Prediction of unsteady aerodynamic loadings on non-planar wings and wing-tail configurations in supersonic flow.
Part II,
Computer program description /
Grodona D. Kramer, George E. Keylon.

Description

Main Author

Kramer, Gordon D.

Related Names

Keylon, George E., author.
United States. Air Force.
Air Force Flight Dynamics Laboratory (U.S.)
Boeing Company. Commercial Airplane Group

Language(s)

English

Published

Wright-Patterson Air Force Base, Ohio : Air Force Flight Dynamics Laboratory, Air Force Systems Command, United States Air Force, 1972.

Subjects

Airplanes > Airplanes / Tail surfaces.
Airplanes > Airplanes / Wings, Swept-back.
Aerodynamics, Supersonic.
Unsteady flow (Aerodynamics)
Aerodynamic load.
Airplanes > Airplanes / Control surfaces.

Summary

The Mach box technique for unsteady aerodynamic loadings has been extended to include wing and tail with dihedral angles and vertical separation. A digital computer program, written in FORTRAN, is presented. The program provides for up to nine sweep angles of the leading and trailing edges of edges of each surface. First order position theory thickness correction is available as an option and two refinement procedures are provided, subdivision with averaging and velocity potential smoothing. For a maximum of twenty oscillatory mode shapes the program calculates normal washes, velocity potentials, lifts, pressures and generalized forces matrices. If only one surface is being analyzed, sampling of wake up-wash, side-wash and longitudinal wash is available.

Note

"March 1972."

Physical Description

xxiv, 399 pages : illustrations ; 28 cm.

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