Force and flight tests were performance on an all-wing model with windmilling propellers. Tests were conducted with deflected and retracted flaps, with and without auxiliary vertical tail surfaces, and with different centers of gravity and trim coefficients. Results indicate serious reduction of stick-fixed longitudinal stability because of wing-tip stalling at high lift coefficient. Directional stability without vertical tail is undesirably low. Low effective dihedral should be maintained. Elevator and rudder control system is satisfactory.
Determination of the Stability and Control Characteristics of a Tailless All-Wing Airplane Model with Sweepback in the Langley Free-Flight Tunnel
1945-02-01
Sonstige
Keine Angabe
Englisch
Engineering Index Backfile | 1945
|Engineering Index Backfile | 1946
|Flight tests of airplane model with 62° swept-back wing in Langley free-flight tunnel
Engineering Index Backfile | 1947
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