG FF cannon firing through the propeller hub, two 7.92 mm wz.30 MGs above the engine and two more in wingroots plus one ventral 250kg bomb
Fokker-Avia B-139, an improved B-137 with a 1,450hp Minerva-Avia 105 V-12 inline engine and aerodynamic improvements for the Czech Air Force. Production began in late 1939.
Maximum speed: 624 km/h (387mph)
Rate of climb: 16.5 m/s (3,248 ft/min) (normal weight)
Fokker-Avia B.142, a single-seat short range, high speed bomber interceptor developed in 1940. This plane is a big engine small bodied sports car of a plane, armed with multiple cannons generate a large number of 20mm hits per firing pass. The fairly high wingloading would prove limiting in a traditional lower elevation dogfight, but this is of less import at altitude and for bomber-hunting, where energy fighter tactics are envisioned. Production for the Czech Air Force began in early 1941 and has now switched to the improved Series II.
Length: 9.14 m (30 ft 0 in)
Wingspan: 9.45 m (31 ft 0 in)
Wing area: 14.59 m² (157 ft²)
Empty weight: 2,588 kg (5,705 lb)
Max takeoff weight: 3,200 kg (7,055lb)
Powerplant: 1 x 1517hp Minerva Paladin II v14-cylinder inline
Range: 896 km (557 miles)
Maximum speed: 691km/h (429 mph) @ 5000m
Service ceiling: 12,192 m (40,000 ft)
Rate of climb : 1064 m/m (3,490 ft/m)
Wingloading Loaded / Empty : 44.9 lbs/ ft², 44.2 lbs/ ft²
Armament: 3x20mm 120rpg, 2x13.2mm 450rpg
Armour : Windscreen, 10mm around engine, 10mm disk aft, self-sealing tanks
Payload : None.
Cost 1940: $37,000
1942 B.142 Series II stats
Powerplant: 1 x 1643hp Minerva Paladin IV v14-cylinder inline
Maximum speed: 713kph (443mph) @ 6000m
Service ceiling: 12,497m (41,000ft)
Rate of climb : 1168 m/m (3,833ft/m)
Cost 1942: $39,000
Fokker-Avia B.144, a single-seat general purpose fighter developed in 1941 to replace the B.135 and B.137 series. It is a well-rounded machine. Choosing to use a heavily cowled radial in the pattern of the FW190 and Renard R37, this also means there will be no competition with the B.142 for engines. Further, the Faucon can be swapped out for Gnome-Rhone, Bristol and Pratt & Whitney engines of similar diameter, allowing customers to match existing equipment if so desired. .
Length: 8.23 m (27 ft 0 in)
Wingspan: 10.36 m (34 ft 0 in)
Wing area: 23.32 m² (251 ft²)
Empty weight: 3,184 kg (7,019 lb)
Max takeoff weight: 3,992kg (8,800lb)
Powerplant: 1 x 1735hp Faucon XVII v14-cylinder radial
Range: 1100km (684miles)
Maximum speed: 690km/h (429 mph) @ 6000m
Service ceiling: 11,430 m (41,000 ft)
Rate of climb : 956 m/m (3,138 ft/m)
Wingloading Loaded / Empty : 35 lbs/ ft², 33 lbs/ ft²
Armament: 1x20mm 250rpg, 4x13.2mm 600rpg
Armour : Windscreen, 8mm around engine, 8mm disk aft, self-sealing tanks
Payload : 2x100kg
Cost 1941: $49,000
Cost 1942: $50,000
Avia B-158, a three-seat twin-engined light bomber. The B-158 was designed to meet a requirement from the Czechoslovak Ministry of National Defence (MNO) for a high performance medium bomber, capable of operation during both day and night. The B-158 has a low-set monoplane with inverted gull-wings, a retractable tailwheel undercarriage and a twin tail to give a better field of fire for the dorsal gun position. The prototype first flew in mid- 1938 and production for the Czech Air Force began in 1939 alongside the Aero A.300 bomber.
