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Evaluation of the constant pressure panel method (CPM) for unsteady air loads predictionThis paper evaluates the capability of the constant pressure panel method (CPM) code to predict unsteady aerodynamic pressures, lift and moment distributions, and generalized forces for general wing-body configurations in supersonic flow. Stability derivatives are computed and correlated for the X-29 and an Oblique Wing Research Aircraft, and a flutter analysis is carried out for a wing wind tunnel test example. Most results are shown to correlate well with test or published data. Although the emphasis of this paper is on evaluation, an improvement in the CPM code's handling of intersecting lifting surfaces is briefly discussed. An attractive feature of the CPM code is that it shares the basic data requirements and computational arrangements of the doublet lattice method. A unified code to predict unsteady subsonic or supersonic airloads is therefore possible.
Document ID
19880045008
Document Type
Conference Paper
Authors
Appa, Kari (Northrop Corp. Hawthorne, CA, United States)
Smith, Michael J. C. (Northrop Corp. Aircraft Div., Hawthorne, CA, United States)
Date Acquired
August 13, 2013
Publication Date
January 1, 1988
Subject Category
AERODYNAMICS
Report/Patent Number
AIAA PAPER 88-2282
Meeting Information
Structures, Structural Dynamics and Materials Conference(Williamsburg, VA)
Funding Number(s)
CONTRACT_GRANT: NAS2-12597
Distribution Limits
Public
Copyright
Other