Gilberto Schleiniger
Abstract
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Linearized supersonic theory for flows past delta wings must be corrected for the cases of wing sweepback angles close to the Mach angle. Results of calculations based on a local transonic expansion valid near the leading edge are presented.
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Linearized supersonic theory for flows past delta wings must be corrected for the cases of wing sweepback angles close to the Mach angle. Results of calculations based on a local transonic expansion valid near the leading edge are presented.
Key concepts: Transonic, Delta wing, Mach number, Supersonic speed, Swept wing, Subsonic and transonic wind tunnel, Physics, Wing