Analytic prediction of surface pressures over a hemisphere-cylinder at incidence

Journal of Aircraft

Volumn 40, Issue 4, 2003, Pages 645-652

  Traub, Lance W ^a   Rediniotis, Othon ^a  

^a Texas A and M University   (United States)

Author keywords

[No Author keywords available]

Indexed keywords

ATMOSPHERIC PRESSURE; CALCULATIONS; CURVE FITTING; LEAST SQUARES APPROXIMATIONS; PERTURBATION TECHNIQUES; REYNOLDS NUMBER; TURBULENT FLOW;

HEMISPHERE; SURFACE PRESSURES;

AERODYNAMICS;

EID: 0042882696     PISSN: 00218669     EISSN: 15333868     Source Type: Journal    
DOI: 10.2514/2.3168     Document Type: Article

References (15)

1. Hoang, H. T., "The Hemisphere-Cylinder at an Angle of Attack," Ph.D. Dissertation, Dept. of Engineering Mechanics, Virginia Polytechnic Inst., and State Univ., Blacksburg, VA, Dec. 1991.
2. Meade, A. J., and Schiff, L. B., "Experimental Study of Three Dimensional Separated Flow Surrounding a Hemisphere-Cylinder at Incidence," AIAA Paper 87-2492-CP, Aug. 1987.
3. Meier, H. U., and Kreplin, H. P., "Experimental Investigations of Boundary Layer Transition and Separation on a Body of Revolution," Zeitschriftfür Flugwiss Weltraumforschung, Vol. 4, 1980, pp. 65-71.
4. Ying, S. X., Schiff, L. B., and Steger, J. L., "A Numerical Study of Three Dimensional Separated Flow Past a Hemisphere Cylinder," AIAA Paper 87-1207, June 1987.
5. Schlichting, H., Boundary-Layer Theory, 7th ed., McGraw-Hill, New York, 1979, pp. 20-33.
6. Traub, L. W., "Prediction of Tunnel Wall Upwash for Delta Wings Including Vortex Breakdown Effects," The Aeronautical Journal, Vol. 103, No. 1021, 1999, pp. 139-142.
7. Traub, L. W., "Prediction of Vortex Breakdown and Longitudinal Characteristics of Swept Slender Planforms," Journal of Aircraft, Vol. 34, No. 3, 1997, pp. 353-359.
8. Traub, L. W., "Prediction of Delta Wing Leading Edge Vortex Circulation and Lift-Curve Slope," Journal of Aircraft, Vol. 34, No. 3, 1997, pp. 450-452.
9. Traub, L. W. "A Theoretical and Experimental Investigation of Biplane Delta Wings," Journal of Aircraft, Vol. 38, No. 3, 2001, pp. 536-546.
10. Landweber, L., "The Axially Symmetric Potential Flow About Elongated Bodies of Revolution," Rept. Taylor Model Basin, Washington, No. 761, March 1951.
11. Lotz, I., "Calculation of Potential Flow Past Airship Bodies in Yaw," NACA TM 675, July 1932.
12. Albone, C. M., "Fortran Programmes for Axisymmetric Potential Flow Around Closed and Semi-Infinite Bodies," Aeronautical Research Council, C.P. 1216, London, March 1972.
13. Vandrey, F., "A Method for Calculating the Pressure Distribution of a Body of Revolution Moving in a Circular Path Through a Perfect Incompressible Fluid," Aeronautical Research Council, R&M 3139, London, Dec. 1953.
14. Munk, M. M., "Airship Theory," NACA Repts. 184 and 191, 1923/24.
15. Maskell, E. C., "Flow Separation in Three Dimensions," Royal Aircraft Establishment, Rept. 2565, Nov. 1955.