Pressure Distribution on the Fuselage of a Midwing Airplane Model at High Speeds (1939)
NASA Technical Reports Server (NTRS) · leaf 13
r Figure 9.- Comparison of theoretical pressures on the wing alone and on the fuselage alone with the experimental pressures of the combination. Of, 0°;.M, 0.182.
NASA Technical Reports Server (NTRS)
Internet Archive · NASA Technical Reports · Public domain (US government work). Free to use for anything.
