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The first three documents are the primary references.

  1. Gentry, Arvel E.; Smyth, Douglas N.; and Oliver, Wayne R.: The Mark IV Supersonic-Hypersonic Arbitrary-Body Program. Volume I - Users Manual. AFFDL-TR-73-159, volume I, USAF Flight Dynamics Laboratory. November 1973.
  2. Gentry, Arvel E.; Smyth, Douglas N.; and Oliver, Wayne R.: The Mark IV Supersonic-Hypersonic Arbitrary-Body Program. Volume II - Program Formulation. AFFDL-TR-73-159, volume II, USAF Flight Dynamics Laboratory. November 1973.
  3. Gentry, Arvel E.; Smyth, Douglas N.; and Oliver, Wayne R.: The Mark IV Supersonic-Hypersonic Arbitrary-Body Program. Volume III - Program Listing. AFFDL-TR-73-159, volume III, USAF Flight Dynamics Laboratory. November 1973.
  4. Gentry, A.E.; and Smyth, D.N.: Hypersonic Arbitrary-Body Aerodynamic Computer Program, Mark III Version, Volume I, User's Manual, Volume II, Program Formulation and Listing, Douglas Report DAC 61552, April 1968.
  5. Gentry, A.E.: Hypersonic Arbitrary-Body Aerodynanic Computer Program (Mark II), Volume I, User's Manual and Volume II, Program Formulation and Listing, Douglas Report No. DAC 56080, March 1967.
  6. Ames Research Staff: Equations, Tables, and Charts for Compressible Flow, NACA Report 1135, 1953.
  7. Bertram, M.H.; and Henderson, A., Jr.: Recent Hypersonic Studies of Wings and Bodies, American Rocket Society Journal, Volume 31, No. 8, August 1961.
  8. Bertram, M.H.; and Blackstock, T.A.: Some Simple Solutions to the Problem of Predicting Boundary-Layer Self-Induced Pressures, NASA TN D-798, April 1961.
  9. Bertram, M.H.: Hypersonic Laminar Viscous Interaction Effects on the Aerodynamics of Two-Dimensional Wedge and Triangular Planform Wings, NASA TN D-3523, August 1966.
  10. Bradley, R.C.; and Miller, B.D.: Lifting Surface Theory Advances and Applications, AIAA Paper No. 70-192, 8th Aerospace Sciences Meeting, New York, January 19-21, 1970.
  11. Bromley, L.A.; and Wilke, C.R.: Viscosity at Low Temperatures, University of California TR HE-150-157.
  12. Carmichael, R.L.: A Critical Evaluation of Methods for Computing Wing-Body Interference at Supersonic Speeds, ICAS Paper No. 68-08, Sixth Congress of the ICAS, Munich, Germany, September 9-13, 1968.
  13. Collingbourne, J.R.: An Empirical Prediction Method for the Non-Linear Normal Force on Thin Wings at Supersonic Speeds, Aeronautical Research Council CP-662, Great Britain, 1963.
  14. Collingborne, J.R.; Crabtree, L.F.; and Bartlett, W.J.: A Semi-Empirical Prediction Method for Pressures on the Windward Surface of Circular Cones at Incidence at High Supersonic and Hypersonic Speeds (M>=3), Aeronautical Research Council, C.P. No.792, January 1964.
  15. Cohen, C.B., and Reshotko, E., The Compressible Laminar Boundary Layer with Heat Transfer and Arbitrary Pressure Gradient, NACA Report 1294, 1956.
  16. Coons, S.A.: Surfaces for Computer-Aided Design of Space Figures, Massachusetts Institute of Technology Preprint No. 299.
  17. Eckert, E.R.G.: Survey on Heat Transfer at High Speeds, WADC TR 54-70, April 1954.
  18. Eggers, A.J.; and Syvertson, C.A.: Inviscid Flow about Airfoils at High Supersonic Speeds, NACA TN 2646, March 1952.
  19. Eggers, A.J., Jr.; Syvertson, C.A., and Kraus, S.: A Study of Inviscid Flow About Airfoils at High Supersonic Speeds, NACA Report 1123, 1953.
