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Path: ACPro/Newtonian
-------------------------------------------------------------------------- Compute the center of pressure from the cad model. It only computes the x value of the center-of-mass. Since version 4 (ACT) -------------------------------------------------------------------------- Form: [c, tErr] = NewtonianCPFromCAD( uMag, alpha, rho, g, z ) -------------------------------------------------------------------------- ------ Inputs ------ uMag (1,1) Magnitude of the velocity alpha (1,:) Angle of attack (rad) rho (1,1) Density g (1,1) CAD data structure z (1,1) Z location of center of mass ------- Outputs ------- c (1,1) Center of pressure in x tErr (3,1) Torque error -------------------------------------------------------------------------- Reference for Demo: X-15 Flight 91, http://en.wikipedia.org/wiki/X-15_Flight_91 http://www.whiteeagleaerospace.com/blog/2009/08/24/the-highest-x-15-flight/ --------------------------------------------------------------------------
AC: ACCoord/UFromAlphaBeta ACPro: ACPerformance/ActiveAeroSurfacesDisplay AeroUtils: CAD/LoadCAD Common: Atmosphere/StdAtm Common: Graphics/Plot2D Common: Graphics/PolygonProps Math: Linear/Cross Math: Linear/Dot Math: Linear/DupVect
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