Abstract
The intent in this chapter is to present some of the methods and techniques being used in the aerospace industry to determine the flow field around a blunt body moving at hypersonic speed. In this context, attention is given primarily to presenting the more significant results obtained in recent years, and, where possible, experimental results are compared with theoretical predictions. Before discussing these methods and results, however, it is worthwhile to view the role that flow-field analysis plays in the design of a hypersonic vehicle.
Access this chapter
Tax calculation will be finalised at checkout
Purchases are for personal use only
Preview
Unable to display preview. Download preview PDF.
References
S. A. Schaff, “Mechanics of Rarefied Gases,” NAVORD Report 1488, Vol. 5 (February 1959).
R. F. Probstein and N. H. Kemp, “Viscous Aerodynamic Characteristics in Hypersonic Rarefied Gas Flow,” Avco, Report RR48 (December 1959).
W. D. Hayes, and R. F. Probstein, Hypersonic Flow Theory: Vol. I, Inviscid Flows, Academic Press, New York (1966).
M. D. Van Dyke, “The Supersonic Blunt-Body Problem—Review and Extension,” Aerospace Sci. 25 (8), 485–496 (August 1958).
H. Lomax, and M. Inouye, “Numerical Analysis of Flow Properties about Blunt Bodies Moving at Supersonic Speeds in an Equilibrium Gas,” NASA TR R-204 (July 1964).
P. Garabedian and H. Lieberstein, “On the Numerical Calculation of Detached Bow Shock Waves in Hypersonic Flow,” J. Aerospace Sci. 25 (8), 109–118 (1968).
H. G. Webb, Jr., H. S. Dresser, B. K. Adler, and S. A. Waiter, “Inverse Solution of Blunt-Body Flow Fields at Large Angle of Attack, ” AIAA J. 5 (6), 1079–1085 (June 1967).
W. W. Joss, “Application of the Inverse Technique to the Flow over a Blunt Body at Angle of Attack,” NASA CR-445 (April 1966).
R. Swigart, “Hypersonic Blunt-Body Flow Fields at Angle of Attack,” AIAA J. 2 (1), 115–117 (1964).
G. E. Kaatari, “Shock Envelopes of Blunt Bodies at Large Angle of Attack,” NASA TN D-1980 (December 1963).
W. D. Hayes, “Rotational Stagnation-Point Flow,” J. Fluid Mech., 19, Part 3, 366–374 (1964).
O. M. Belotserkovskii, “Flow with a Detached Shock Wave about a Symmetrical Profile,” Prikl. Matern, i Mekhan. 22(2), 206–219 (1958); translated in Appl. Math. Mech. 1958, pp. 279–296.
G. Waldman, “Integral Approach to the Yawed Blunt-Body Problem,” AIAA Paper No. 65-28 presented at AIAA 2nd Aerospace Sciences Meeting, New York, 1965.
F. G. Gravalos, I. H. Edelfelt, and H. W. Emmons, “The Supersonic Flow about a Blunt Body of Revolution for Gases at Chemical Equilibrium,” in: Proceedings of the Ninth International Astronomical Congress, Vol. 1, Springer-Verlag, Berlin (1959).
S. H. Maslen, and W. E. Moeckel, “Inviscid Hypersonic Flow Past Blunt Bodies,” Aeron. Sci., 24 (9), 683–693 (1957).
H. G. Webb, Jr., and D. M. Schrello, “Final Report: Flow-Field Prediction and Analysis for Project RAM—Phase II,” Space Division, North American Rockwell Corporation, SID 64 - 548 (July 1964).
I. O. Bohachevsky, and R. E. Mates, “A Direct Method for Calculation of the Flow about an Axisymmetric Blunt Body at Angle of Attack,” AIAA J., 4 (5), 776–782 (1966).
L. Fox, “Numerical Solutions of Ordinary and Partial Differential Equations,” Pergamon Press, New York (1962).
G. Moretti, and M. Abett, “A Time-Dependent Computational Method for Blunt- Body Flows,” AIAA J. 4 (2), 2136–2141 (December 1966).
H. G. Webb, Jr. and H. S. Dresser, “Unsteady Flow over Axisymmetric Blunt Bodies at Zero Angle of Attack,” Space Division, North American Rockwell Corporation, SD 67 - 881 (September 1967).
P. D. Lax, “Weak Solutions of Nonlinear Hyperbolic Equations and Their Numerical Computations,” Commun. Pure Appl. Math., 7, 159–193 (1954).
