Box method employing characteristic grid and based upon source superposition method of linear theory is used to calculate nonsteady aerodynamic forces on one rectangular and one cropped delta wing; allowance is made for downwash singularity at subsonic leading edge of cropped delta wing; results are shown for reduced frequency 0.9 (based on semispan) and for Mach numbers M in range 1.05 M less than 1.42.
Calculation of aerodynamic forces on two oscillating finite wings at low supersonic mach numbers
Svenska Aeroplan Aktiebolaget -- Tech Note
1964
24 pages
Article (Journal)
English
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