A method for modifying two-dimensional adaptive wind-tunnel walls including analytical and experimental verification
Joel L. Everhart, United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch
National Aeronautics and Space Administration, Scientific and Technical Information Branch, 1983 - Mathematics - 45 pages
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analysis analytic angle of attack APPENDIX assumed Boundary conditions calculated Calspan Cauchy integral Cauchy integral formula chord chord-height ratio circular cylinder convergence characteristics defined determined effective walls effective wind-tunnel wall evaluated Experimental Verification exterior factor of 0.25 flexible-wall tunnel FLEXWAL program four iterations free-air free-stream Mach number ft/sec imaginary flow fields incompressible incompressible flow infinity integrals in equations inviscid isentropic itera iterations were started Langley Research Center Laplace equation lower walls MAAD computer MAAD program measurement stations method NACA 0012 airfoil National Physical Laboratory perturbation-velocity potential presented in figure pressure data pressure orifices real flow relaxation factor root mean square shock waves shown in figure singularity solid flexible walls spline curve starting from straight straight walls straight-wall settings streamline slope strip tion transonic Mach number tunnel walls two-dimensional U+(z undiverged walls upper and lower velocity wall change wall corrections wall shape obtained