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The first reference is the big theoretical/empirical reference for the program. The second, third, and fourth references are the three volumes of the users manual for the computer program. Notice the difference in the titles: The 4-volume paper reference is called DATCOM; the computer program is called Digital Datcom.

  1. Fink, R.: USAF Stability and Control DATCOM.. AFWAL-TR-83-3048. McDonnell Douglas Corporation, Douglas Aircraft Division, for the Flight Controls Division, Air Force Flight Dynamics Laboratory, Wright-Patterson AFB, Ohio. October 1960, revised November 1965, revised April 1978.
  2. The USAF Stability And Control Digital Datcom, Volume I, Users Manual. USAF Technical Report AFFDL-TR-79-3032 (AD A086557), April 1979.
  3. The USAF Stability And Control Digital Datcom, Volume II, Implementation of Datcom Methods. USAF Technical Report AFFDL-TR-79-3032 (AD A086558), April 1979.
  4. The USAF Stability And Control Digital Datcom, Volume III, Plot Manual. USAF Technical Report AFFDL-TR-79-3032 (AD A086559), April 1979.
  5. Pitts, William C.; Nielsen, Jack N.; and Kaattari, George E.: Lift and Center of Pressure of Wing-Body-Tail Combinations at Subsonic, Transonic, and Supersonic Speeds. NACA Report 1307, July 1953.
  6. Hopkins, Edward J.: A Semi Empirical Method for Calculating the Pitching Moment of Bodies of Revolution at Low Mach Numbers. NACA Research Memorandum A51C14, May 1951.
  7. Kaattari, George E.; Nielsen, Jack N.; and Pitts, William C.: Method for Estimating Pitching Moment Interference of Wing-Body Combinations at Supersonic Speeds. NACA Research Memorandum A52B06, April 1952.
  8. Ashley, Holt; and Landahl, Marten: Aerodynamics of Wings and Bodies. Addison Wesley, 1965 (Now available from Dover in low-cost edition).
  9. Wieselsburger, C.: Airplane Body (Non-Lifting System) Drag and Influence on Lifting System. Influence of the Airplane Body on the Wings. Vol. IV of Aerodynamics Theory, div. K, ch. III. sec. 1, W. F. Durand, ed., Julius Springer (Berlin), 1934, pp. 152-157.
  10. Hopkins, Edward J., and Carel, Hubert C.: Experimental and Theoretical Study of the Interference at Low Speed Between Slender Bodies and Triangular Wings. NACA Research Memorandum A53A14, 1953.
  11. Nielsen, Jack N., and Pitts, William C.: Wing-Body Interference at Supersonic Speeds with an Application to Combinations with Rectangular Wings. NACA Technical Note 2677, 1952.
  12. Ferrari, Carlo: Interference Between Wing and Body at Supersonic Speeds. Theory and Numerical Application. Journal of the Aeronautical Sciences, vol. 15, no. 6, June 1948, pp. 317-336.
  13. Morikawa, George K.: The Wing-Body Problem for Linearized Supersonic Flow. PhD. Thesis, Calif. Inst. of Tech., 1949.
  14. Nielsen, Jack N., Katzen, Elliott D., and Tang, Kenneth K.: Lift and Pitching-Moment Interference Between a Pointed Cylindrical Body and Triangular Wings of Various Aspect Ratios at Mach Numbers of 1.50 and 2.02. NACA Technical Note 3795, 1956. (Supersedes NACA Research Memorandum A50F06)
  15. Silverstein, Abe: Toward a Rational Method of Tail-Plane Design. Journal of the Aeronautical Sciences, vol. 6, no. 9, July 1939, pp. 361-369.
  16. Silverstein, Abe; and Katzoff, S.: Design Charts for Predicting Downwash Angles and Wake Characteristics Behind Plain and Flapped Wings. NACA Report 648, 1939.