Length: 12.00 m (39 ft 4 in)
Wingspan: 16.00 m (52 ft 6 in)
Height: 5.20 m (17 ft 1 in)
Wing area: 43.00 m2 (462.8 sq ft)
Empty weight: 4,300 kg (9,480 lb)
Gross weight: 6,600 kg (14,551 lb)
Powerplant: two Avia-built 850hp Hispano-Suiza 12Ydrs
Maximum speed: 435 km/h (270 mph)
Cruising speed: 365 km/h (227 mph)
Range: 1,100 km (684 miles)
Service ceiling: 8,500 m (27,887 ft)
Rate of climb: 7.00 m/s (1,378 ft/min)
Armament: three 7.92 mm wz.30 MGs (in nose, dorsal and ventral positions) and up to 1,000kg (2,200lbs) of bombs
Fokker-Avia B.159, a two-seat dive bomber developed during 1938. Developed to meet a perceived market for a dive bomber, the plane is built around a large radial engine and designed for repeated short sorties. Expecting rapid short range sorties, a radius of 185nm leaves a 25% reserve. It is armed with heavy MGs firing API ammunitions and features self-sealing tanks, armoured windscreens, and 10mm armour plating before and after the crew compartment.
Length: 8.84 m (29 ft 0 in)
Wingspan: 12.5 m (41 ft 0 in)
Wing area: 26.85 m² (289 ft²)
Empty weight: 3,362 kg (7,041 lb)
Max takeoff weight: 4,581 kg (10,100 lb)
Powerplant: 1 x 1375hp Avia Faucon II 14-cylinder radial
Range: 857 km (534 miles)
Maximum speed: 526km/h (327 mph) @ 4000m
Service ceiling: 10,700 m (35,000 ft)
Rate of climb : 615 m/m (2,019 ft/m)
Wingloading Loaded / Empty : 35.0 lbs/ ft², 31.2 lbs/ ft²
Armament: 4x13.2mm fore, 1x flexible 13.2mm aft, 450rpg
Armour : Windscreen, 10mm around engine, 10mm disk aft, self-sealing tanks
Payload : 1x500kg or 2x250kg, or 5x100kg bomb at 448km (278miles)
Cost 1938: $41,000
1942 B.159 Series II stats
Empty weight: 3,505 kg (7,728 lb)
Max takeoff weight: 5,080 kg (11,200 lb)
Powerplant: 1 x 1735hp Avia Faucon XVII 14-cylinder radial
Maximum speed: 574kph (357mph) @ 4000m
Service ceiling: 10,820m (35,500ft)
Rate of climb : 813 m/m (2688 ft/m)
Payload : 1x800kg or 2x400kg, or 4x 200kg, or 5x150kg bomb at 448km (278miles)
Cost 1942: $49,000
Fokker-Avia B.161, a five-seat “Schnell bomber” developed from early 1939. In the conflict over Grand Uruguay, fast penetrating raids by bombers against high value targets proved very difficult to intercept and defeat. With a high maximum speed and cruise speed, the available time to intercept the bomber was limited. Expecting that nations may desire to emulate this model, Avia decided to develop a fast bomber. This proved more difficult than expected. Desiring a good bomb load and range, 2 tonnes at 1,000km was settled on. Minimal defensive armament and armour was provided to deal with any fighters that proved to be in their path. If only two were used, available engines could not propel the bomber at acceptable speeds, while 4 nacelles added considerable weight, cost and frontal area for a minimal bomb load than normally found on heavy bombers. So the Avia designers, probably influenced by their time working with Fokker engineers, settled on a twin-boom, central nacelle design with three engines- two pullers fronting the booms, and a pusher on the nacelle. While the pusher would only be 80% as effective due to disrupted airflow, the additional power came with no additional frontal area, and added considerably to performance. Adopting an oval cross-section for the fuselage, narrowing down in a teardrop towards the pusher, aided airflow to the prop, and allowed turrets to be placed on the top & bottom of the oval where they could fire past the blades.
Crew : 5 (Pilot, Co-pilot/radio, Bombardier/Navigator, Engineer/Dorsal gunner, Radio/Ventral gunner) Option for 6th crewmember.
