############################################################################## # # TA1 External Aerodynamics AC1-02 RAE M2155 Wing # # File contains the Experimental pressure coefficients at y/b = 0.30 # # Mach number : 0.806 # Reynolds number : 4.1 x 10^6 # Angle of incidence : 2.50 (deg) ############################################################################## %AC = 1-02 %Column1Name = x/c %Column1Units = %Column1Type = Real %Column2Name = Cp %Column2Units = %Column2Type = Real %End of Metadata 0.0500 -0.7756 0.0750 -1.0643 0.1000 -1.1992 0.1250 -1.2707 0.1500 -1.3044 0.1750 -1.3041 0.2000 -1.2862 0.2250 -1.0788 0.2500 -0.8529 0.2750 -0.7743 0.3000 -0.7362 0.3250 -0.7153 0.3500 -0.7035 0.3750 -0.6795 0.4000 -0.6148 0.4250 -0.5183 0.4500 -0.4570 0.4750 -0.4286 0.5000 -0.4091 0.5250 -0.3959 0.5500 -0.3838 0.5750 -0.3720 0.6000 -0.3615 0.6250 -0.3514 0.6500 -0.3457 0.6750 -0.3389 0.7250 -0.3191 0.7500 -0.3069 0.8000 -0.2732 0.8500 -0.1865 0.9000 -0.0817 0.9500 0.0286 0.9750 0.0762