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A = Stern–Volmer constant-related coefficient B = Stern–Volmer constant-related coefficient c = wing-model chord length c = wing-model mean aerodynamic chord, mm cp = pressure coefficient f = frequency, Hz fs = sample frequency, Hz I = luminescence intensity (arbitrary units) M1 = freestream Mach number N = number of data points used for analysis p = pressure, Pa Rec = u1 c=v1 Reynolds number Re1 = u1=v1 unit Reynolds number, m 1 s = wing-model half-span, mm t = time, s u1 = freestream velocity w = von Hann window function x = streamwise coordinate y = spanwise coordinate 0 = time-averaged geometric flow angle of attack at wing root = 1.4 ratio of specific heat = y=s relative half-span coordinate = power spectral density ! = angular frequency ! = 2 f c=u1 reduced frequency
Steimle et al. (Wed,) studied this question.