R.T. Jones, “Estimated Lift-Drag Ratios at Supersonic Speeds,” NACA TN 1350, 1947.
C.F. Hall, “Lift, Drag, and Pitching Moment of Low Aspect Ratio Wings at Subsonic and Supersonic Speeds,” NACA RM A53A30, 1953. This is the original NACA conical camber derivation with the equations of the shape. It includes wind tunnel data for several wings.
J.W. Boyd, E. Migotsky, and B.E. Wetzel, “A Study of Conical Camber for Triangular and Sweptback Wings,” NACA RM A55G19, Nov. 1955. This report repeats the geometric definition with some typos fixed. The equations are fairly complicated. Wind tunnel results are presented for a number of wings.
S.H. Tsien, “The Supersonic Conical Wing of Minimum Drag,” JAS, Vol. 23, No. 12, Dec. 1955, pp. 805-817. This is a theoretical study independent of the NACA work. Rich Pelz generated an input data set for use in COREL and did a study when he was a summer student at Grumman before his senior year at Virginia Tech.
E.R. Phelps and J.W. Boyd, “A Wind-Tunnel Investigation of the Effects of Conical Camber for an Airplane Configuration Having a Triangular Wing of Aspect Ratio 2.2,” NACA RM A57A10, April 1957. This report has data for a number of wings tested on an F-106 model at NACA Ames. The conical camber used was a simplification of the full NACA conical camber geometry described above. A comparison of the cambers is given. The report contains tab data for the forces and moments at both sub- and supersonic Mach numbers.
W.H. Mason and D.S. Miller, “Controlled Supercritical Crossflow on Supersonic Wings - An Experimental Validation,” AIAA Paper No. 80-1421, July 1980.
D.S. Miller, E.J. Landrum, J.C. Townsend, and W.H. Mason, “Pressure and Force Data for a Flat Wing and a Warped Conical Wing Having a Shockless Recompression at Mach 1.62,” NASA TP 1759, April 1981.
W.H. Mason, D.S. Miller, J.L. Pittman, and M.J. Siclari, “A Supersonic Maneuver Wing Designed for Nonlinear Attached Flow,” AIAA Paper No. 83-0425, January 1983.
W.H. Mason, “SC3 - A Wing Concept for Supersonic Maneuvering,” AIAA Paper No. 83-1858, July 1983.
W.H. Mason, “A Wing Concept for Supersonic Maneuvering,” NASA CR 3763, December 1983.
J.L. Pittman, D.S. Miller, and W.H. Mason, “Fuselage and Canard Effects on an Attached Flow, Maneuver Wing at Mach 1.62,” NASA TP 2249, February 1984.
J.L. Pittman, D.S. Miller, and W.H. Mason, “Supersonic, Nonlinear, Attached-Flow Wing Design for High Lift with Experimental Validation,” NASA TP 2336, August 1984.
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direct comments and suggestions to W.H. Mason, whmason@vt.edu