Author/Authors :
Davari, AR islamic azad university - Science and Research Campus - Dept of Mech and Aerospace Eng, ايران , Dulabi, M Hadi malekeashtar university of technology - Dept of Aerospace Eng, تهران, ايران , Soltani, M R sharif university of technology - Dept of Aerospace Eng, تهران, ايران , Askari, F sharif university of technology, تهران, ايران
Abstract :
An experimental study was performed to investigate the effects of the body angle of attack on the tail surface pressure distribution for a half body-tail combination in subsonic flow. The results show, in small deflection angle regions, that the tail deflection has the same effect on the surface pressure as the body angle of attack. However at moderate to high deflections, the flowfiled caused by the tail deflection angle is completely different from that of the body angle of attack, which is an indication of the nose and body vortex shedding effects on the tail at high angle of attack regime.