Length: 16.74 m (55 ft 0 in)
Wingspan: 17.98 m (59 ft 0 in)
Wing area: 60.29 m² (649 ft²)
Empty weight: 8,292 kg (18,281 lb)
Max takeoff weight: 13,749 kg (30,313 lb)
Powerplant: 3 x 1517hp Minerva Paladin II v14-cylinder inline
Range: 2000 km (1,242 miles)
Maximum speed: 617km/h (384 mph) @ 5000m
Service ceiling: 11,430 m (37,500 ft)
Rate of climb : 826 m/m (2,711 ft/m)
Wingloading Loaded / Empty : 46.7 lbs/ ft², 37.9 lbs/ ft²
Armament: 4x13.2mm fore, Twin 13.2mm Turrets dorsal/Ventral 450rpg
Armour : 10mm bulkhead behind cockpit, self-sealing tanks
Payload : 2500kg at 1,000km (621mi), or 3,500kg at 500km (310mi)
Cost 1939: $126,000
1942 Model B.161 Series II stats
Powerplant: 3 x 1643hp Minerva Paladin IV v14-cylinder inline
Maximum speed: 663kph (412mph) @ 6000m
Service ceiling: 11,887m (39,000ft)
Rate of climb : 813 m/m (2995 ft/m)
Cost 1942: $135,000
Fokker-Avia B-33
In 1946 Avia secured a licence to build the Russian Ilyushin Il-10 ground-attack aircraft under licence. Meant for export markets, the Dutch brought 50 in late 1946 and the first examples flew in early 1947. Several changes in armament, equipment and engine were made to suit customer requirements.
Crew: 2
Length: 11.06 m (36 ft 3 in)
Wingspan: 11.06 m (36 ft 3 in)
Height: 4.18 m (13 ft 9 in) (tail up)
Wing area: 30.00 m2 (322.9 sq ft)
Empty weight: 4,680 kg (10,318 lb)
Gross weight: 6,335 kg (13,966 lb)
Max takeoff weight: 6,535 kg (14,407 lb)
Fuel capacity: 747 L (164 imp gal; 197 US gal)
Powerplant: 1 1,592hp Avia-Minerva Paladin IIIE liquid-cooled V12 engine
Propeller: 3-bladed AV-5L-24, 3.60 m (11 ft 10 in) diameter
Maximum speed: 551 km/h (342 mph) at 2,800 m (9,200 ft); 507 km/h (315 mph) at sea level
Cruising speed: 310 km/h (193 mph) at 500 m (1,600 ft)
Range: 800 km (497 miles) at 500 m (1,600 ft)
Service ceiling: 5,500 m (18,045 ft)
Time to altitude: 5 minutes to 3,000 m (9,800 ft)
Armament: 4× 23 mm Madsen cannon (150 rpg) and 1× 12.7 mm GAST machine gun (550 rpg) in dorsal turret; 4× rockets or 6× 50 kg (110 lb) or 4× 100 kg (220 lb) or 2× 250 kg (550 lb) bombs underwing
Avia Av-36 Bojar/ Av-236 Bojar Major
This side-by-side two-seater cabin light aircraft was designed under the leadership of Ing. František Novotný. The wings have a wooden two-spar structure with plywood covering while the fuselage is of welded steel-tube structure with fabric covering. The prototype made its first flight on July 16, 1946. During 1947, the prototype was fitted a more powerful 105hp Toma 4 engine and the fuselage was lengthened to 7.98 m (26 ft 2.2 in) as the Av-236. It had superior performance including a maximum speed of 219 km/h (136 mph) and a ceiling of 4000 m (13,120 ft).
Span: 10.59 m (34 ft 9 in)
Length: 7.09 m (23 ft 3 in); Av-236 7.98 m (26 ft 2.2 in)
Height: 1.96 m (6 ft 5 in)
Wing area: 15 sq m (161.4 sq ft)
Powerplant: one 65hp Walter Mikron 4-III with an Avia two-blade fixed-pitch wooden airscrew; Av-236 one 105hp Toma 4
Empty weight: 455 kg (1,003 lb)
Loaded weight: 655 kg (1,444 lb)
Wing loading: 43.64 kg/sq.m (8.94 lb/sq ft)
Power loading: 10.18 kg/hp (22.2 lb/hp)
Max speed: 180 km/h (112 mph) at sea level; Av-236 219 km/h (136 mph)
Cruise speed: 68 km/h (99 mph)
Climb: 150 m/min (492 ft/min)
Service ceiling: 3500 m (11,480 ft); Av-236 4000 m (13,120 ft).