  17. Morikawa, George: Supersonic Wing-Body-Tail Interference. Journal of the Aeronautical Sciences, vol. 19, no. 5, May 1952, pp. 333-340.
  18. Lomax, Harvard, and Byrd, Paul F.: Theoretical Aerodynamic Characteristics of a Family of Slender Wing-Tail-Body Combinations. NACA Technical Note 2554, 1951.
  19. Lagerstrom, Paco A., and Graham, Martha E.: Aerodynamic Interference in Supersonic Missiles. SM-13743, Douglas Aircraft Co., Inc., Santa Monica, July 1950.
  20. Alden, Henry L., and Schindel, Leon H.: The Calculations of Wing Lift and Moments in Nonuniform Supersonic Flows. M. I. T. Meteor Report 53, May 1950.
  21. Spreiter, John R.: The Aerodynamic Forces on Slender Plane- and Cruciform-Wing and Body Combinations. NACA Report 962, 1950. (Formerly NACA TN's 1662 and 1897)
  22. Morikawa, George: Supersonic Wing-Body Lift. Journal of the Aeronautical Sciences, vol. 18, no. 4, Apr. 1951, pp. 217-228.
  23. Allen, H. Julian, and Perkins, Edward W.: A Study of Effects of Viscosity on Flow Over Slender Inclined Bodies of Revolution. NACA Report 1048, 1951.
  24. Jones, Robert T.: Properties of Low-Aspect-Ratio Pointed Wings at Speeds Below and Above the Speed of Sound. NACA Report 835, 1946.
  25. Beskin, L.: Determination of Upwash Around a Body of Revolution at Supersonic Velocities. Report No. CM-251, Johns Hopkins Univ., Applied Physics Lab., May 27, 1946.
  26. Nielsen, Jack N.: Quasi-Cylindrical Theory of Wing-Body Interference at Supersonic Speeds and Comparison With Experiment. NACA Report 1252, 1956.
  27. Lagerstrom. Paco A., and Van Dyke, M. D.: General Considerations About Planar and Non-Planar Lifting Systems. SM-13432, Douglas Aircraft Co., Inc., Santa Monica, June 1949.
  28. Jones, Robert T.: Thin Oblique Airfoils at Supersonic Speed. NACA Report 851, 1946. (Formerly NACA TN 1107)
  29. Lagerstrom, P. A.: Linearized Supersonic Theory of Conical Wings. NACA Technical Note 1685, 1950.
  30. Heaslet, Max. A., and Spreiter, John R.: Reciprocity Relations in Aerodynamics. NACA Technical Note 2700, 1952. {not scanned yet}
  31. DeYoung, John, and Harper, Charles W.: Theoretical Symmetric Span Loading at Subsonic Speeds for Wings Having Arbitrary Plan Form. NACA Report 921, 1950.
  32. Spreiter, John R., and Sacks, Alvin: The Rolling-Up of the Trailing Vortex Sheet and Its Effect on Downwash Behind Wings. Journal of the Aeronautical Sciences, vol. 18, no. 1, Jan. 1951, pp. 21-32, 72.
  33. Rogers, Arthur W.: Application of Two-Dimensional Vortex Theory to the Prediction of Flow Fields Behind Wings of Wing-Body Combinations at Subsonic and Supersonic Speeds. NACA Technical Note 3227, 1954.
  34. Lawrence, H. R.: The Lift Distribution on Low Aspect Ratio Wings at Subsonic Speeds. Journal of the Aeronautical Sciences, vol. 18, no. 10, Oct. 1951, pp. 683-695.
  35. McDevitt,John B.: A Correlation by Means of Transonic Similarity Rules of Experimentally Determined Characteristics of a Series of Symmetrical and Cambered Wings of Rectangular Plan Form. NACA Report 1253, 1955.
  36. Dugan, Duane W., and Hikido, Katsumi: Theoretical Investigation of the Effects on Lift of a Gap Between Wing and Body of a Slender Wing-Body Combination. NACA Technical Note 3224, 1954.
