Investigation of Aerodynamic Loads at Spin Entry.
Annual rept. 1 Apr 75-1 May 76,
NIELSEN ENGINEERING AND RESEARCH INC MOUNTAIN VIEW CALIF
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The second years work is summarized on an investigation of the aerodynamic load distribution on fighter-bomber type aircraft at incipient spin entry flight conditions. The principal tasks were development of an asymmetric vortex-lattice computer program for a wing-body in combined pitch and sideslip and water tunnel tests on realistic aircraft nose models. The technical approach on the vortex-lattice program is described and typical calculative results are shown. The tunnel test program is described. A cooperative test program between ONR and Langley Research Center, NASA, to obtain simultaneous force and moment and flow field measurements on a generalized figher model at high angles of attack is described. Computer methods have been developed for vortex shedding from circular noses, for the wing-body loads induced by an arbitrary distribution of nose vortices, and for afterbody and tail loads. The principal missing features are noncircular nose effects and detailed experimental data to check the methods. Author