Cruise range: 515 km (320 miles)
Avia Av-38
This five-seater twin boom high-wing light transport was designed under the leadership of Ing. František Novotný during 1947 and the prototype first flew in May 1948. Production began in early 1949 for aero club and private use.
Wingspan: 12.00 m (39 ft 4 in)
Length: 8.53 m (28 ft 0 in)
Height: 2.97 m (9 ft 9 in)
Wing area: 18.0 m² (193 ft²)
Empty weight: 961 kg (2,115 lb)
Max. take-off weight: 1,427 kg (3,140 lb)
Powerplant: 1x 380hp Gipsy Queen 70-3 with supercharging driving a six blade contra-rotating pusher propeller
Maximum speed: 227 km/h (141 mph)
Cruise speed: 185 km/h (115 mph)
Ceiling: 4,800 m (15,750 ft)
Climb to 1,000 m (3,300 ft): 5.7 min
Range: 950 km (590 miles)
Avia Av-42
In 1946 the Czechoslovak Air Force called for a new multi-purpose fighter and Avia designed a conventional single-engine fighter. The first of three prototypes flew in March 1948 and in January 1948 ten pre-production aircraft were built. Due to less than anticipated performance only 100 production fighters were built during 1948-49.
Length: 8.94 m (29 ft 4 in)
Wingspan: 10.36 m (34 ft 0 in)
Height: 2.59 m (8 ft 6 in)
Wing area: 23.32 m² (251 ft²)
Empty weight: 3,184 kg (7,019 lb)
Max takeoff weight: 3,992kg (8,800lb)
Powerplant: 1x 1,592hp Avia-Minerva Paladin IIIES liquid-cooled V12 driving a four-bladed VDM propeller
Maximum speed: 650 km/h (403 mph)
Range: 1,100 km (684 miles)
Service ceiling: 11,430 m (41,000 ft)
Rate of climb : 956 m/m (3,138 ft/m)
Rate of climb: 16 m/s (2,200 ft/min)
Armament: 3x 23 mm Madsen cannon and 2× 12.7 mm GAST MGs; 1x 250kg (550lb) bomb on ventral rack; 4× rockets or 4× 50kg (110lb) bombs underwing
Avia Av-50
CSA in 1948 issued a requirement for a new airliner to replace its Aero A.350 tri-motor fleet. Avia won the design competition with the Av-50 and two prototypes were flown during the spring of 1949. The first of 28 production airliners for CSA entered commercial service in July 1950. The cabin can accommodate thirty passengers sat three-abreast, though a high-density forty-seat four-abreast layout can also be used.
Length: 22.30 m (73 ft 2 in)
Wingspan: 31.70 m (104 ft 0 in)
Height: 7.90 m (25 ft 11 in)
Wing area: 99.7 m² (1,073 ft²)
Empty weight: 12,600 kg (27,778 lb)
Max. takeoff weight: 18,000 kg (39,683 lb)
Powerplant: 2x 1,874hp Avia Faucon XXI 14-cylinder air-cooled radials
Maximum speed: 440 km/h (273 mph)
Range: 1,305 km (811 miles) (with full payload)
Service ceiling: 7,400 m (24,280 ft)
Minerva -Avia Engines
Head Office and Works: LetHany
The Belgian firm of Minerva brought a controlling stake in Fokker-Avia’s engine division in the mid-1930s and the firm now builds under licence Minerva products as well as other manufacturers products. Minerva was known for its quality and “Knight” auto engines, essentially being a Belgian Rolls–Royce. The radials are primarily built in Czechoslovakia, both home designed and licensed copies. Inline engines are developed in Belgium by Minerva and built at both Belgian and Czech factories. These engines are available for export independent from the aircraft.
Products:
Paladin
While Minerva cut its teeth on licensed copies of the Hispano-Suiza 12Y, it has developed its own follow on, the “Paladin”. This is a 14-cylinder V-12 engine. In the 1930s, maximum supercharging for Avia inlines was limited to 4,000 and 5,000m. In the 1940s this has crept up to 6,000m and now Avia are developing a three-stage supercharger. The Paladin weighs roughly 1600lbs and runs on 94-Octane fuel.
