Publication Date:
2019-07-11
Description:
In order to obtain insight into the flow conditions on tail surfaces on airplanes during spins, pressure-distribution measurements were performed on a rotating model of the design BFW-M31. For the time being, the tests were made for only one angle of attack (alpha = 60 degrees) and various angles of yaw and rudder angles. The results of these measurements are given; the construction of the model, and the test arrangement used are described. Measurements to be performed later and alterations planned in the test arrangement are pointed out.
Keywords:
Aircraft Design, Testing and Performance
Type:
NACA-TM-1220
,
ZWB Forschungsbericht Nr. 704; Rept-704
Format:
application/pdf
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