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
1983-01-18
Report
No indication
English
Aircraft Manoeuvres Simulation Steady and Unsteady Aerodynamic
SAE Technical Papers | 2003
|Aircraft Manoeuvres Simulation Steady and Unsteady Aerodynamic
British Library Conference Proceedings | 2003
|