1938 Paladin I 1327hp
1939 Paladin II 1517hp
1940 Paladin III 1592hp
1941 Paladin IV 1643hp
Faucon
This is an Avia-developed 14-cylinder radial engine.
1937 Faucon I 1290hp
1939 Faucon I 1375hp
1940 Faucon VI 1650hp
1941 Faucon XVII 1735hp
Beneš-Mráz (Beneš-Mráz Tovarna Na Letadla)
Head Office and Works: ChoceH
Established at ChoceH by Pavel Beneš and Jaroslav Mráz on 1 April 1935 to manufacturer light aircraft of their own design.
Current Types:
Beneš-Mráz Be-252C Beta-Scolar, a two-seat aerobatic aircraft based on the Beneš-Mráz Beta-Minor, with a structure considerably strengthened for aerobatics and a more powerful radial engine in place of the Beta-Minor's inline engine.
Another variant from 1940 is the Be-352 two-seat trainer with a 190/ 205hp Walter Major 6 engine for a maximum speed of 300 km/h (186 mph) and enclosed cockpits. In 1941 the Czech Air Force brought 150 Be-352 trainers.
Length: 7.45 m (24 ft 5 in)
Wingspan: 10.66 m (35 ft 0 in)
Wing area: 14.0 m2 (151 ft2)
Empty weight: 610 kg (1,345 lb)
Gross weight: 890 kg (1,960 lb)
Powerplant: one 120hp Walter Scolar
Maximum speed: 250 km/h (156 mph)
Range: 500 km (312 miles)
Service ceiling: 7,000 m (22,960 ft)
Rate of climb: 4.2 m/s (820 ft/min)
Beneš-Mráz Bibi , a two-seat light aircraft based on the Beta-Minor design but with side-by-side seating instead of in tandem and the cockpit was fully enclosed, retaining the Beta-Minors cantilever low-wing cantilever monoplane layout with fixed tailwheel undercarriage. Various models are made; the Be-501 two-seat cabin tourer, Be-502 Bibi four-seat development prototype, Be-550 Bibi initial production version introduced in 1936 and the Be-555 Super Bibi with many improvements first flown in 1941.
Length: 7.15 m (23 ft 5 in)
Wingspan: 11.50 m (37 ft 9 in)
Wing area: 14.0 m2 (151 ft2)
Empty weight: 240 kg (529 lb)
Gross weight: 560 kg (1,235 lb)
Powerplant: one 65hp Walter Mikron inverted air-cooled inline piston engine
Maximum speed: 195 km/h (122 mph)
Range: 700 km (436 miles)
Service ceiling: 4,000 m (13,120 ft)
Beneš-Mráz K-65 áp, a two-seat high-wing monoplane designed for light civil use. The wing is equipped with leading-edge slats and combined with flaps the type has excellent STOL characteristics. The prototype first flew during May 1943 and in early 1944 the Air Force selected the type as an artillery spotter and in December 1944 the first of 40 were delivered.
Length: 9.9 m (32 ft 6 in)
Wingspan: 14.3 m (46 ft 9 in)
Height: 3.1 m (10 ft 0 in)
Wing area: 26 m² (280 ft²)
Empty weight: 860 kg (1,900 lb)
Loaded weight: 1,260 kg (2,780 lb)
Powerplant: one 240hp Argus As.10C
Maximum speed: 175 km/h (109 mph) at 300 m (1,000 ft)
Range: 380 km (240 miles)
Service ceiling: 4,600 m (15,090 ft)
Rate of climb: 4.8 m/s (945 ft/min)
Beneš-Mráz M-2 Skaut, a wooden two-seat, single engine, low wing sports aircraft designed by Zdenk Rubli
. To simplify production, the wing and tail from his earlier M-1C Sokol was used. The prototype first flew in May 1945. The type has a side-by-side cockpit and tricycle landing gear and is a wood framed, fabric covered aircraft. It is intended for civil and sports use.
