Steady lifting flows over highly swept delta wings at large incidence were studied. After an exhaustive literature review, development of a vortex-lattice method was attempted. To demonstrate the feasibility of using such a method, an existing code was modified. A system of vortex lines to simulate the leading-edge wake was added. The coefficients predicted by the modified code were in good agreement with experimental data.
Subsonic steady and unsteady aerodynamic loads on missiles and aircraft
18.01.1983
Report
Keine Angabe
Englisch
Aircraft Manoeuvres Simulation Steady and Unsteady Aerodynamic
SAE Technical Papers | 2003
|Aircraft Manoeuvres Simulation Steady and Unsteady Aerodynamic
British Library Conference Proceedings | 2003
|