Comparison of zero-lift drags determined by flight tests at transonic speeds of symmetrically mounted nacelles in various spanwise positions on a 45 degrees sweptback wing and body combination

William B. Pepper, Jr., Sherwood Hoffman
naca-rm-l51d06
May 1951


Rocket-powered models were flown at transonic speeds to determine the effect of nacelle location on zero-lift drag. Symmetrically mounted nacelles of fineness ratio 9.66 were successively located spanwise at 18, 25, 40, 60, 80, and 96 percent of the wing semispan The chordwise location of the nacelles was such that approximately 50 percent of the nacelle length was forward of the wing maximum thickness.

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