Abstract:

A force measurement experimental study was performed on a flatplate delta wing of 82.5° sweep angle and combination of the identical delta wing with low dorsal fins. The test was conducted at the lowspeed wind tunnel using a six-component internal straingage balance at 12°~32° angles of attack. Two fins of different heights were tested, and the ratios of the local fin height to the local wing semispan were 0.3 and 0.6 respectively. There were two Reynolds numbers, 1.66 ×10.6 and 2.33×10.6,used.

Key words: vortex , stability,  , high , angle , of , attack,  , fin,  , slender , body,  , flatplate , delta , wing