| Akaflieg Berlin | |
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HW100 - 45000
UAW55 - 105000 RRW100 - 175000 PKRR - 7500 |
Akaflieg Berlin Skyports Company type - Non-profit Genre - Aviation research Founded - 1920 Headquarters - Technische Hochschule, Germany Website - akaflieg-berlin.de Akaflieg Berlin is one of around thirteen flying groups, or Akaflieg, currently attached to German universities. Akaflieg Berlin, is the abbreviation of Akademische Fliegergruppe Berlin e.V. (Academic Aviator Group Berlin), a group of students enrolled at several Berlin universities, though they are mainly from TU Berlin, who are involved with the development and the design of gliders, as well as research in aerodynamics. Founded in 1920 Akaflieg Berlin is one of the oldest gliding clubs in Germany, flying their gliders from Kammermark airfield near Pritzwalk, which they share with the AFV Berlin (Akademische Fliegervereinigung Berlin e.V.), which mainly consists of former members of Akaflieg Berlin, jokingly referred to as the “elderly ladies and gentlemen”. As at 2007/2008 Akaflieg Berlin was the executive group of the Idaflieg (Interessengemeinschaft deutscher akademischer Fliegergruppen e.V.), the controlling body for all German university flying groups. Akaflieg Berlin currently has three two-seaters: a Grob G-103 Twin III and two of its own designs, the Akaflieg Berlin B12 and the Akaflieg Berlin B13. It further operates a Schempp-Hirth Discus and a Schleicher ASW 24. Akaflieg Berlin has undertaken the following development projects: Akaflieg Berlin B1 Charlotte 1922, single-seat glider, tailless, shoulder-wing, two skids, all-wood. Akaflieg Berlin B2 Teufelchen 1923, single-seat glider, cantilever shoulder-wing, all-wood. Akaflieg Berlin B3 Charlotte II 1923, single-seat glider, air brakes, one skid, otherwise like B1. Akaflieg Berlin B4 F.F. 1931, single-seat engined aeroplane, 20 HP, high-wing, all wood body, cloth covered retractable wings. Akaflieg Berlin B5 1937, single-seat performance glider, cantilevered gull-wings, retractable landing-gear, all-moving-tail, dive air-brakes, all-wood. Akaflieg Berlin B6 1938, single-seat performance glider, cantilevered mid-wing aeroplane with Junkers-flaps, retractable landing gear, all moving tail, dive air brakes, wood and steel body. Akaflieg Berlin B7 This 1939 project was a two-seater performance glider, planned, but not built. Akaflieg Berlin B8 Designed and built in 1939 for the Olympic games glider competition in Rome, this single-seat performance glider, was built to meet the specifications of the Olympia tender (the competition to design a glider for the 1940 Olympic Games). With cantilever shoulder-wing, dive air-brakes and all wood construction, the B8 was constructed in 2 versions with variations in dihedral. The Olympic competition was ultimately won by the DFS Meise. Akaflieg Berlin B9 Designed in 1943, the B9 was a two-seater twin-engined experimental aeroplane for high-g-flights, with a cantilever low-wing, retractable landing gear and 2 x 105 HP engines. The B9 was intended to research the effects of high-g flight with the pilot lying in a prone position, being assigned the RLM designation 8-341. Akaflieg Berlin B10 Conceived in 1944, this two-seated twin-engined amphibian didn't pass the design stage. Akaflieg Berlin B11 Designed in 1963, the B11 was a single-seat tail less performance glider with negative wing-sweep. Construction of the prototype was not completed due to faulty design. Akaflieg Berlin B12 The B 12 is a two-seated epoxy-glass-resin performance glider with the seats in tandem. The main aim of the project was the optimisation of the aerodynamics of the fuselage at high speeds. The B12 has flaps and a retractable landing-gear and is still used by the group for performance flights and contests. The maiden flight was in 1977 at Ehlershausen near