Abstract:
Pressure and heat-transfer measurements have been made on the lee surface of a delta wing at 14 degrees incidence in free flight over a Mach number range of 1.0 to 3.6 and at free-stream Reynolds numbers between 6 and 24 millions based on centreline chord. A comparison is made with the results from a previous free-flight model test to assess the effect on the lee surface pressure and heat transfer of a change in sweepback angle from 65.9 to 76 degrees.
