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Evaluation and Application of VSAERO to a Nonaxisymmetric Afterbody with Thrust Vectoring
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English
Abstract
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.
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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.Also In
References
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- Burley, James R., II Carlson, John R. Henderson, William P. Experimental and Numerical Results For a Generic Axisymmetric Single-Engine Afterbody with Horizontal and Vertical Tails at Transonic Speeds August 1986
- Carlson, John R. Pendergraft, Odis C. Burley, James R., II Comparison of Experimental Surface Pressures with Theoretical Predictions on Twin Two-Dimensional Convergent-Divergent Nozzles August 1986
- Capone, Francis, J. The Effects on Propulsion-induced Aerodynamic Forces of Vectoring a Partial-span Rectangular Jet at Mach Numbers from 0.40 to 1.20
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