Publication Date:
2019-06-28
Description:
A theoretical and experimental investigation of the longitudinal and lateral-directional stability and control of a finned cylindrical body has been conducted at Mach 6. The angle-of-attack range extended from 20 to 65 deg. to encompass maximum lift. Stability, performance, and trim could be accurately predicted with the fins in the + arrangement but this was not the case when the fins were in the x orientation where windward fin choking occurred at angles of attack above 50 deg. reducing their effectiveness and causing pitch up.
Keywords:
AERODYNAMICS
Type:
NASA-TM-89050
,
NAS 1.15:89050
Format:
application/pdf
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