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Type2 + 8 seat airlinera 2 + 8 seat airlinerb
Engine1 BMW VID   
DimensionsLength 14.8 m, height 4.00 m, span 20.0 m, wing area 62.5 m2
WeightsEmpty 2850 kg, flying weight 4500 kg   
PerformanceMax. speed 200 km/h, cruising speed 176 km/h, landing speed 92 km/h, range 800 km, service ceiling 4700 m, required runway for take off 480 m 
Focke-Wulf A 29 "Möwe".
The Focke-Wulf "Möwe" type A 17a with Siemens-Jupiter geared engine is used in German and international air traffic by Deutsche Lufthansa A.-G. has become a well-known
phenomenon. Its excellent route probation, according to Lufthansa's certificate, mainly on long foreign routes (e.g. Berlin-Zurich, Berlin-Paris
) and its good bad-weather flight characteristics, quickly made it popular with guides and passengers. However, the Focke-Wulf "Möwe" is almost unique in
its high operating efficiency due to its good aerodynamic properties and the simple design, which results in a moderate purchase price with low
maintenance and repair costs.
Although the last aircraft of the 10 units of the series was delivered to Lufthansa in 1928 not quite a year earlier, the Focke-Wulf "Seagulls" had
already covered over a million km in August 1929.
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So it is easy to understand that it was precisely in view of the urgent need for the most economical work today that Lufthansa wanted to put
more "seagulls" into service, and that Focke-Wulf Flugzeugbau A.-G. received an order for 4 more machines.
This time the version with B. M. W. VI engines was desired, and the resulting model was given the designation: A 29 "Möwe".
With the heavy, water-cooled engine, the cooling system and its water content, as well as the numerous existing and newly added wishes of practical
air traffic, a considerable increase in weight compared to the A17 a was unavoidable, unless something of the solid design was sacrificed should. The first experts doubted that with the resulting flight weight of 4300 kg instead of 4000 kg (assuming the same payload) a sufficient take-off power would be achieved. However, the forecasts of Focke-Wulf have not only been fulfilled, but have been far exceeded, because the A29 "Möwe" has a slightly better take-off performance (480 m for a height of 20 m) than the A17a (485 m for a height of 20 m), and that at a flying weight of 4400 kg. The same applies to the
climbing performance, which has been improved from 6.4 min. to 5.7 min. for 1000 m, also with 4400 kg. So the payload could be increased from 1550 kg to 1690 kg (see below). This was achieved with B. M. W. VI engine (1:5.5) without gearbox. For comparison purposes, an engine with a gearbox is installed in one of the aircraft, which
naturally improves performance even further.
On the outside, the A29 differs from the A17a at first glance only in the engine installation with forehead cooler. However, some details have been perfected, partly in close cooperation with Lufthansa. For example, the windshield arrangement of the driver's cab was changed in order to further improve visibility without neglecting aerodynamic considerations. The keel fin was made adjustable at the bottom and the elevator fin adjustment was changed in design. In addition, at Lufthansa's request, the chassis was fitted with ball joints everywhere instead of the previous cardan pieces. You can hiexpect a reduction in the cost of bolt wear. Finally, the outline shape of the horizontal stabilizer was changed in systematic tests in order to achieve the strongest possible rudder effect during landing.
An interesting variation of the A 29 and the A 17 a was ordered by the German Aviation Research Institute. This sample, called "A26", is intended for tests with
different air- and water-cooled engines in the same cell and accordingly has interchangeable engine stems that can be exchanged together with the fully
installed engines. By measuring the flight performance, the influence of the engine power and speeds of the propeller, including the shape of the front part of the fuselage caused by the engine itself, possibly the radiator flow, etc., can be determined.
The cabin equipment has been omitted and the space thus available is used to accommodate the instruments and observers in order to study the operating conditions of the engines in flight.
Dimensions and weights: wing area 62.5 m2, wingspan 20 m; length over all 14.8 m, maximum height 4 m, set-up weight 2710 kg, payload: 2 drivers 160 kg, fuel for 5 hours 500 kg, oil 50 kg, 8 passengers 640 kg, luggage and cargo 340 kg, together 1690 kg, flight weight 4400 kg.
Performance with 4400 kg according to measurements of the D. V. L. or D. L. H.: Maximum speed 198 km/h, cruising speed at 12 percent throttling 176 km/h,
landing speed 92 km/h, climb times for 1000 m 5.7 min., 2000 m 12.6 min., 3000 m 21.7 min., 4000 m 36.2 min., 4500 m 48.8 min. Climb rate in air density 1.1 kg/m3 2.6 m/sec., Summit altitude (climbing speed = 0) 4700 m, service maximum altitude (climbing speed = 0.5 m/sec) 4500 m, instead of: reaching a height