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A General Three-Dimensional Potential-Flow Method Applied to V/STOL Aerodynamics
ISSN: 0148-7191, e-ISSN: 2688-3627
Published February 01, 1968 by SAE International in United States
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This paper describes a numerical method for solving three-dimensional incompressible flow problems and its use in predicting the aerodynamic characteristics of V/STOL aircraft. Arbitrary configuration and inlet geometry, fan inflow distributions, thrust vectoring, jet entrainment, angles of yaw, and flight speeds from hover through transition can be treated. Potential-flow solutions are obtained with the method of influence coefficients, using source and doublet panels distributed on the boundary surfaces. The results include pressure distributions, lift, induced drag and side force, and moments. Theoretical solutions are presented for clean lifting wings and for a NASA fan-in-wing model. Comparisons with the experimental NASA data demonstrate the validity of the approach and uncover the importance of viscous effects, fan inflow distribution, and jet entrainment.
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CitationRubbert, P. and Saaris, G., "A General Three-Dimensional Potential-Flow Method Applied to V/STOL Aerodynamics," SAE Technical Paper 680304, 1968, https://doi.org/10.4271/680304.
- Rubbert P. E., “Theoretical Characteristics of Arbitrary Wings by a Non-Planar Vortex Lattice Method.” The Boeing Co., Document D6-9244, Feb. 5, 1964.
- Monical R. E, “A Method of Representing Fan-Wing Combinations for Three-Dimensional Potential Flow Solutions.” Paper No. 65-85 presented at AIAA Third Aerospace Sciences Meeting, New York, January 1965.
- Kroeger R. A, “The Streamline Matching Technique for V/STOL Wind-Tunnel Wall Corrections.” Paper No. 67-183 presented at AIAA Fifth Aerospace Sciences Meeting, New York, January 1967.
- Hess J. L. and Smith A. M. O., “Calculation of Non-Lifting Potential Flow About Arbitrary Three-Dimensional Bodies.” Douglas Aircraft Co., Report No. E. S. 40622, 1962.
- Hickey D. H. and HallL. P., “Aerodynamic Characteristics of a Large-Scale Model with Two High Disk-Loading Fans Mounted in the Wings.” NASA TN D-1650, February 1963.
- Heyson H., “Wind-Tunnel Wall Effects at Extreme Force Coefficients.” International Congress of Subsonic Aerodynamics, sponsored by New York Academy of Sciences, New York, April 1967.
- Lamb H., “Hydrodynamics.” New York: Dover Publishing Co., 1945.
- Rubbert P. E., SaarisG. R., Scholey M. B., Standen N. M. and Wallace R. E., “A General Method for Determining the Aerodynamic Characteristics of Fan-in-Wing Configurations.” Vol. 1 -- Theory and Application. USAAVLABS Technical Report 67-61A, 1967.
- Davenport F., “Singularity Solutions to General Potential Flow Airfoil Problems.” NASA Document N66-38134, 1966.
- Jones R. T. and Cohen D., “High Speed Wing Theory.” Princeton Aeronautical Paperback No. 6, Princeton University Press, 1960.
- Hink G. R., Gilbert R. F., and Sundstrom K. A., “A General Method for Determining the Aerodynamic Characteristics of Fan-in-Wing Configurations.” Vol. 2 -- Computer Program Description. USAAVLABS Technical Report 67-61B, 1967.