Calculation of lift and pitching moments due to angle of attack and steady pitching velocity at supersonic speeds for thin sweptback tapered wings with streamwise tips and supersonic leading and trailing edges

Author / Creator

Martin, John C., author

Available as

Online

Summary

On the basis of linearized supersonic-flow theory the stability derivatives, moment coefficients due to angle of attack and steady pitching velocity, and lift coeffient due to steady pitching veloc...

On the basis of linearized supersonic-flow theory the stability derivatives, moment coefficients due to angle of attack and steady pitching velocity, and lift coeffient due to steady pitching velocity, were derived for a series of thin swept-back tapered wings with streamwise tips and supersonic leading and trailing edges. The results are valid for a range of Mach number for which the Mach lines from the leading edge of the center section cut the trailing edges. An addiitional limitation is that the foremost Mach line from either tip may not intersect the remote half of the wing.

The results of the analysis are presented in a series of design charts. Some illustrative variations of the derivatives and of the chordwise center-of-pressure location with the various wing design parameters are also included.

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