P. D. Lax, and B. Wendroff, “Systems of Conservation Laws,” Commun. Pure Appl. Math. 13, 217–237 (1960).
R. D. Richtmyer, Difference Methods for Initial-Value Problems, Interscience, New York (1957).
G. Moretti, and G. Bleich, “Three-Dimensional Flow around Blunt Bodies,” AIAA Paper No. 67-222 presented at AIAA 5th Aerospace Sciences Meeting, New York, January 23–26, 1966.
A. D. Wood, J. F. Springfield, and A. J. Pallone, “Chemical and Vibrational Relaxation of an Inviscid Hypersonic Flow,” AIAA J. 2 (10), 1697–1705 (October 1964).
B. T. Chu, “Wave Propagation and the Method of Characteristics in Reacting Gas Mixtures with Application to Hypersonic Flow,” Wright Air Development Center, TN-57-213, ASTIA Doc. AD 118350 (May 1957).
C. W. Chu, A. F. Niemann, Jr., and S. A. Powers, “An Inviscid Analysis of the Plume Created by Multiple Rocket Engines and a Comparison with Available Schlieren Data—Part I: Calculation of Multiple Rocket Engine Exhaust Plumes by the Method of Characteristics,” AIAA Paper No. 66-651 presented at AIAA Second Propulsion Joint Specialist Conference, Colorado Springs, Colorado, June 13–17, 1966.
J. V. Rakich, “Three-Dimensional Flow Calculation by the Method of Characteristics,” AIAA J. 5 (10), 1906–1908 (October 1967).
E. C. Knox, and C. H. Lewis, “A Comparison of Experimental and Theoretically Predicted Pressure Distributions and Force and Stability Coefficients for a Spherically Blunted Cone at M∞ ≈ 18 and Angles of Attack,” ARO Inc., AEDC-TR-65-234 (February 1966).
S. V. Patankar, “Heat and Mass Transfer in Turbulent Boundary Layers,” PhD thesis, Imperial College of Science and Technology, University of London (June 1967).
J. Valensi, R. Michel, and D. Guffroy, “Résultats Expérimentaux et Théoriques sur le Transfert de Chaleur au Bord d’Attaque des Ailes à Forte Flèche en Hypersonique,” AG ARD Report No. 97 (May 1965).
H. Schlichting, Boundary-Layer Theory, 6th ed., McGraw-Hill Book Co., New York (1968).
C. R. Cohen, and E. Reshotko, “Similar Solutions for the Compressible Laminar Boundary Layer with Heat Transfer and Pressure Gradient,” NACA TR 1293 (1956).
G. L. Mellor, “Incompressible Turbulent Boundary-Layer Equations with Arbitrary Pressure Gradients and Divergent or Convergent Cross Flows,” AIAA J. 5 (9), 1570–1579 (September 1967).
S. A. Waiter, and L. P. LeBlanc, “Solution of the Boundary-Layer Equation by an Implicit Variable-Step-Size Finite-Difference Technique,” Space Division, North American Rockwell Corporation, SD 68 - 635 (1968).
S. A. Waiter, and R. B. Anderson, “Solution of the Laminar Boundary-Layer Equations by an Implicit Finite-Difference Technique,” Space Division, North American Rockwell Corporation, SD 67 - 587 (September 1967).
A. Roshko, and G. J. Thomke, “Correlation for Incipient-Separation Pressure,” McDonnell Douglas Corporation, Report DAC-59800 (May 1966).
Z. Popinski, and C. F. Ehrlich, “Development Design Methods for Predicting Hypersonic Aerodynamic Control Characteristics,” Lockheed California Company, Technical Report AFFDL-TR-66-85 (1966).
W. L. Hankey, “Prediction of Incipient Separation in Shock-Boundary-Layer Separation,” AIAA J. 5 (2), 355–356 (February 1967).
D. A. Needham, “A Note of Hypersonic Incipient Separation,” AIAA J. 5 (12), 2284–2285 (December 1967).
D. R. Chapman, D. M. Kuehn, and H. K. Larson, “Investigation of Separated Flows in Supersonic and Subsonic Streams with Emphasis on the Effect of Transition,” NACA Report 1356 (1958).
G. E. Gadd, D. W. Holder, and J. D. Regan, “An Experimental Investigation of the Interaction between Shock Waves and Boundary Layers,” Proc. Royal Soc. (London) Ser. A 226, 227–253 (1954).
S. M. Bogdonoff, and C. E. Kepler, “Separation of a Supersonic Turbulent Boundary Layer,” Department of Aeronautical Engineering, Princeton University, Report 249 (January 1954).
L. P. LeBlanc and H. G. Webb, Jr., “Boundary-Layer Separation in a Supersonic Stream,” Space Division, North American Rockwell Corporation, SID 61–72 (1961).
