Tables of wing-aileron coefficients of oscillating air forces for two-dimensional supersonic flow

Vera Huckel, Barbara J. Durling
naca-tn-2055
Mar 1950


Wing-aileron coefficients of oscillating air forces for two-dimensional supersonic flow are tabulated for Mach numbers of ten-ninths, five-fourths, ten-sevenths, five-thirds, two and five-halves. Various ratios of control-surface chord to airfoil chord are employed in the calculations, names, 0.1, 0.2, 0.3, 0.4, 0.5, 0.6, 0.7, 0.8 and 0.9 and for each combination of chord ratio and Mach number approximately 35 values of reduced frequency are utilized.

An Adobe Acrobat (PDF) file of the entire report:
http://naca.central.cranfield.ac.uk/reports/1950/naca-tn-2055.pdf