Static aeroelastic analysis of a three-dimensional oblique wing

• Published in: Computing systems in engineering 1990, Vol.1 (2), p.219-227
• Main Authors: Lee, I., Miura, H., Chargin, M.K.
• Format: Article
• Language: English
• Subjects: Aerodynamics
• ISSN: 0956-0521; 1873-6211
• DOI: 10.1016/0956-0521(90)90009-A

Requirements for the aeroelastic analyses of an oblique-wing aircraft have posed serious problems because available analysis programs cannot be applied to asymmetric configurations in the subsonic through the low supersonic speed range and the effects of the wing leading edge suction forces are completely disregarded. Therefore, a capability to perform static aeroelastic analyses of an oblique wing at arbitrary skew positions was developed based on the framework of the MSC/NASTRAN static aeroelastic analysis. By the means of DMAP alterations, a portion of the subsonic static aeroelastic analysis scheme was modified to insert an aerodynamic influence coefficient matrix created externally by the NASA Ames Research Center aerodynamic panel codes. The modified scheme can cover the subsonic as well as the supersonic range for both symmetric and asymmetric configurations. Static aeroelastic responses of the oblique wing are studied at two skew angles and, in particular, the capability to calculate three-dimensional camber effects on the aerodynamic properties of the wing is investigated. Various aerodynamic coefficients of the rigid oblique wing are computed for two Mach numbers, 0.7 and 1.4, and the angle of attack is varied from −5 through 15°. Also, the wing flexibility effects on the aerodynamic coefficients and the displacement are examined at a Mach number of 0.7 for a 45° swept wing.