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The first item is the primary reference for this program and Appendix H of this document is the users guide for creating an input file..

  1. Cunningham, Atlee M.: A Steady and Oscillatory Kernel Function Method for Interfering Surfaces in Subsonic, Transonic and Supersonic Flow. NASA Contractor Report 144895, September 1976.
  2. Watkins, Charles E.; Woolston, Donald S.; and Cunningham, Herbert J.: A Systematic Kernel Function Procedure for Determining Aerodynamic Forces on Oscillatory or Steady Finite Wings at Subsonic Speeds. NASA Technical Report R-48, June 1959.
  3. Cunningham, Herbert J.: Application of a Supersonic Kernel Function Procedure to Flutter Analysis of Thin Lifting Surfaces. NASA Technical Note D-6012, November 1970.
  4. Cunningham, Herbert J.: Computer Program for Supersonic Analysis of Thin Lifting Surfaces. NASA Technical Memorandum X-2913, April 1974.
  5. ???, J. Aircraft Nov 1974, p.197
  6. Cunningham, Herbert J.; and Desmaris, Robert N.: Generalization of the Subsonic Kernel Function in the s-Plane, with Applications to Flutter Analysis. NASA Technical Paper 2292, March 1984.
  7. Stenton, T.E.; and Andrew, L.V.: Transonic Unsteady Aerodynamics for Planar Wings with Trailing Edge Control Surfaces. AFFDL-TR-57-180, U.S. Air Force, Aug. 1968.
  8. Magnus, R.; and Yoshihara, H.: Inviscid Transonic Flow Over Airfoils. AIAA Journal, vol. 8, no. 12, Dec. 1970, pp. 2157-2162.
  9. Murman, E.; and Cole, J.: Calculation of Transonic Flows. AIAA Journal, vol. 9, no. 1, Jan. 1971, pp. 121-141.
  10. Bailey, F.R.; and Steger, J.L.: Relaxation Techniques for Three-Dimensional Transonic Flow About Wings. AIAA Paper No. 72-189, Jan. 1972.
  11. Magnus, R.; and Yoshihara, H.: Finite Difference Calculations of the NACA 64A-410 Airfoil Oscillating Sinusoidally in Pitch at Mach 0.72. CASD-NSC-74-004, Office of Naval Research, Aug. 1974.
  12. Cunningham, A.M., Jr.: The Application of General Aerodynamic Lifting Surface Elements to Problems in Unsteady Transonic Flow. NASA Contractor Report 112264, Feb. 1973.
  13. Cunningham, A.M., Jr.: A Collocation Method for Predicting Oscillatory Subsonic Pressure Distributions on Interfering Parallel Lifting Surfaces. AIAA Paper No. 71-329, Apr. 1971.
  14. Cohen, D.: Formulas for the Supersonic Loading, Lift and Drag of Flat Swept-Back Wings with Leading Edges Behind the Mach Lines. NACA Report 1050, 1951.
  15. Ii, J.M.; Borland, C.J.; and Hogley, J.R.: Prediction of Unsteady Aerodynamic Loadings of Non-Planar Wings and Wing-Tail Configurations in Supersonic Flow, Part 1 - Theoretical Development, Program Usage and Application. AFFDL-TDR-71-108, U.S. Air Force, March 1972.
  16. Woodward, F.A.; and Hague, D.S.: A Computer Program for the Aerodynamic Analysis and Design of Wing-Body-Tail Combinations at Subsonic and Supersonic Speeds, Volume I: Theory and Program Utilization. ERR-FW-867, Fort Worth Division of General Dynamics, Feb. 1969.
  17. Landrum, E.J.: A Tabulation of Wind-Tunnel Pressure Data and Section Aerodynamic Characteristics at Mach Numbers 1.61 and 2.01 for Two Trapezoidal Wings and Three Delta Wings Having Different Surface Shapes. NASA Technical Note D-1344, Sept. 1962. [NOTE: This paper seems to have been withdrawn from the NASA report file. Aug. 2010]
  18. Landahl, M.T.: Unsteady Transonic Flow. Pergamon Press, New York, Oxford, London, Paris, 1961.
  19. Lessing, Henry C.; Troutman, John L.; and Menees, Gene P.: Experimental Determination of the Pressure Distribution on a Rectangular Wing Oscillating in the First Bending Mode for Mach Numbers from 0.24 to 1.30. NASA Technical Note D-344, Dec. 1960.
  20. Becker, J.: Vergleich gemessener and berechneter instationärer Druckverteilungen für den hohen Unterschall an einem elastischen gepfeilten Flugel. EWR-Report Nr. 403-69, Messerschmitt-Bölkow-Blohm, Sept. 1969.
  21. Tijdeman, H.: Correspondence to S. R. Bland on Corrections to Experimental Data published by NLR, (Amsterdam). Sept. 1973.
  22. Bergh, H.; Tidjeman, H.; and Zwaan, R.J.: High Subsonic and Transonic Effects on Pressure Distributions Measured for a Swept Wing with Oscillating Control Surfaces. Z. Flugwiss., 18 (1970), Heft 9/10, pp. 339-347 (in English).
  23. Laschka, B.; and Schmid, H.: Unsteady Aerodynamic Forces on Coplanar Lifting Surfaces in Subsonic Flow (Wing-Horizontal Tail Interference). Jahrbuch 1967 der WGLR, pp. 211-222 (in English).
  24. Multhopp, H.: Methods for Calculating the Lift Distribution of Wings, (Appendix I, Contributed by W. Mangler). Report No. Aero-2353, Royal Aircraft Establishment, Farnborough, Hants, Jan. 1950. Superceded by R & M 2884, 1955.
  25. Pai, S.: Introduction to the Theory of Compressible Flow. D. Van Nostrand Company, Inc., Princeton, Toronto, New York, London, 1959.
  26. Anon.: Tables of Chebyshev Polynomials Sn(x) and Cn(x), (Introduction by Cornelius Lanczos). Applied Mathematics Series, 9, National Bureau of Standards, 1952.
  27. Harder, R.L.; and Desmarias, R.N.: Interpolation Using Surface Splines. Journal of Aircraft, Vol. 9, No. 2, Feb. 1972, pp. 189-191.

Note that there are two distinct researchers named Cunningham working in this field. This program is from the 1976 report by Atlee Cunningham.

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