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1.0 x/CHORD FIGURE airfoil algebraic system analysis angle of attack arbitrary aspect ratio wing boundary conditions calculation scheme Cauchy problem chordwise compressible flow computer program correction potential differential equation Discontinuous flow past e.g. reference equations 23 evaluation flow calculations flow solutions FORMAT freestream Mach number H H H harmonic solution incompressible flow influence coefficients influence function integral equation Jacobian matrix Kutta condition leading edge linearized solution method of parametric method of steepest NACA NAMELIST NASA Newton's method NOWW0C numerical analysis numerical solutions obtained PARABOLIC ARC WING parameter parametric differentiation past a non-lifting perturbation velocity potential cp PRESENT RESULT pressure distribution rectangular wing shock discontinuities solution of system spanwise steepest descent Subcritical flow subroutine subsonic Supercritical flow past swept wing symmetrical system 23 system 31 tcomp Thickness ratio three-dimensional two-dimensional unique velocity potential wing configuration wing planform WING RECTANGULAR PLANFORM