Julio Chu

• Experimental surface pressure data obtained on 65 ̊delta wing across Reynolds number and Mach number ranges
• High-Reynolds-number test of a 5-percent-thick low-aspect-ratio semispan wing in the Langley 0.3-meter transonic cryogenic tunnel, wing tunnel distributions
• Pressure measurements on a thick cambered and twisted 58ʻ́
• Pressure meaurements on a thick cambered and twisted 58 [degree] delta wing at high subsonic speeds