Publication Date:
2019-06-28
Description:
A method for converting steady state, potential panel methods into a time-dependent mode is derived and applied to several test cases. For this development, an improved vortex wake model was constructed which was also suitable for simulating the leading edge separation of slender wings at high angles of attack. Computed flow-field simulations are presented for various unsteady, and high-angle-of-attack conditions, involving geometries such as simple wings, rotors, and complete aircraft configurations.
Keywords:
AIRCRAFT STABILITY AND CONTROL
Type:
AIAA PAPER 86-2180
Format:
text
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