MISLIFT- AERODYNAMIC LIFT ON WING-BODY COMBINATIONS AT SMALL ANGLES OF
ATTACK IN SUPERSONIC FLOW

( NASA Langley Research Center )

     Two separate and distinct theories are incorporated in this computer
program to estimate the lift-induced pressures existent on a wing-body com-
bination. 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 at-
tack, and (2) the linear-theory integral equations, which is used to evalu-
ate the lifting pressures induced by the wing.

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

     Most of the input required by this program is involved with the de-
scription of the missile planform geometry. The output consists of the com-
puted value of the lifting pressure slope (the differential pressure coef-
ficient 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.

     COSMIC, and the COSMIC logo are registered trademarks of the National
Aeronautics and Space Administration. All other brands and product names
are the trademarks of their respective holders.



LANGUAGE: FORTRAN IV

MACHINE REQUIREMENTS: CDC 6000 SERIES

PROGRAM SIZE: APPROXIMATELY 638 SOURCE STATEMENTS

DISTRIBUTION MEDIA: 9 Track 1600 BPI Card Image Format Magnetic Tape

PROGRAM NUMBER: LAR-10932

DOMESTIC - DOCUMENTATION PRICE: $15.00    PROGRAM PRICE: $200.00

INTERNATIONAL - DOCUMENTATION PRICE: $30.00   PROGRAM PRICE: $400.00



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