Wake measurements were made in a vertical plane behind a semi span wing section of XP-51 fighter at Mach numbers up to 0.78. The results show that the large increase in drag coefficients shown by wind-tunnel tests beyond the critical Mach number was also obtained under flight conditions, and that the wake width is extended sharply when shock is encountered. At the wing section tested, the critical Mach number of the section is exceeded by 0.05 before large increases in the profile-drag coefficient occur.
Wake Measurements Behind a Wing Section of the XP-51 Airplane in Fast Dive
1947
21 pages
Report
No indication
English
Wake measurements behind wing section of fighter airplane in fast dives
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