#################################################################################### # # TA1 External Aerodynamics AC1-02 RAE M2155 Wing # # File contains CFD boundary layer results at x/c=0.4342 and y/b=0.3500 # # x/c is the distance aft of leading edge in the direction of the root chord divided # by the local chord # # y/b is the spanwise location divided by the wing semi-span # # Z/C is the distance from the surface divided by the geometric mean chord # # U/UP is the local velocity divided by the velocity at the edge of the boundary # layer # # 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) # Turbulence model : Spalart Allmaras ##################################################################################### %AC = 1-02 %Column1Name = Z/C %Column1Units = %Column1Type = Real %Column2Name = U/UP %Column2Units = %Column2Type = Real %End of Metadata 0.743435E-06 0.000000E+00 0.813514E-05 0.367685E-01 0.172920E-04 0.787258E-01 0.267799E-04 0.125888E+00 0.385845E-04 0.178090E+00 0.513821E-04 0.232909E+00 0.670481E-04 0.285839E+00 0.851413E-04 0.331763E+00 0.107096E-03 0.367955E+00 0.130926E-03 0.395533E+00 0.159500E-03 0.417453E+00 0.192486E-03 0.436207E+00 0.230990E-03 0.453283E+00 0.273905E-03 0.469488E+00 0.326309E-03 0.485282E+00 0.385002E-03 0.500939E+00 0.453954E-03 0.516634E+00 0.533387E-03 0.532494E+00 0.625287E-03 0.548641E+00 0.732302E-03 0.565226E+00 0.856637E-03 0.582417E+00 0.999947E-03 0.600389E+00 0.116588E-02 0.619340E+00 0.135795E-02 0.639501E+00 0.157992E-02 0.661127E+00 0.183709E-02 0.684497E+00 0.213540E-02 0.709919E+00 0.247994E-02 0.737710E+00 0.287898E-02 0.768170E+00 0.334014E-02 0.801521E+00 0.387455E-02 0.837748E+00 0.449225E-02 0.876266E+00 0.520561E-02 0.915354E+00 0.603215E-02 0.951603E+00 0.698590E-02 0.980168E+00 0.808815E-02 0.996885E+00 0.936008E-02 0.100168E+01 0.108299E-01 0.999214E+00 0.125249E-01 0.995078E+00 0.144800E-01 0.991975E+00 0.167328E-01 0.989714E+00 0.193267E-01 0.987300E+00 0.223107E-01 0.984286E+00 0.257389E-01 0.980756E+00 0.296733E-01 0.976876E+00