CHEAT TRANSFER DISTRIBUTIONS ON A 70° DELTA WING WITH FLAP-INDUCED SEPARATION

摘要

An experimental study of heat transfer distributions on the compression surface of a 70 deg delta at 8.2 M and a free stream Reynolds number of 170000/in is presented. The tests were carried out in a hypersonic gun tunnel. The model used was a swept plain-cropped delta wing with 70 deg sweep. This had a trailing edge with incidence variable in 3 discrete steps between 10 and 30 deg. Emphasis is placed on the flow separation induced by a trailing-edge flap, which is shown to be strongly dependent upon transitional effects for these flow conditions. The experimental results are compared with pressure and flow visualization studies carried out on one delta wing (of 70 deg sweepback) with and without full-span trailing edge flaps.