  20. Eggers, A.J., Jr.; and Savin, R.C.: A Unified Two-Dimensional Approach to the Calculation of Three-Dimensional Hypersonic Flows, with Application to Bodies of Revolution, NACA Report 1249, 1955.
  21. Epstein, P.S.: On the Air Resistance of Projectiles, Proc. National Academy Sci. U.S.A., Vol. 17, pages 552-547, 1931.
  22. Fetterman, D.E.: A Method for Predicting the Normal Force Characteristics of Delta Wings at Angles of Attack from 0° to 90°, NASA TM X-757, March 1963.
  23. Goldberg, L.: The Structure of the Viscous Hypersonic Shock Layer, General Electric Report R65SD50, December 1965.
  24. Goldberg, L.: Forces and Moments on the Front Face of a Blunt Lifting Reentry Vehicle, General Electric Report R66SD21, April 1966.
  25. Grabau, M.: A Method of Forming Continuous Empirical Equations for the Thermodynamic Properties of Air From Ambient Temperatures to 15,000°K, with Applications, AEDC-TN-59-102, August 1959.
  26. Granville, P.S.: The Calculation of the Viscous Drag of Bodies of Revolution, Report 849, David Taylor Model Basin, July, 1953.
  27. Gregorek, G.M.; Nark, T.C.; and Lee, J.D.: An Experimental Investigation of the Surface Pressure and Laminar Boundary Layer on a Blunt Flat Plate in Hypersonic Flow, Vol.I, ASD-TDR-62-792, March 1963.
  28. Griffith, B.J.: Comparison of Data from the Gemini Flights and AEDC-VKF Wind Tunnels, AEDC-TR-66-178, October 1966.
  29. Hammitt, A.G.; and Murthy, K.R.: Approximate Solutions for Supersonic Flow Over Wedges and Cones, Journal of the Aeronautical Sciences, January 1960, pp. 71-73.
  30. Hankey, W.L., Jr.: Optimization of Lifting Re-Entry Vehicles, ASD-TDR-62-1102, March 1963.
  31. Hansen, C.F.: Approximations for the Thermodynamic and Transport Properties of High Temperature Air, NACA TN-4150, 1958.
  32. Harder, R.L.; and Desmarais, R.N.: Interpolation Using Surface Splines, Journal of Aircraft, Volume 9, No. 2, February 1972, pp. 189-191.
  33. Hayes, W.D.; and Probstein, R.F.: Hypersonic Flow Theory, Volume I, Inviscid Flows, Second Edition (1966), Academic Press, New York.
  34. Hayes, W.D.; and Probstein, R.F.: Hypersonic Flow Theory, Vol. 5, Academic Press, 1959.
  35. Hayes, W.D.; and Probstein, L.F.: Hypersonic Flow Theory, Academic Press, 1959.
  36. Henderson, A., Jr.; and Braswell, D.O.: Charts for Conical and Two Dimensional Oblique Shock Flow Parameters in Helium at Mach Numbers From About 1 to 100, NASA TN D-819, Jun,: 1961,
  37. Hess, J.L.; and Riddell, T.M.: Direct Solutions of a Square Matrix Whose Size Greatly Exceeds High-Speed Storage, McDonnell Douglas Report DAC 70000, July 1969.
  38. Hess, J.L.; and Smith, A.M.O.: Calculation of Non-Lifting Potential Flow About Arbitrary Three-Dimensional Bodies, Douglas Report No. ES 40622, March 1962.
  39. Hilsenrath, J.; and Klein, M.: Tables of Thermodynamic Properties of Air in Chemical Equilibrium Including Second Virial Corrections from 1500°K to 15,000°K, AEDC-TR-65-58, March 1965.