  37. Johnson, Ben H., Jr., and Rollins, Francis W.: Investigation of a Thin Wing of Aspect Ratio 4 in the Ames 12-Foot Pressure Wind Tunnel. V - Static Longitudinal Stability and Control Throughout the Subsonic Speed Range of a Semispan Model of a Supersonic Airplane. NACA Research Memorandum A9I01, 1949.
  38. Cahn, Maurice S., and Bryan, Carroll R.: A Transonic-Wing Investigation in the Langley 8-Foot High-Speed Tunnel at High Subsonic Mach Numbers and at a Mach Number of 1.2. Wing-Fuselage Configuration Having a Wing of Zero Sweepback, Aspect Ratio 4.0, Taper Ratio 0.6, and NACA 65A006 Airfoil Section. NACA Research Memorandum L51A02, 1951.
  39. Weber and Kehl: Wind-Tunnel Measurements on the Henschel Missile "Zitterrochen" in Subsonic and Supersonic Velocities. NACA Technical Memorandum 1159, 1948.
  40. Anderson, Adrien E.: An Investigation at Low Speed of a Large-Scale Triangular Wing of Aspect Ratio Two. III. Characteristics of Wing With Body and Vertical Tail. NACA Research Memorandum A9H04, 1949.
  41. Polhamus, Edward C., and King, Thomas J., .Jr.: Aerodynamic Characteristics with Fixed and Free Transition of a Modified Delta Wing in Combination with a Fuselage at High Subsonic Speeds. NACA Research Memorandum L50C21, 1950.
  42. House, Rufus O., and Wallace, Arthur R.: Wind Tunnel Investigation of Effect of Interference on Lateral-Stability Characteristics of Four NACA 23012 Wings, and Elliptical and a Circular Fuselage, and Vertical Fins. NACA Report 705, 1941.
  43. McKay, James M., and Hall, Albert W.: The Effects on the Aerodynamic Characteristics of Reversing the Wing of a Triangular Wing-Body Combination at Transonic Speeds as Determined by the NACA Wing-Flow Method. NACA Research Memorandum L54H23, 1954.
  44. Hall, Albert W., and Morris, Garland J.: Aerodynamic Characteristics at a Mach Number of 1.25 of a 6-Percent-Thick Triangular Wing and 6- and 9-Percent-Thick Triangular Wings in Combination With a Fuselage. Wing Aspect Ratio 2.31. Biconvex Airfoil Sections. NACA Research Memorandum L50D05, 1950.
  45. Ellis, Macon C., Jr., and Grigsby, Carl E.: Aerodynamic Investigation at Mach Number 1.92 of a Rectangular Wing and Tail and Body Configuration and Its Components. NACA Research Memorandum L9L28a, 1950. {not scanned yet}
  46. Jaeger, B. F., and Brown, A. E.: The Aerodynamic Characteristics at Mach Number 2.0 of 14- and 18-Caliber Fin-Stabilized Rockets with Varying Body and Fin Parameters. U. S. Naval Ordnance Test Station, Inyokern, Calif., NAVORD Report 1244, Jan. 20, 1950.
  47. Stivers, Louis S., Jr., and Malick, Alexander W.: Wind-Tunnel Investigation at Mach Numbers from 0.50 to 1.29 of an All-Movable Triangular Wing of Aspect Ratio 4 Alone and with a Body. NACA Research Memorandum A9L01, 1950.
  48. Niewald, Roy J., and Moul, Martin T.: The Longitudinal Stability, Control Effectiveness, and Control Hinge-Moment Characteristics Obtained from a Flight Investigation of a Canard Missile Configuration at Transonic and Supersonic Speeds. NACA Research Memorandum L50I27, 1950.
PDAS Home > Contents > Digital Datcom > References
Public Domain Aeronautical Software (PDAS)