Hannover and the measured glide-ratio (Idaflieg-summer-meeting 1978) is 40.5. Akaflieg Berlin B13 The B13 is a two-seater epoxy-carbon-resin electric motor glider with the seats positioned side-by-side. The wing span is 23.2 m and the measured glide-ratio (Idaflieg-summer-meeting 1992) is 46.5. The wing profile is a modified flap-HQ-41-profile. Developed in the eighties, the B13 had its successful maiden flight in 1991 at Strausberg near Berlin. After the integration of the 33hp (24.5kW) Rotax engine, an innovative brushless linear induction motor was substituted, powered by energy from renewable sources using fuel cells and solar technology. Glider launch winch Because of the high take-off weight of the B13, the group decided in 1984 to design and construct a new more powerful winch to launch their gliders. Daimler-Benz donated a 320 HP 10-cylinder diesel engine including an axle and cable drums. In addition to achieving a higher performance, the project's aim was to make winch launching safer for modern gliders which have higher minimum speeds during a winch launch, especially on days when there is no wind or even a light tail-wind. By using big azimuth rollers and inclined inlet guides, the winch is designed to minimize the bending of the cable under load. The groups also designed automatic process controls for the pneumatically driven gearbox actuators;mounted on an all-wheel drive Tatra 148 chassis, the winch was finished in 1994 and has operated with Dyneema-plastics cables since 2004. B9 (Model) B12 B13 Glider launch winch of the Akaflieg Berlin Akaflieg Berlin B1 B1 Charlotte Role - Sailplane National origin - Germany Manufacturer - Akaflieg Berlin First flight - 1922 Number built - 1 The Akaflieg Berlin B1 Charlotte (named after the university at Charlottenburg), was a glider built in Germany in the 1920s. It featured a high-wing, tailless sailplane configuration of all-wood construction, which had a pair of skids for landing. Design and development Hermann Winter and Edmund Pfister shared the design work for the "Charlotte", hoping to compete at the 2nd Rhön competition at the Wasserkuppe. Progress was slow as Pfister had a full-time job to fulfill. Professor Winter was determined to compete at the next Rhön meeting, so he engaged the Sablatnig Works for completion of the glider, which went on to win at the Wasserkuppe in August 1922. Specifications (B1) Data from 75 Jahre 10 NI AKAFLIEG BERLIN 1920-1995 General characteristics Crew: 1 Length: 4.5 m (14 ft 9 in) Wingspan: 15.2 m (49 ft 10 in) Wing area: 20 m2 (220 sq ft) Aspect ratio: 11.1 Empty weight: 100 kg (220 lb) Gross weight: 170 kg (375 lb) Performance Wing loading: 8.5 kg/m2 (1.7 lb/sq ft) Charlotte at the Rhön competition in 1922 Akaflieg Berlin B2 Teufelchen (Akaflieg Berlin B2) B2 Teufelchen Role - Glider National origin - Germany Designer - Kurt Tank First flight - 1922 Number built - 1 The Akaflieg Berlin B2 Teufelchen was a glider built in Germany in the 1920s. It featured a high-wing, cantilever sailplane configuration of all-wood construction. Design and development Kurt Tank studied electrical engineering, but he also tried his hand at a home-built glider, nicknamed Teufelchen (en:Little devil). Anxious to compete at the Rossitten coastal gliding competition in 1923 Tank had the LFG-Stralsund works complete the glider in time for the competition; transporting the aircraft by horse-drawn cart. The 'B2' was characterized by warping wing-tips, in the hope of dispensing with ailerons. Construction was mixed with wooden structure covered with aluminium sheeting, which earned the Teufelchen a prize for best construction. After Tank crashed the B2 it was returned to Berlin and repaired at the Sablatnig works where it had been built. The B2 next attended the 4th Rhön meeting in August 1923, where Tank had a hard landing. The 2nd Rossitten coastal