Evaluation and Application of VSAERO to a Nonaxisymmetric Afterbody with Thrust Vectoring 871775
The incorporation of multifunction nozzles into fighter aircraft can enhance fighter maneuverability and performance. Development of computational methods will be vital for determining efficient methods of aerodynamic integration of these nozzles. This paper will discuss the utilization of a current technology subsonic panel method (VSAERO) for predicting the flow about a nonaxisymmetric nozzle afterbody with and without a thrust vectoring concept. Two modelings for the vectored exhaust are presented. Highly favorable comparisons were obtained with a rudimentary modeling of the vectored exhaust.
Citation: Carlson, J., "Evaluation and Application of VSAERO to a Nonaxisymmetric Afterbody with Thrust Vectoring," SAE Technical Paper 871775, 1987, https://doi.org/10.4271/871775. Download Citation
Author(s):
John R. Carlson
Affiliated:
National Aeronautics and Space Administration Langley Research Center Hampton, VA
Pages: 12
Event:
Aerospace Technology Conference and Exposition
ISSN:
0148-7191
e-ISSN:
2688-3627
Related Topics:
Nozzles
Aircraft
Thrust
Aerodynamics
Simulation and modeling
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