Paneling methods with vorticity effects and corrections for nonlinear compressibilityThe prediction of missile aerodynamic characteristics is presently undertaken through the application of supersonic paneling methods and nonlinear corrections to the prediction of missile aerodynamic characteristics. Attention is given to supersonic panel methods and line-singularity methods for the modeling of axisymmetric bodies, in combination with corrections for nonlinear flow phenomena, which are applied to complete missile, inlets, and wing-body combinations. The LRCDM2 computer program is used as an example of the methods presented.
Document ID
19870035665
Acquisition Source
Legacy CDMS
Document Type
Conference Proceedings
Authors
Dillenius, Marnix F. E. (Nielsen Engineering and Research, Inc. Mountain View, CA, United States)
Allen, Jerry M. (NASA Langley Research Center Hampton, VA, United States)