meeting saw many of the competitors flying over the dunes and sea, including the B2, which Möller was forced to land in and the B2 sank. Specifications (B2) (Data from 75 Jahre AKAFLIEG BERLIN 1920-1995) General characteristics Length: 5 m (16 ft 5 in) Wingspan: 11.5 m (37 ft 9 in) Wing area: 13.7 m2 (147 sq ft) Empty weight: 106 kg (234 lb) Gross weight: 176 kg (388 lb) Performance Maximum glide ratio: 9.6 Wing loading: 12.8 kg/m2 (2.6 lb/sq ft) Teufelchen at the 1923 Rossiten coastal gliding competition Akaflieg Berlin B3 Charlotte II (Akaflieg Berlin B3) B3 Charlotte II Role - Sailplane National origin - Germany Manufacturer - Akaflieg Berlin First flight - 1923 Number built - 1 The Akaflieg Berlin B3 Charlotte II was a glider built in Germany in the 1920s. It featured a high-wing, tailless sailplane configuration of all-wood construction, which had a single skid for landing and applied brakes. Specifications (Data from 75 Jahre 10 NI AKAFLIEG BERLIN 1920-1995) General characteristics Length: 4.1 m (13 ft 5 in) Wingspan: 14.2 m (46 ft 7 in) Height: 1.5 m (4 ft 11 in) Wing area: 19.5 m2 (210 sq ft) Aspect ratio: 10.3 Empty weight: 133 kg (293 lb) Gross weight: 195 kg (430 lb) Performance Wing loading: 10 kg/m2 (2.0 lb/sq ft) 2-view profile Akaflieg Berlin B4 F.F. (Akaflieg Berlin B4) B4 F.F. Role - Light aircraft National origin - Germany Manufacturer - Akaflieg Berlin Designer - Walter Stender, dr. Martin Schrenk and Gerald Klein First flight - December 1931 Number built - 1 The Akaflieg Berlin B4 F.F. was a single-seat aircraft built in Germany in the early 1930s. It was a high-wing monoplane of all-wood construction with fabric-covered foldable wings. Design and development In 1931 the Deutsche Luftfahrt-Verband e.V. (DLV) opened a competition for an inexpensive light aircraft. Two entries were put forward; Akaflieg Berlin's B4 F.F. (D-2229) and Dipl.-Ing. Hermann Mayer's MM-1 (D-2230), with both aircraft exhibited at the 1932 Deutschen Luftsport-Ausstellung (DELA) in Berlin. Like the Mayer MM-1 the B4 F.F. was constructed at the DLV workshops in Adlershof. Design took eight months and construction a further nine. Specifications (B4 F.F.) General characteristics Length: 5.7 m (18 ft 8 in) Wingspan: 9 m (29 ft 6 in) Height: 2.4 m (7 ft 10 in) Wing area: 10 m2 (110 sq ft) Aspect ratio: 8 Empty weight: 185 kg (408 lb) Gross weight: 285 kg (628 lb) Powerplant: 1 × Daimler F7502 , 15 kW (20 hp) Propellers: 2-bladed fixed-pitch propeller Performance Maximum speed: 125 km/h (78 mph, 67 kn) Service ceiling: 3,500 m (11,500 ft) g limits: +8 (ultimate load factor) Wing loading: 28.5 kg/m2 (5.8 lb/sq ft) Power/mass: 19.18 kg/kW (31.53 lb/hp) The B4 over Johannisthal Akaflieg Berlin B5 B5 Role - Sailplane National origin - Germany Manufacturer - Akaflieg Berlin First flight - 1937 Number built - 1 The Akaflieg Berlin B5 was a glider built in Germany in the late 1930s. It featured a high-wing, cantilever sailplane configuration of all-wood construction, with cantilevered gull-wings, retractable landing-gear, all-moving-tail, dive air-brakes. Specifications (B5) (Data from, Flugzeug-Typenbuch. Handbuch der deutschen Luftfahrt- und Zubehör-Industrie 1944) General characteristics Crew: 1 Length: 6.15 m (20 ft 2 in) Wingspan: 15 m (49 ft 3 in) Height: 1.24 m (4 ft 1 in) Wing area: 11 m2 (120 sq ft) Length de-rigged: 7.28 m (24 ft) Width de-rigged (without tailplane): 1 m (3 ft 3 in) Width de-rigged (with tailplane): 2.5 m (8 ft 2 in) Height de-rigged: 1.24 m (4 ft 1 in) Aspect ratio: 20.45 Airfoil: root Göttingen 549; mid span Göttingen 497; tip Göttingen 497 Empty weight: 140 kg (309 lb) Gross weight: 225 kg (496 lb) Performance Never exceed speed: 228 km/h (142 mph, 123 kn) Aerotow speed: 120 km/h (75 mph; 65 kn) g limits: +8 (ultimate) Maximum glide ratio: 30.5:1 at 76 km/h (47 mph; 41 kn) Rate of sink: 0.67 m/s (132 ft/min) at 