  40. Inouye, M.; Rakich, J.V.; and Lomax, H.: A Description of Numerical Methods and Computer Programs for Two-Dimensional and Axisymmetric Supersonic Flow Over Blunt-Nosed and Flared Bodies, NASA TN D-2970, August 1965.
  41. Jackson, C.M.; and Smith, R.S.: A Method for Determining the Total Drag of a Pointed Body of Revolution in Supersonic Flow With Turbulent Boundary Layer, NASA TN D-5046, March 1969.
  42. Jackson, C.M.; and Sawyer, W.C.: A Method for Calculating the Aerodynamic Loading on Wing-Body Combinations at Small Angles of Attack in Supersonic Flow, NASA TN D-6441, October 1971.
  43. Jernell, L.S.: Comparisons of Theoretical and Experimental Pressure Distributions Over a Wing-Body Model at High Supersonic Speeds, NASA TN D-6480, September 1971.
  44. Jones, D.J.: Tables of Inviscid Supersonic Flow About Circular Cones at Incidence, gamma=1.4, AGARDograph 137, November 1969.
  45. Jones, D.J.: A Pressure Formula for an Inclined Circular Cone in Supersonic Flow, gamma = 1.4, AIAA Journal, February 1972, pp.234-236.
  46. Kaufman, L.G., II: Pressure Estimation Techniques for Hypersonic Flows Over Blunt Bodies, Journal of Astronautical Sciences, Volume X, No. 2, Summer 1963.
  47. Kaups, K.; and Keltner, G.: Laminar Compressible Boundary Layer on a Yawed Infinite Wing, Douglas Deport No. LB 32706, March 1967.
  48. Kaattari, G.E.: Estimation of Directional Stability Derivatives at Moderate Angles and Supersonic Speeds, NASA Memo 12-1-58A.
  49. Kaufman, L.G.,II.: Pressure Estimation Techniques for Hypersonic Flows over Blunt Bodies, Journal of the Astronautical Sciences, Volume X, No. 2, Summer 1963.
  50. Korn, G.A.; and Korn, T.M.: Mathematical Handbook for Scientists and Engineers, McGraw-Hill, April 1961.
  51. Lee, J.D.: Pressures on the Blunt Plate Wing at Supersonic and Hypersonic Speeds, FDL-TDR-64-102, July 1964.
  52. Lees, L.: Hypersonic Flow, Fifth International Aeronautical Conference Proceedings, June 1955.
  53. Levis, C.H.; and Burgess, E.G., III: Empirical Equations for Thermodynamic Properties of Air and Nitrogen to 15,000°K, AEDC-TDR-63-138, July 1963.
  54. Liepmann, H.W.; and Roshko, A.: Elements of Gasdynamics, John Wiley and Sons, Inc., 1957.
  55. Love, E.S.: Generalized Newtonian Theory, Journal of Aerospace Sciences (Readers Forum), Vol. 26, No. 5, May 1959, pages 314-315.
  56. Love, E.S.; Henderson, A., Jr.; and Bertram, M.H.: Some Aspects of the Air-Helium Simulation and Hypersonic Approximations, NASA TN D-49, October 1959.
  57. Lukasiewicz, J.: Hypersonic Flow-Blast Analogy, AEDC-TR-61-4, June 1961.
  58. McLellan, C.H.; Bertram, M.H.; and Moore, J.A.: An Investigation of Four Wings of Square Planform at a Mach Number of 6.86 in the Langley 11-inch Hypersonic Tunnel, NACA Research Memorandum L51 D17, June 1951.
  59. McNally, W.D., FORTRAN Program for Calculating Compressible Laminar and Turbulent Boundary Layers in Arbitrary Pressure Gradients, NASA TN D-5681, May 1970.
  60. Michel, R.; and Kretzschmar, G.: Determination Theorique D'une Enthalpie de Reference Pour la Couche Limite Laminiaire de la Plaque Plane, Influence due Nombre de Prandtl, O.N.E.R.A. Report T.P. No. 41, 1963.
