Spin and Recovery Tests of a 1/28-Scale Model of the YF-93A Airplane

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Report Number: WADC TR 52-206
Author(s): Rose, Eugene S., Jr., Parker, Dan M.
Corporate Author(s): Flight Control Laboratory
Laboratory: Flight Control Laboratory
Date of Publication: 1952-08
Pages: 50
DoD Task:
Identifier: AD0014890
AD Number: 14890

Spin tests were made in the Wright Field 12-ft vertical wind tunnel. Conclusions are presented (on the basis of these tests) regarding the spin and recovery characteristics of the aircraft at 20,000 ft. These include: (1) for all load conditions and configurations tested, with ailerons held against the spin (stick left for a right spin), recovery attempts by full rudder reversal will fail to termiate the spin; (2) satisfactory to marginal recoveries will result from full rudder reversal and simulataneous movement of ailerons to full with the spin (stick right for a right spin); (3) the elevators should be full up during the first part of the spin recovery attempt for fastest recovery; and (4) the gross weight at take-off and the design gross weight over target conditions are more adverse to recovery.

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