Free-flight investigation at transonic and supersonic speeds of the rolling effectiveness of a 42.7 degree sweptback wing having partial-span ailerons

Carl A. Sandahl
naca-rm-l8e25
Oct 1948


An investigation of the rolling effectiveness at transonic and supersonic speeds of partial-span ailerons on a 42.7 degree sweptback wing having symmetrical circular-arc airfoil sections of 10-percent thickness ratio normal to the wing quarter-chord line has been made by means of rocket-propelled test vehicles. The results are compared with results of a supersonic wind-tunnel test at Mach number 1.9.

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http://naca.central.cranfield.ac.uk/reports/1948/naca-rm-l8e25.pdf