Abstract:

ESDU 91007 applies to missiles in which interference loads make a large contribution because of the small span-to-body-diameter ratio; an axisymmetric body with mid-wing is considered at low angles of attack (less than 2 degrees) in subsonic or supersonic flow. The method takes the body-alone contribution (ESDU 89008 provides values for forebody-cylinders) and adds contributions from the wing (in the presence of the body) and from the change in body lift-curve slope due to the wing. Both contributions are obtained by factoring the isolated wing lift-curve slope from ESDU 70011 or 70012 (for subsonic or supersonic flow respectively). Equations and graphs are given for the factors. The wing factor is a function of span-to-body-diameter ratio, while, at supersonic speeds, the body correction factor depends on whether the Mach line from the wing tip intersects the root chord or passes downstream of its trailing-edge. In the latter case the factor is a function of body length downstream of the wing. The method applies to straight or swept-forward trailing-edges, but has been found to be satisfactory for moderate trailing-edge sweeps. It is found to compare with experiment within about 10 per cent. A worked example illustrates the use of the method.