#################################################################################### # # TA1 External Aerodynamics AC1-02 RAE M2155 Wing # # File contains experimental measurements at x/c=1.0501 and y/b=0.0.3626 for the # surface/wake profiles # Data taken from AGARD 303 data files # # x/c is the distance aft of leading edge in the direction of the root chord divided # by the the local chord # # y/b is the spanwise location divided by the wing semi span # # Z/C is the distance from the surface of the model divided by the geometric mean # chord # # U/UP is the local velocity within a shear layer divided by the velocity obtained # from the total velocity at the edge of a shear layer and the local static pressure # # P/H is the local static pressure divided by the freestream total pressure # # Mach number : 0.806 # Reynolds number : 4.1 x 10^6 # Angle of incidence : 2.50 (deg) ##################################################################################### %AC = 1-02 %Column1Name = Z/C %Column1Units = %Column1Type = Real %Column2Name = U/UP %Column2Units = %Column2Type = Real %Column3Name = P/H %Column3Units = %Column3Type = Real %End of Metadata -0.02989 1.0000 0.7058 -0.02810 0.9989 0.7055 -0.02728 0.9986 0.7055 -0.02605 0.9983 0.7050 -0.02464 0.9961 0.7054 -0.02334 0.9878 0.7036 -0.02204 0.9827 0.7043 -0.02056 0.9771 0.7049 -0.01924 0.9555 0.7020 -0.01774 0.9369 0.7021 -0.01625 0.9290 0.7037 -0.01478 0.9043 0.7038 -0.01323 0.8724 0.7045 -0.01194 0.8399 0.7039 -0.01047 0.8171 0.7043 -0.00893 0.7751 0.7043 -0.00788 0.7365 0.7044 -0.00659 0.6904 0.7039 -0.00548 0.6456 0.7029 -0.00442 0.6014 0.7021 -0.00334 0.5626 0.7009 -0.00253 0.5338 0.7012 -0.00149 0.4997 0.7004 -0.00034 0.4763 0.7000 0.00059 0.4643 0.7001 0.00158 0.4619 0.6989 0.00307 0.4727 0.6996 0.00453 0.4920 0.6996 0.00613 0.5183 0.7001 0.00771 0.5452 0.7006 0.00928 0.5781 0.7007 0.01080 0.6125 0.7009 0.01229 0.6421 0.7013 0.01391 0.6801 0.7016 0.01521 0.7090 0.7021 0.01656 0.7357 0.7028 0.01835 0.7709 0.7026 0.01991 0.8032 0.7020 0.02153 0.8334 0.7022 0.02313 0.8554 0.7015 0.02488 0.8821 0.7010 0.02643 0.9070 0.7004 0.02793 0.9277 0.6995 0.02947 0.9446 0.6967 0.03098 0.9585 0.6979 0.03258 0.9713 0.6972 0.03409 0.9804 0.6965 0.03560 0.9875 0.6961 0.03717 0.9934 0.6967 0.03847 0.9964 0.6951 0.04003 0.9977 0.6940 0.04151 0.9984 0.6955 0.04295 0.9997 0.6940 0.04455 1.0000 0.6933