#################################################################################### # # TA1 External Aerodynamics AC1-02 RAE M2155 Wing # # File contains experimental measurements at x/c=1.0498 and y/b=0.7633 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 -0.03173 1.0000 0.7087 -0.03048 1.0109 0.7083 -0.02920 1.0217 0.7075 -0.02794 1.0331 0.7071 -0.02655 1.0452 0.7071 -0.02533 1.0547 0.7066 -0.02399 1.0638 0.7059 -0.02254 1.0726 0.7057 -0.02130 1.0776 0.7057 -0.01986 1.0802 0.7048 -0.01842 1.0782 0.7030 -0.01702 1.0707 0.7031 -0.01553 1.0601 0.7025 -0.01422 1.0438 0.7017 -0.01289 1.0285 0.7010 -0.01135 1.0124 0.7007 -0.01034 1.0025 0.7005 -0.00906 0.9947 0.7003 -0.00803 0.9904 0.7007 -0.00699 0.9818 0.7008 -0.00594 0.9744 0.7014 -0.00520 0.9602 0.7023 -0.00421 0.9361 0.7022 -0.00308 0.9019 0.7028 -0.00218 0.8703 0.7027 -0.00121 0.8423 0.7019 0.00014 0.8193 0.7024 0.00154 0.8347 0.7022 0.00306 0.8975 0.7023 0.00453 1.0000 0.7022