  61. Monaghan, R.J.: An Approximate Solution of the Compressible Laminar Boundary Layer on a Flat Plate, British R & M No 2760, 1953.
  62. Neal, L., Jr.: Average Pressure and Skin Friction on Tapered Plates Hypersonic Flow, J. Spacecraft, Volume 3, No. 6, June 1966, pp. 945-946.
  63. Roberts, M.L.: Newtonian Aerodynamic Coefficients for and Arbitrary -Body, Including "All Shadowed" Areas, J. Spacecraft, Volume 7, No. 9, September 1970.
  64. Sasman, P.K.; and Cresci, R.J.: Compressible Turbulent Boundary Layer with Pressure Gradient and Heat Transfer, AIAA Journal, Volume 4, No. 1, January 1966, pp.19-25.
  65. Savin, R.C.: Application of the Generalized Shock-Expansion Method to Inclined Bodies of Revolution Traveling at High Supersonic Speeds, NACA TN 3349, April 1955.
  66. Schlichting, H., Boundary Layer Theory. Sixth Ed., McGraw-Hill Book Company, Inc., 1968.
  67. Schlichting, H., and Ulrich, A., Zur Berechnung des Umschlages Laminar-Turbulent, Jahrbuch d. dt. Luftfahrtforschung, No. 1. 1942, --. 8-35.
  68. Schwartz, L.W.: Comment on 'An Empirical Expression for Drag Coefficients of Cones at Supersonic Speeds', AIAA Journal, March 1969, pp. 572-573.
  69. Seiff, A.: Secondary Flow Fields Embedded in Hypersonic Shock Layers, NASA TN D-1304, May 1962.
  70. Seiff, A.; and Whiting, E.E.: Calculation of Flow Fields from Bow Wave Profiles for the Downstream Region of Blunt Nosed Circular Cylinders in Axial Hypersonic Flight, NASA TN D-1147, 1961.
  71. Shapiro, A.H.: The Dynamics and Thermodynamics of Compressible Fluid Flow, The Ronald Press, 1953.
  72. Sieron, T.R.; and Martinez, C., Jr.: Effects and Analysis of Mach Number and Reynolds Number on Laminar Skin Friction at Hypersonic Speeds, AFFDL-TR-65-5, April 1965.
  73. Sivells, J.C.; and Payne, R.G.: A Method of Calculating Turbulent-Boundary-Layer Growth at Hypersonic Mach Numbers, AEDC-TR-59-3, March 1959.
  74. Spalding, D.B.; and Chi, S.W.: The Drag of a Compressible Turbulent Boundary Layer on a Smooth Flat Plate With and Without Heat Transfer, J. Fluid Mechanics, Volume 18, Part 1, January 1964, pp. 117-143.
  75. Syvertson, C.A., and Dennis, D.H.: A Second-Order Shock-Expansion Method Applicable to Bodies of Revolution Near Zero Lift, NACA Report 1328, 1957.
  76. Van Dyke, M.D.: Second-Order Slender-Body Theory - Axisymmetric Flow, NASA TR R-47, 1959.
  77. Van Dyke, M.D.: A Study of Hypersonic Small-Disturbance Theory, NACA Report 1194, l954.
  78. Van Tassell, W.: Free-Molecular and Newtonian Coefficients for Arbitrary Bodies, RAD-TM-63-63, August 1963.
  79. White, F.M., Jr.: Hypersonic Laminar Viscous Interactions of Inclined Flat Plates, American Rocket Society Journal, May 1962.
  80. Witcofski, R.D.; and Marcum, D.C., Jr.: Effect of Thickness and Sweep Angle on the Longitudinal Aerodynamic Characteristics of Slab Delta Planforms at a Mach Number of 20, NASA TN D-3459, June 1966.
  81. Woodward, F.A., A Unified Approach to the Analysis and Design of Wing-Body Combinations at Subsonic and Supersonic Speeds, AIAA Paper No. 68-55, January 22-24, 1968.
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