J. G. Lewis, T. Kubota, and L. Lees, “Experimental Investigation of Supersonic Laminar, Two-Dimensional Boundary-Layer Separation in a Compressible Corner with and without Cooling,” AIAA J. 6 (1), 7–14 (January 1968).
N. Curie, “The Effects of Heat Transfer on Laminar Boundary-Layer Separation in Supersonic Flow,” Aero. Quart. 12 Part 4, 309–336 (1961).
E. E. Zukowski, “Turbulent Boundary-Layer Separation in front of a Forward-Facing Step,” AIAA J. 5 (10), 1746–1753 (October 1967).
L. Lees and B. L. Reeves, Supersonic Separated and Reattaching Laminar Flows: I—General Theory and Application to Adiabatic Boundary Layer Shock-Wave Interactions, AIAA J. 2 (11), 1907–1920 (1964).
D. R-S. Ko and T. Kubota, “Supersonic Laminar Boundary Layer along a Two-Dimensional Adiabatic Curved Ramp,” AIAA Paper 68-105 presented at 6th Aerospace Sciences Meeting, New York, 22–24 January 1968.
M. R. Dennison and E. Baum, “Compressible Free Shear Layer with Finite Initial Thickness,” AIAA J. 1 (2), 342–349 (February 1963).
D. R. Chapman, “Laminar Mixing of a Compressible Fluid,” NACA Report 958 (1950).
T. Kubota and C. F. Dewey, Jr., “Momentum Integral Methods for the Laminar Free Shear Layer,” AIAA J. 2 (4), 625–629 (April 1964).
B. L. Reeves and L. Lees, “Theory of the Laminar Near Wake of Blunt Bodies in Hypersonic Flow,” AIAA J. 3 (11), 2061–2074 (1965).
W. H. Webb, R. J. Golik, F. W. Vogenitz, and L. Lees, “A Multimoment Integral Theory for the Laminar Supersonic Near Wake,” Proceedings of the 1965 Heat Transfer and Fluid Mechanics Institute, Stanford University Press, Stanford, California (1965).
J. Grange, J. M. Klineberg, and L. Lees, “Laminar Boundary-Layer Separation and Near-Wake Flow for a Smooth Blunt Body at Supersonic and Hypersonic Speeds,” AIAA J. 5 (6), 1089–1097 (June 1967).
J. F. McCarthy, Jr., “Hypersonic Wakes,” California Institute of Technology, GALCIT Hypersonic Research Project, Memo 67 (1962).
J. F. McCarthy, Jr. and T. Kubota, “A Study of Wakes behind a Circular Cylinder at M = 5.7, ” AIAA J. 2 (4), 629–636 (April 1964).
T. Kubota, “Laminar Wake with Streamwise Pressure Gradient,” California Institute of Technology, GALCIT Hypersonic Research Project, Memo No. 9 (May 1962).
W. Behrens, “The Far Wake behind Cylinders at Hypersonic Speeds: I, Flowfield,” AIAA J. 5 (12), 2135–2141 (1967).
W. Behrens, “The Far Wake behind Cylinders at Hypersonic Speeds: II, Stability,” AIAA J., 6 (2), 225–232 (February 1968).
W. G. Clay, M. Labitt, and R. E. Slattery, “Measured Transition from Laminar to Turbulent Flow and Subsequent Growth of Turbulent Wakes,” AIAA J. 3 (5), 837–841 (May 1965).
L. N. Wilson, “Far-Wake Behavior of Hypersonic Spheres,” AIAA J. 5 (7), 1238–1244 (July 1967).
L. Lees, and L. Hromas, “Turbulent Diffusion in the Wake of a Blunt-Nosed Body at Hyprsonic Speeds,” J. Aerospace Sci., 29, 976 (1962).
R. Knystautas, “Growth of the Turbulent Inner Wake behind 3-in. Diameter Spheres,” AIAA J. 2 (8), 1485–1486 (1964).
Author information
Authors and Affiliations
Editor information
Editors and Affiliations
Rights and permissions
Copyright information
© 1969 Plenum Press, New York
About this chapter
Cite this chapter
McCarthy, J.F. (1969). Hypersonic Blunt-Body Gas Dynamics. In: Loh, W.H.T. (eds) Modern Developments in Gas Dynamics. Springer, Boston, MA. https://doi.org/10.1007/978-1-4615-8624-1_5
Download citation
DOI: https://doi.org/10.1007/978-1-4615-8624-1_5
Publisher Name: Springer, Boston, MA
Print ISBN: 978-1-4615-8626-5
Online ISBN: 978-1-4615-8624-1
eBook Packages: Springer Book Archive