Solution by iteration estimates performance of twisted and cambered wings of arbitrary planform. SUBAER based on linearized theory lifting-surface solution provides spanwise distribution of theoretical leading edge thrust, in addition to surface distribution of perturbation velocities. Program written in FORTRAN IV.
Wing Subsonic Aerodynamic Performance Estimates
NASA Tech Briefs ; 7
1983-08-01
Sonstige
Keine Angabe
Englisch
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