64 km/h (40 mph; 35 kn) Wing loading: 20.45 kg/m2 (4.19 lb/sq ft) Akaflieg Berlin B6 B6 Role - Sailplane National origin - Germany Manufacturer - Akaflieg Berlin First flight - 1938 Number built - 1 The Akaflieg Berlin B6 was a glider built in Germany in the late 1930s. It featured a high-wing, cantilevered mid-wing sailplane configuration with Junkers-flaps, retractable landing gear, all moving tail, dive air brakes, wood and steel body. Specifications (B6) (Data from 75 Jahre 10 NI AKAFLIEG BERLIN 1920-1995, Flugzeug-Typenbuch. Handbuch der deutschen Luftfahrt- und Zubehör-Industrie 1944) General characteristics Crew: 1 Length: 6.2 m (20 ft 4 in) Wingspan: 16 m (52 ft 6 in) Height: 1.25 m (4 ft 1 in) Wing area: 14.6 m2 (157 sq ft) Length de-rigged: 7.7 m (25 ft) Width de-rigged (without tailplane): 1 m (3 ft 3 in) Width de-rigged (with tailplane): 2.8 m (9 ft 2 in) Height de-rigged: 1.25 m (4 ft 1 in) Aspect ratio: 17.53 Airfoil: NACA 43012 Empty weight: 155 kg (342 lb) Gross weight: 240 kg (529 lb) Performance Never exceed speed: 225 km/h (140 mph, 121 kn) Maximum glide ratio: 30:1 at 68 km/h (42 mph; 37 kn) Rate of sink: 0.58 m/s (114 ft/min) at 54 km/h (34 mph; 29 kn) Wing loading: 16.42 kg/m2 (3.36 lb/sq ft) Akaflieg Berlin B8 B8 V2 Role - Sailplane National origin - Germany Manufacturer - Akaflieg Berlin First flight - 1939 Number built - 2 The Akaflieg Berlin B8 was a German sailplane built in the late 1930s for the 1939 Olympic games glider competition in Rome. It was a high-wing sailplane with a cantilever shoulder-wing, dive air-brakes and all wood construction. Specifications (variant specified) (Data from, Flugzeug-Typenbuch. Handbuch der deutschen Luftfahrt- und Zubehör-Industrie 1944) General characteristics Crew: 1 Length: 7.1 m (23 ft 4 in) Wingspan: 15 m (49 ft 3 in) Height: 1.5 m (4 ft 11 in) Wing area: 15.6 m2 (168 sq ft) Length de-rigged: 7.1 m (23 ft) Width de-rigged (without tailplane): 0.65 m (2 ft 2 in) Width de-rigged (with tailplane): 3 m (10 ft) Height de-rigged: 1.5 m (4 ft 11 in) Aspect ratio: 14.41 Airfoil - root: Göttingen 549; mid-span: Göttingen 535; tip: Göttingen 535; tail unit: NACA 0012 Empty weight: 165 kg (364 lb) Gross weight: 260 kg (573 lb) Performance Maximum glide ratio: 23:1 at 68 km/h (42 mph; 37 kn) Rate of sink: 0.7 m/s (140 ft/min) at 56 km/h (35 mph; 30 kn) Wing loading: 16.65 kg/m2 (3.41 lb/sq ft) Akaflieg Berlin B9 Akaflieg Berlin B9 Role - Experimental aircraft National origin - Germany Manufacturer - Akaflieg Berlin First flight - 1943 Status - Prototype only Number built - 1 The Akaflieg Berlin B9 was a twin-engined experimental aircraft, developed by Akaflieg Berlin and Flugtechnische Fachgruppe in the 1940s. It was designed to examine the benefits of having a pilot in a prone position. The aircraft was flown in 1943, but was eventually abandoned. Specifications (Data from FFG-Berlin B9) General characteristics Crew: One Length: 6.06 m (19 ft 11 in) Wingspan: 9.4 m (30 ft 10 in) Height: 2.32 m (7 ft 7 in) Wing area: 11.9 m2 (128 sq ft) Empty weight: 940 kg (2,072 lb) Gross weight: 1,115 kg (2,458 lb) Fuel capacity: 95L Powerplant: 2 × Hirth HM 500 4-cylinder air-cooled inverted in-line piston engine, 77 kW (103 hp)105PS each Performance Maximum speed: 250 km/h (160 mph, 130 kn) Service ceiling: 4,000 m (13,000 ft) Aircraft of comparable role, configuration, and era Gloster Meteor F8 "Prone Pilot" Henschel Hs 132 Ikarus 451 Reid and Sigrist R.S.3 Akaflieg Berlin B12 Akaflieg Berlin B12 Role - Two place glider aircraft National origin - Germany Manufacturer - Akaflieg Berlin First flight - B12:27 July 1977; B12T:11 August 1987 Primary user - Akaflieg Berlin Number built - 1 The Akaflieg Berlin B12 is a high performance two-place glider aircraft that was designed and built in Germany. Conceived as a research vehicle, only one unit was constructed. Development The