Length: 6.75 m (22 ft 2 in)
Wingspan: 10.0 m (32 ft 9 in)
Wing area: 13.8 m² (148 ft²)
Empty weight: 370 kg (815 lb)
Max takeoff weight: 660 kg (1,454 lb)
Powerplant: one 75hp Praga D
Maximum speed: 185 km/h (115 mph)
Range: 700 km (380 nm, 435 mi)
Service ceiling: 4,200 m (13,800 ft)
Rate of climb: 3.5 m/s (700 ft/min)
CKD-Praga (Ceskomoravská-Kolben-Dank Prague)
Head Office and Works: Praha-Karlin
The company was founded in 1915 as Praga, an engine manufacturing company. The company started designing aircraft in 1930–31 when the designers Pavel Beneš and Miroslav Hajn came to KD-Praga from Avia. Jaroslav Šlechta became chief designer in 1934.
Current Types:
Praga E.114, a two-seat high-wing monoplane single-engine sport airplane designed by Jaroslav Šlechta. Due to its light weight it is also called Air Baby. The prototype flew for the first time in September 1934 and series production started in 1935. There are several production variants; the basic E.114, the E.115 with a more powerful 75hp Praga D engine and enclosed cockpit and the E.117 with a tricycle undercarriage produced from 1940. Further development includes a variant powered by a Walter Micron III engine flown in 1943 as the E.118.
Length: 6.58 m (21 ft 7 in)
Wingspan: 10.90 m (35 ft 9 in)
Height: 1.65 m (5 ft 5 in)
Wing area: 15.20 m² (163.6 ft²)
Empty weight: 265 kg (584 lb)
Max takeoff weight: 465 kg (1,025 lb)
Powerplant: one 40hp Praga B2 Boxer engine
Maximum speed: 150 km/h (93 mph)
Range: 510 km (317 miles)
Service ceiling: 3,300 m (10,800 ft)
Climb to 3,000 m (9,800 ft): 43.7 min
Praga E.210, a four-seat tourer or air-taxi with a high wing cantilever monoplane, enclosed cabin for four ahead of the wing and a conventional tailwheel fixed undercarriage and twin fins. It has two engines close to the fuselage driving small propellers in a pusher layout. The wing is made in a single piece, a wooden structure built around two spars and plywood covered. The leading edge was significantly swept, but the trailing edge was straight with Schrenk type landing flaps. The Walter Minor engines were cantilevered from the rear spar on steel frames, with fairings both above and below the wings. The flat sided fuselage is built on a steel tube framework, the nose and the cabin were plywood skinned and the rest fabric covered. The prototype first flew in late 1936 with a single fin which was later altered and production began in March 1939
Length: 8.5 m (27 ft 11 in)
Wingspan: 12.5 m (41 ft 0 in)
Height: 2.07 m (6 ft 9 in)
Wing area: 17.5 m2 (188 sq ft)
Empty weight: 730 kg (1,609 lb)
Gross weight: 1,250 kg (2,756 lb)
Powerplant: two 85hp Walter Minor 4-cylinder air cooled inverted inline engines
Maximum speed: 230 km/h (140 mph)
Cruising speed: 210 km/h (130 mph)
Range: 600 km (373 miles)
Service ceiling: 4,500 m (14,764 ft)
Time to altitude: 13.6 min to 2,000 m (6,560 ft)
Praga E.51, a twin-engined three-seat fighter with the crew in the fuselage with a mid-set monoplane, twin boom layout, twin fins and a streamlined fixed tricycle landing gear and tail wheel. The construction was mixed with steel-tube fuselage with plywood and fabric covering and wooden wings. It first flew in 1937 but never entered production.
Span: 15.60 m (51 ft 1 in)
Length: 11.69 m (38 ft 3 in)
Wing area: 35.44 m 2
Empty weight: 3102 kg (6,838 lb)
Take-off weight: 4120 kg (9,083 lb)
Powerplant: two 550hp Walter Sagitta I-MR 12-cylinder inline inverted V, air-cooled engines
Maximum speed: 380 km/h (236 mph)
Cruising speed: 330 km/h (205 mph)
Time of climb to altitude 3000 m: 7 minutes 30 seconds
Ceiling: 7000 m (22,965 ft)
Range: 900 km (560 miles)
Armament: two 7.92 mm wz.30 MGs (in the nose and one in the rear gunner’s position)
Praga E.211, a development of the E.210 with more powerful 105hp Walter Minor 4-111 engines, a central fin in addition to the endplates, tricycle undercarriage, better cabin access, with a starboard side door opening onto the front seats and a port side door for the rear seat passengers. Four passengers are accommodated plus the pilot. The prototype flew on 6 July 1943. A version for light freight was first flown in December 1943.
