Wing-body interference using a hybrid panel method

Summary The problem of determining the pressures acting on bodies in the region of wing-body interference in subsonic, inviscid flows is dealt with in detail in the current paper in the framework of a hybrid vortex lattice/first order panel method. Here the lift carryover and the wing-body interference effects are accounted for by the use of interpenetrating singularity panels. The non-lifting components are modeled by constant source panels and lifting elements by horse shoe vortices. Several alternative models have been programmed to study their effects on the pressure distribution in the wing-body interference region. The final procedure has been validated by comparing the pressures from experiments for several wing-body combinations.Notation AR Wing aspect ratio - b Wing span - B Body - C_p,C_p Pressure coefficient,P-P/1/2U² - ,n Unit normal to panel; also direction of normal - r(p, q) Distance between two points in three dimensional space; especially between a point where a source is located and a point where the velocities are computed - U,V_FS Free stream velocity - V_B Velocity due to body sources - V_D Velocity due to distributed vortices - V_T Velocity due to wing thickness sources - V_P Total velocity at pointP - V_c+ Velocity due to camber and incidence - W Wing - X_B Distance along length of body - Angle of attack - , Vortex strength - Air density - Azimuthal distribution of panels on fuselage - Non-dimensional spanwise station - Source density - Free stream conditions