Flight Investigation of Stall, Spin and Recovery Characteristics of a Low-Wing, Single-Engine, T-Tail Light Airplane

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Flight Investigation of Stall, Spin and Recovery Characteristics of a Low-Wing, Single-Engine, T-Tail Light Airplane

Flight Investigation of Stall, Spin and Recovery Characteristics of a Low-Wing, Single-Engine, T-Tail Light Airplane

H. P. Stough / D. J. Dicarlo / J. M. Patton

Flight tests were performed to investigate the stall, spin, and recovery characteristics of a four-place, low-wing, single-engine, T-tail, general aviation research airplane at an aft center-of-gravity position. Most stalls resulted in roll-offs. Spins were oscillatory in roll and pitch at 43 deg angle of attack; the magnitude of the oscillations was determined by aileron position. Power, flap deflection, and landing gear position did not affect the angle of attack to the spin. Antispin rudder followed by forward wheel with ailerons neutral produced the fastest and most consistent recoveries but the initial application of recovery controls did not always stop a spin.

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Title :

Flight Investigation of Stall, Spin and Recovery Characteristics of a Low-Wing, Single-Engine, T-Tail Light Airplane

Contributors:

H. P. Stough (author) / D. J. Dicarlo (author) / J. M. Patton (author)

Publication date :

1985

Size :

98 pages

Type of media :

Report

Type of material :

No indication

Language :

English

Keywords :

Aircraft , Aeronautics , Aerodynamic stalling , Aircraft spin , Angular momentum , Spin dynamics , Aerodynamic characteristics , Aircraft performance , Angle of attack , Controllability , Damage assessment , Flight tests

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