Praga E.55, a two-seat high-wing monoplane artillery spotter with a twin fin tailplane on a boom aft. Evaluated against the Aero A.345 during 1946. It is powered by a 105hp Walter Minor engine.
XE.2, a design team led by Jaroslav Slechta, began developing the XE.1 two-seat helicopter project in 1944, fitted with twin inter-meshing rotors and powered by a 100hp Praga M-197 engine. The XE.1 was abandoned but further work led to the XE-II which flew on 14 December 1946. The XE.2 is an open single-seat helicopter with a single three-blade main rotor powered by a 75hp Praga D engine.
The specs for the XE.1 are;
Rotor diameter: 9 m (29 ft 5in)
Length: 5.92 m (19 ft 4 in)
Height: 3.6 m (11 ft 8 in)
Gross weight: 710 kg (1,565 lb)
Maximum speed: 145 km/h (90 mph)
Cruising speed: 120 km/h (74.5 mph)
Hovering ceiling: 400 m (1,312 ft)
Service ceiling: 3000 m (9,842 ft)
Range: 180 km (111 miles)
Hodek
Hodek HK-101, V. Hodek designed and produced the HK-101 high-speed two-seater monoplane. The pilot and passenger sit in tandem and the prototype was flown during September 1944. The HK-101 is powered by two 105hp Walter Minor engines.
Length 5.91 m (19 ft 3 in)
Wingspan: 7.7 m (25 ft 2 in)
Hodek HK P-1, a two-seat advanced trainer and courier aircraft based on the Hodek HK-101. It is powered by two 160hp Walter Minor 6-III engines for a maximum speed of 380 km/h (236 mph). First flown in 1948 and entered Czech Air Force service in 1949.
Letov (Vojenska Tovarna Na Letadla Letov)
Head Office and Works: Praha –Lethany
Letov was founded in 1918 by the Czechoslovakian Ministry of Defence to repair Great War-era aircraft. The first indigenous aircraft, the Letov Š-1, was designed and built in 1920. Letov is a partner in the production of the Aero A.350 airliner.
Current Types:
Š-50, a three-seat all-metal twin-engined low mid-wing monoplane with a fixed landing gear and twin fins. The prototype flew in May 1938 and production began in late 1939.
Powerplant: two 420hp Avia Rk.17 radials
Maximum speed: 305 km/h (190 mph)
Š-101, a small airliner powered by two Argus As 410 engines and seating 12 passengers and two crew. Designed in 1946, first flown January 1947 and certificated in June 1948.
Š-52, a single-seat jet-powered fighter. Development began in June 1947 and the first of three prototypes flew on 21 August 1949. The prototypes were followed by ten pre-production aircraft during 1950 and the type entered service with the Czechoslovakian Air Force in May 1951. The wings are swept and the 5,000lb thrust Rolls-Royce Nene III is fed from a nose intake and a single tail exhaust is fitted.
Wingspan: 12.50m
Length: 12m
Height: 3.70m
Empty weight: 2,214kg
Take-off weight: 5,760kg
Engine: 1x 5,000lb Rolls-Royce RB.41 Nene III
Maximum speed: 920km / h
Cruising speed: 760km / h
Landing speed: 160km / h
Service ceiling: 11,500m
Range: 1,000km
Armament: 2x 23mm GAST cannon plus 24x 55mm or 2x 210mm rocket projectiles or 2x 250kg bombs on two underwing hardpoints.
CŠ-52, a two-seat conversion trainer version of the Š-52 fighter. It retains all the same features but features a new tandem cockpit with full dual controls. The prototypes first flew on 2 March 1950 and the type entered service with the Czechoslovakian Air Force in April 1951.
Wingspan: 12.50m
Length: 12m
Height: 3.70m
Empty weight: 2,254kg
Take-off weight: 5,760kg
Engine: 1x 5,000lb Rolls-Royce RB.41 Nene III
Maximum speed: 920km / h
Cruising speed: 760km / h
Landing speed: 160km / h
Service ceiling: 11,500m
Range: 750km
Armament: 1x 23mm GAST cannon plus 24x 55mm or 2x 210mm rocket projectiles or 2x 250kg bombs on two underwing hardpoints.
