Transition Measurement of Natural Laminar Flow Wing on Supersonic Experimental Airplane NEXST-1

layer. In this paper, the results of the transition measurement are introduced and compared with the numerically predicted results. The transition locations detected experimentally are in good agreement with the predicted locations, and the natural laminar flow effect is confirmed in the aerodynamic design conditions of the supersonic experimental airplane NEXST-1. Nomenclature C = local chord length CL = lift coefficient of full configuration Cp = surface pressure coefficient Cprms = fluctuation (rms) of surface static pressure of the wind tunnel E = dc output of the hot-film sensor e = ac output of the hot-film sensor H = altitude M = Mach number p = local surface pressure measured by the dynamic pressure transducer PPRT = local total pressure measured by the Preston tube Rec = Reynolds number based on the mean aerodynamic chord S = semispan length Tblow = time from the beginning of the blow in the windtunnel test Tlo = time from the liftoff in the flight test TTC = local temperature measured by the thermocouple X = chordwise position Xtip = axial length from the tip of the wind-tunnel model Y = spanwise position � = angle of attack ’ = circumferential angle from the top line on the nose 0 = fluctuation