An aerodynamically balanced aircraft configuration is discussed. The design reduces the effects of large nose-down pitching moments generated by the flap high-lift forces, the loss of trim lift during high-lift flight, and the yawing moments caused by the loss of an engine without the use of large horizontal and vertical tails. Drawings of the proposed configuration are provided. Detailed descriptions of the airframe and control surfaces are included.
High Lift Aircraft
1973
15 pages
Report
Keine Angabe
Englisch
Europäisches Patentamt | 2018
|Europäisches Patentamt | 2017
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