Škoda (Škoda Vojenska Tovarna Na Letadla)
Head Office and Works: Kunovice
The Škoda Works industrial concern in 1928 brought a share of Avia but later sold its holding to Fokker in 1931. Skoda then set about planning for its own aircraft division. Construction of the aircraft factory in Kunovice started in 1936 and was completed during 1938.
Current Types:
Škoda SK-3, a single-seat light aircraft with enclosed cockpit and fixed undercarriage and stubby fuselage. Only the prototype was flown, abandoned in 1939.
Škoda SK-4, a single-seat fighter-trainer with a low-wing monoplane and retractable undercarriage. Four prototypes were flown from 1940 to 1942 with different engines. The chosen production variant was powered by a 485hp Argus As 410 engine and production for the Czech Air Force began in September 1942.
Length: 7.1 m (23 ft 4 in)
Wingspan: 7.6 m (24 ft 11 in)
Wing area: 8.4 m2 (90 sq ft)
Powerplant: one 485hp Argus As 410 12-cylinder air-cooled inverted-V engine
Maximum speed: 350 km/h (220 mph)
Range: 930 km (578 miles)
Service ceiling: 7,500 m (24,606 ft)
Škoda SK-8, a two-seat light cabin low-wing monoplane light aircraft with side-by-side seating and fixed undercarriage. The leading edge of the wing is swept and a first flight was undertaken on 16 January 1942 with production starting in February 1943.
Length: 6 m
Wingspan: 7.95m
Powerplant: one 105hp Walter Minor 4-111
Škoda SK-5, a single-seat single-engined fighter with a low-wing monoplane wing and conventional layout and appearance. The wing will have novel tubular-spar construction. The first flight is planned for July 1942 with entry into Czech service during 1944.
Length: 10 m
Wingspan: 12.20 m
Powerplant: one 1,600hp Avia-built Hispano-Suiza HS12Z
Maximum speed: 690 km/h (430 mph)
Armament: four wing-mounted 20 mm Orkileon MG FF cannon
Zlin Aircraft
Head Office and Works: Otrokovice Airfield, Otrokovice
The company was founded in 1934 and has specialised in gliders as both trainers and for sports purposes, but has since 1943 entered the light aircraft market. A small workshop on the site has begun manufacturing a series of light engines.
Zlin 22 Junak, a two-seat trainer with side-by-side seating. It is a low-wing cantilever monoplane with a conventional tailwheel landing gear powered by a 75hp Praga D engine, although the prototype had a 57hp Zlin Persy III engine. The prototype first flew during 1944. A three-seat variant, the Zlin 22M was developed during 1946 powered by a 105hp Walter Minor 4-III, and two prototypes of a three/four seat tourer variant, the Zlin 122, were built during 1947. Each were powered by the 105hp Zlin Toma 4 engine.
Length: 7.25 m (23 ft 9½ in)
Wingspan: 10.60 m (34 ft 9 in)
Height: 1.96 m (6 ft 5 in)
Wing area: 14.65 m2 (157.7 ft2)
Powerplant: one 75hp Praga D engine
Maximum speed: 180 km/h (112 mph)
Cruising speed: 160 km/h (99 mph)
Range: 650 km (400 miles)
Service ceiling: 4,500 m (14,700 ft)
Rate of climb: 3.0 m/s (590 ft/min)
Zlin Z-28
A two-seat twin-engined training aircraft. The fuselage is based on that of the Z22 but with new wings with two 105hp Walter Minor 4-III engines. The prototype first flew on 19 September 1947 and production began in late 1948.
Length: 7.25 m (23 ft 9½ in)
Wingspan: 12.25 m (40 ft 2 in)
Powerplant: two 105hp Walter Minor-III 4-cylinder inlines
Maximum speed: 265 km/h (165 mph)
Range: 1,000 km (620 miles)
Service ceiling: 4,400 m (14,400 ft)
Tuesday, April 16th 2024, 10:26pm
Go to the top of the page
Quoted 
