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.
Davari,A. , Hadi Dulabi,M. , Dr. Soltani,M. R. and asakari,F. (2009). Impact of Body on the Tail Surface Flowfield at High Incidences. Journal of Aerospace Science and Technology, 6(1), 25-35.
MLA
Davari,A. , , Hadi Dulabi,M. , , Dr. Soltani,M. R. , and asakari,F. . "Impact of Body on the Tail Surface Flowfield at High Incidences", Journal of Aerospace Science and Technology, 6, 1, 2009, 25-35.
HARVARD
Davari A., Hadi Dulabi M., Dr. Soltani M. R., asakari F. (2009). 'Impact of Body on the Tail Surface Flowfield at High Incidences', Journal of Aerospace Science and Technology, 6(1), pp. 25-35.
CHICAGO
A. Davari, M. Hadi Dulabi, M. R. Dr. Soltani and F. asakari, "Impact of Body on the Tail Surface Flowfield at High Incidences," Journal of Aerospace Science and Technology, 6 1 (2009): 25-35,
VANCOUVER
Davari A., Hadi Dulabi M., Dr. Soltani M. R., asakari F. Impact of Body on the Tail Surface Flowfield at High Incidences. Journal of Aerospace Science and Technology, 2009; 6(1): 25-35.
