1ONERA M6 Wing. Low Mach, Inviscid Flow. M_infty=0.3, alpha=0.0 deg. Freestream conditions (* indicates calculated) Mach number 0.300 Angle of attack 0.000 degrees Yaw angle 0.000 degrees Gamma 1.400 Gas constant (R) 286.959 m2/s2-K 1716.000 ft2/s2-R Static pressure 101353. N/m2 14.7000 lbf/in2 Static temperature 255.556 K 460.000 R Static density* 1.38207 kg/m3 0.268167E-02 slug/ft3 Total pressure* 107883. N/m2 15.6471 lbf/in2 Total temperature* 260.156 K 468.280 R Total density* 1.44511 kg/m3 0.280398E-02 slug/ft3 Speed of sound 320.418 m/s 1051.24 ft/s Velocity 96.1253 m/s 315.372 ft/s Dynamic pressure 6385.23 N/m2 0.926100 lbf/in2 Laminar Viscosity 0.162748E-04 kg/m-s 0.339906E-06 slug/ft-s Enthalpy* 256669. m2/s2 0.276276E+07 ft2/s2 Stagnation Enthalpy* 261289. m2/s2 0.281249E+07 ft2/s2 Downstream axis is +X, vertical axis is +Y Reference area : 1.00000E+00 ft2 Reference length: 1.00000E+00 ft Moments computed about reference point: X: 0.00000E+00 ft Y: 0.00000E+00 ft Z: 0.00000E+00 ft Force integration modes: Integrate over all selected points Normal derivatives computed second order Pressure integration performed as (p-pinf)*dA 1Subset 1 of ZONE 2 (*UNTITLED*), J= 1: area is 7.833314E+01 in2, 5.053740E-02 m2 Ax = 0.748534E+01 in2, Ay = 0.764344E+02 in2, Az = 0.406728E+01 in2 Ax+= 0.374267E+01 in2, Ay+= 0.000000E+00 in2, Az+= 0.316183E+01 in2 Ax-= 0.374267E+01 in2, Ay-= 0.764344E+02 in2, Az-= 0.905448E+00 in2 Reference dynamic pressure: 9.26100E-01 lbf/in2 Coefficients: Pressure Viscous Total CL = -7.51048E-02 CL = 0.00000E+00 CL = -7.51048E-02 CD = 1.35561E-05 CD = 0.00000E+00 CD = 1.35561E-05 CX = 1.35561E-05 CX = 0.00000E+00 CX = 1.35561E-05 CY = -7.51048E-02 CY = 0.00000E+00 CY = -7.51048E-02 CZ = 1.47290E-03 CZ = 0.00000E+00 CZ = 1.47290E-03 CMX = 3.39800E-02 CMX = 0.00000E+00 CMX = 3.39800E-02 CMY = -1.12563E-03 CMY = 0.00000E+00 CMY = -1.12563E-03 CMZ = -3.18147E-02 CMZ = 0.00000E+00 CMZ = -3.18147E-02 Dimensional surface totals: Lift = -1.00159E+01 lbf Drag = 1.80782E-03 lbf X-force = 1.80782E-03 lbf Y-force = -1.00159E+01 lbf Z-force = 1.96423E-01 lbf X-moment = 5.43781E+01 in*lbf Y-moment = -1.80135E+00 in*lbf Z-moment = -5.09131E+01 in*lbf Subset 1 of ZONE 3 (*UNTITLED*), J= 1: area is 7.833306E+01 in2, 5.053736E-02 m2 Ax = 0.748535E+01 in2, Ay = 0.764346E+02 in2, Az = 0.406728E+01 in2 Ax+= 0.374267E+01 in2, Ay+= 0.764346E+02 in2, Az+= 0.316183E+01 in2 Ax-= 0.374267E+01 in2, Ay-= 0.000000E+00 in2, Az-= 0.905449E+00 in2 Reference dynamic pressure: 9.26100E-01 lbf/in2 Coefficients: Pressure Viscous Total CL = 7.51014E-02 CL = 0.00000E+00 CL = 7.51014E-02 CD = 1.33403E-05 CD = 0.00000E+00 CD = 1.33403E-05 CX = 1.33403E-05 CX = 0.00000E+00 CX = 1.33403E-05 CY = 7.51014E-02 CY = 0.00000E+00 CY = 7.51014E-02 CZ = 1.47125E-03 CZ = 0.00000E+00 CZ = 1.47125E-03 CMX = -3.39778E-02 CMX = 0.00000E+00 CMX = -3.39778E-02 CMY = -1.12443E-03 CMY = 0.00000E+00 CMY = -1.12443E-03 CMZ = 3.18125E-02 CMZ = 0.00000E+00 CMZ = 3.18125E-02 Dimensional surface totals: Lift = 1.00154E+01 lbf Drag = 1.77904E-03 lbf X-force = 1.77904E-03 lbf Y-force = 1.00154E+01 lbf Z-force = 1.96203E-01 lbf X-moment = -5.43747E+01 in*lbf Y-moment = -1.79943E+00 in*lbf Z-moment = 5.09096E+01 in*lbf *********************************** Totals *********************************** ** Total Wetted area is 1.566662E+02 in2, 1.010748E-01 m2 Coefficients: Pressure Viscous Total CL = -3.39001E-06 CL = 0.00000E+00 CL = -3.39001E-06 CD = 2.68964E-05 CD = 0.00000E+00 CD = 2.68964E-05 CX = 2.68964E-05 CX = 0.00000E+00 CX = 2.68964E-05 CY = -3.39001E-06 CY = 0.00000E+00 CY = -3.39001E-06 CZ = 2.94415E-03 CZ = 0.00000E+00 CZ = 2.94415E-03 CMX = 2.13087E-06 CMX = 0.00000E+00 CMX = 2.13087E-06 CMY = -2.25007E-03 CMY = 0.00000E+00 CMY = -2.25007E-03 CMZ = -2.16067E-06 CMZ = 0.00000E+00 CMZ = -2.16067E-06 Dimensional surface totals: Lift = -4.52087E-04 lbf Drag = 3.58686E-03 lbf X-force = 3.58686E-03 lbf Y-force = -4.52087E-04 lbf Z-force = 3.92626E-01 lbf X-moment = 3.41003E-03 in*lbf Y-moment = -3.60078E+00 in*lbf Z-moment = -3.45772E-03 in*lbf