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

*the second-order shock-expansion theory, which is used to obtain the lifting pressures on the body alone at small angles of attack, and**the linear-theory integral equations, which is used to evaluate the lifting pressures induced by the wing.*

These equations relate the local surface slope at a point on the lifting surface to the pressure differential at the point and the influence of the pressures upstream of the point. The numerical solution of these equations is effected by treating the wing planform as a composite of elemental rectangles and applying summation techniques to satisfy the necessary integral relations.

Most of the input required by this program is involved with the description of the missile planform geometry. The output consists of the computed value of the lifting pressure slope (the differential pressure coefficient per degree angle of attack) for each of the elements in the planform array. A force and moment summary is presented for the configuration under consideration. ( NASA Langley Research Center )

This program was released by NASA through COSMIC as LAR-10932. The italicized text above is from the official NASA release.

- Go to the page of references for the MISLIFT program.
- Download mislift.zip, containing the original source code.