MISLIFT
Aerodynamic Lift on Wing-Body Combinations at Small Angles of Attack in Supersonic Flow
Two separate and distinct theories are incorporated in this computer program to estimate the lift-induced pressures existent on a wing-body combination. These are (1) the second-order shock-expansion theory, which is used to obtain the lifting pressures on the body alone at small angles of attack, and (2) the linear-theory integral equations, which is used to evaluate the lifting pressures induced by the wing. Most of the input required by this program is involved with the description of the missile planform geometry. A force and moment summary is presented for the configuration under consideration.
Program Size: 638 Statements
Computer Language: FORTRAN IV
Copyright (c) 1996 Pacific HiTech, Inc. and COSMIC 