students at Akaflieg Berlin set out to improve the performance of modern gliders by reducing drag. To improve a modern glider's performance through modifying the aerofoil sections is time-consuming and very costly, so to reduce costs the group utilised production wings from a Schempp-Hirth Janus B, shortened to 18.2m (59.71 feet), allowing the students to concentrate their efforts and budget on improving the fuselage. The shape and profiles of the new fuselage were developed at the Institut für Luftfahrzeugbau (Institute for aircraft industry) and a new two-seat fuselage was constructed using contemporary GFRP (Glass-fibre Re-inforced Plastic) techniques in a monocoque shell. Construction Built principally from GFRP the B12 uses monocoque construction, avoiding the use of a welded steel-tube core structure, maximising the volume available for crew accommodation and payloads such as research instrumentation. The cockpit seats two in tandem under large plexiglas canopies with the instructor seat, in the rear, set at a higher level to improve his forward view. The wings are standard 'Janus B' items built using identical construction methods. The empennage originally utilised a cruciform tail using an NACA 0009-64 aerofoil section formed with 'Rohacell'/GFRP sandwich supported by CFRP (Carbon-Fibre Re-inforced Plastic) spars. After a trailer accident during road transport in 1986, which destroyed the rear fuselage and tail-unit, a T-tail was fitted during repairs. A thicker aerofoil section was used for the vertical tail of this revised unit, a specially developed Wortmann FX-71 L 150/30 profile. The single retractable main undercarriage wheel is supported on a tall leg assembly which was originally built with electric actuation, but after a field landing with a flat battery caused a wheels-up landing a manual system was fitted. A rubber tail skid, capped with hardened steel, under the rear fuselage completes the undercarriage. In the original fuselage a braking parachute, used for approach control, was housed at the extreme rear, but this feature was not carried through to the replacement tailcone during its rebuild. History After the first flight of the B12 on 27 July 1977, piloted by Jürgen Ehlers Thorbeck, the B12 was used for research, cross country and competition flying until a trailer accident in 1986, whilst being transported by road, destroyed the tail section and twisted the rear fuselage. Repairs were carried out and the B12 was flying again on 1 August 1987 at the IDAFLIEG ( Interessengemeinschaft deutscher akademischer Fliegergruppen e.V. - interest group for academic flying groups) summer camp at Aalen-Elchingen, sporting a T-tail identical to that of the Akaflieg Berlin B13. The B12 continues to fly but rarely emerges from the hangar unless the soaring weather is good. Flying Flying the B12 requires a certain amount of care, due to: - high nose-up seating position - tall undercarriage, which reduces forward view at low ground roll speeds - high-mounted wings with significant dihedral, which makes ground-handling awkward - the ailerons are relatively ineffective - control pressures are large, causing pilot fatigue - rigging and de-rigging of the aircraft are complicated and strenuous, requiring several ground-handlers - high weight causes high wing loading, reducing thermalling performance (i.e. rate of climb) Once the quirks and foibles of the B12 are understood it is possible to compete effectively with other contemporary two-seaters. However the expected performance gains were only partly realised and the B12 does not rank with the highest performance gliders, as was hoped. One quirk is the B12 'sigh' which can be heard in certain flight conditions, the origin of which remains a mystery. Competition flying is carried out with the call-sign CB and a handicap index of 106 is applied. The aircraft carries