Postwar Dorand Projects

hesham

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Hi everybody,

Dorand project of 1954 for STOL mailplane.
 

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Hi all,

In Docavia 23 I have found little infos about the Dorand DA.08 and DA.09, both light airplane projects from ca. 1957. I know Dorand only as inventor for helicopters? Do you have more informations...

Servus Maveric
 
hesham said:
Hi everybody,

Dorand project of 1954 for STOL mailplane.

It wasn't so much STOL as VTOL! See: http://modelarchives.free.fr/Bestiaire/DVTOL_P/index.html
 
In Aero France, January 1956 issue, I found an article with the title " L'Avion A Ailes Propulsives Et A Gouvernes
Par Controle De La Couche Limite", including a 3-view.
I've attached the text, too, maybe a native French speaker could give a short summary ?
I think, the 3-view shows the DA 8, obviously an 8-seater, but mentioned, too, is the DH G 4,
an experimantal two-seater, which seems to have been build.
 

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The goal is to produce small, low-power transport aircraft: max 750 hp, moderate commercial speed 350 km/h, capable of flying at low speed: 50 km/h, of taking off without assistance from small and bad strips.


Fuel use per kg of thrust is: stopped 0.37 kg/kg/h , at 385km/h 0.7 kg/kg/h.


Here are the reasons which lead René Dorand to use low pressure fluid:
The feeding of propulsive wings by medium-pressure fluid (ratio 1.5 to 1.7) is interesting for planes with a slim profile, for which the cruise speed is around 700 km/h, with a minimum speed of 90 km/h.


The comparison with classical airplanes enables the following observations:
- for the same performance, the rolling length is divided by 4
- in the same flying conditions, horizontal speed is increased by 30%


As an example, the performance of a twin-seater trainer Fouga Magister fitted with medium-pressure propulsive wings would be as follows:
(table)
The experimental twin-seater Dorand DH G4 is considered with a Turbomeca Soulor powerplant.


With a feed by low-pressure fluid (preferably mixed fluid, pressure ratio 1.06 to 1.15), the minimum speed is divided by 2, the rolling length divided by 5.
 
Nice find my dear Boxkite,

and from TU magazine.
 

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In Docavia 23 I have found little infos about the Dorand DA.08 and DA.09, both light airplane projects from ca. 1957. I know Dorand only as inventor for helicopters? Do you have more informations...
From TU magazine,

there was also DA.01,DA.3,DA.5 & DA.06,and for DA.8 and
DA.9.
 

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there was also DA.01,DA.3
From TU magazine;

DA.01,

Two-seater with a total weight of 2,200 kg at a maximum speed of
260 km / h for a 650 km radius of action.
Equipped with a TURBOMECA TURMO II powertrain.

DA.03,

Aircraft whose characteristics and performances were as follows:
Wingspan: 8.30 meters,
Length: 10 meters,
Wing length: 3.75 meters,
Rope for attaching to the fuselage: 1.50 meters,
End rope: 0.75 meter,
Wing area (excluding fuselage): 8.50 m2,
Thruster: 2 ARTOUSTE III turbo-compressor units (the hot fluid is used to
1s propulsion, the cold fluid circulating in the lifting surface and
the horizontal tail feeds the fluid flaps),
Empty weight: 1.042 Kg,
Payload: 906 Kg including 500 Kg of fuel.
Performance compared with a conventional aircraft of the same total weight, even thruster were as follows:
 

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