Abstract:

Unsteady tunnel wall corrections for a delta wing oscillating in pitch to very high angles of attack were presented, applying influence functions in steady wall pressure correction method and unsteady wall pressure at the optimum points. Results of this study showed that the unsteady wall corrections, just like unsteady aerodynamic load, produce hysteresis loops, The unsteady wall correction values were increasing with the reduced frequencies increase at the begining, and then afterward on the contrary. For the same ratio of wing span to test section width, the unsteady wall correction values for a delta wing with a sweptback angle of 70° were greater than those with a sweptback angle of 60°.

Key words: post-stall, wall interference, delta wings