registration 'D-7612'. Variants B12 The original aircraft built with a cruciform style tail unit using a NACA 0009-64 aerofoil section. B12T Designation of the aircraft once re-built, after a trailer accident, with a t-tail using a specially developed Wortmann FX-71 L 150/30 aerofoil section. Specifications (B12T) (Data from Jane's All the World's Aircraft 1988-89) General characteristics Crew: 2 Length: 8.865 m (29 ft 1 in) Wingspan: 18.2 m (59 ft 9 in) Height: 1.65 m (5 ft 5 in) Wing area: 16.58 m2 (178.5 sq ft) Airfoil: root:Wortmann FX-67-K-170; tip:Wortmann FX-67-K-150 Empty weight: 438.5 kg (967 lb) Max takeoff weight: 620 kg (1,367 lb) Performance Stall speed: 72 km/h (45 mph, 39 kn) Never exceed speed: 250 km/h (160 mph, 130 kn) in smooth air 180 km/h (97 kn; 110 mph) in rough air 150 km/h (81 kn; 93 mph) on aero-tow 130 km/h (70 kn; 81 mph) on winch launch g limits: +6 -4 Maximum glide ratio: 40.5 at 110 km/h (59 kn; 68 mph) Rate of sink: 0.68 m/s (134 ft/min) at 90 km/h (49 kn; 56 mph) Wing loading: 37.39 kg/m2 (7.66 lb/sq ft) at max t/o weight General characteristics Crew: 2 Length: 8.7 m (28 ft 7 in) Wingspan: 18.2 m (59 ft 9 in) Wing area: 16.58 m2 (178.5 sq ft) Aspect ratio: 20.0 Empty weight: 446 kg (983 lb) Gross weight: 620 kg (1,367 lb) Performance Maximum speed: 200 km/h (124 mph, 108 kn) Maximum glide ratio: 40.5 at 110 km/h (59 kn; 68 mph) Rate of sink: 0.68 m/s (134 ft/min) at 90 km/h (49 kn; 56 mph) Related development Schempp-Hirth Janus B Aircraft of comparable role, configuration, and era Akaflieg Braunschweig SB-10 Schirokko The B12T rolling for a winch launch Akaflieg Berlin B13 Akaflieg Berlin B13 Role - High Performance Two-Seat Glider (with sustainer) National origin - Germany Manufacturer - Akaflieg Berlin First flight - 1991 Primary user - Akaflieg Berlin Number built - 1 The Akaflieg Berlin B13 is a two-seat motor-glider designed and built in Germany. Development Students at Akaflieg Berlin studied a high-performance motor-glider with the engine in the nose and an automatically folding propeller. After approval was given, a prototype was built in 1991, as the ' Akaflieg Berlin B13', using GFRP (glass-fibre re-inforced plastic) to form a fuselage with smooth lines, housing the engine in the nose and a two-seat side-by-side cockpit covered by a large plexiglas canopy. Intended to use a sustainer motor, for sustaining flight only, power was to be supplied by a modified 24.5KW (33 hp) engine in the extreme nose driving a 5-blade folding retractable propeller, specially developed by Prof. Oehler. However, problems with the integration of the engine with the fuselage have prevented the fitting of the engine, resulting in the 'B13' being restricted to un-powered flight only. Specifications (B13 power off) (Data from Jane's All the World's Aircraft 1988-89, sailplanedirectory.com) General characteristics Crew: 2 Length: 8.3 m (27 ft 3 in) Wingspan: 23.2 m (76 ft 1 in) Height: 1.9 m (6 ft 3 in) Wing area: 18.9 m2 (203 sq ft) Aspect ratio: 28.5 Airfoil: HQ 41/ 14,35 Empty weight: 590 kg (1,301 lb) Max takeoff weight: 850 kg (1,874 lb) Fuel capacity: 25 L (6.6 US gal; 5.5 imp gal) Water Ballast: 160 L (42 US gal; 35 imp gal) Powerplant: 1 × Rotax 377 2-cyl. horizontally-opposed air-cooled piston engine, 24 kW (32 hp) Propellers: 5-bladed Oehler folding propeller Performance Stall speed: 70 km/h (43 mph, 38 kn) Never exceed speed: 280 km/h (170 mph, 150 kn) in smooth air 200 km/h (110 kn; 120 mph) in rough air 75 km/h (40 kn; 47 mph) on aero-tow 120 km/h (65 kn; 75 mph) on winch launch g limits: +5.3 - 2.65 Maximum glide ratio: 49 at 105 km/h (57 kn; 65 mph) Rate of sink: 0.55 m/s (108 ft/min) at 75 km/h (40 kn; 47 mph) Wing loading: 42.2 kg/m2 (8.6 lb/sq ft) at max t/o weight Power/mass: 0.0376 kW/kg (0.0229 hp/lb) Aircraft of comparable role, configuration, and era Stemme S-10 Caproni Vizzola Calif |