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నైరూప్య

Effect of Stall on blended Wing Body Aircraft

Darshan N, Deepa MS, Komalesh BE

This paper represents the study of effect of wing sweep on blended wing body aircraft at different sweep angles with fixed platform design. A3-D BWB model was designed in CATIA V5 and simulation was carried in ANSYS fluent. Twenty-three BWB geometries with varying sweep ranging from -400 (forward sweep angle) to 550 (backward sweep angle) were designed, with the aero foil profiles and twist distribution unchanged from the original geometry. This gives insight on the platform of the design. The simulations were carried out using Euler solutions of flow field. The body was meshed with unstructured grids with tetrahedral and triangular shapes. The best sweep angle BWB was found between forward and backward sweep angles. The best sweep angle was considered and the angle of attack of the whole body of the aircraft was changed. The stalling angle of attack of the aircraft was found using the best sweep angle.