The effects of winglets on low aspect ratio wings at supersonic Mach numbers. M.S. Thesis Report Feb. 1989 - Apr. 1991

A computational study was conducted on two wings, of aspect ratios 1.244 and 1.865, each having 65 degree leading edge sweep angles, to determine the effects of nonplanar winglets at supersonic Mach numbers. A Mach number of 1.62 was selected as the design value. The winglets studied were parametrically varied in alignment, length, sweep, camber, thickness, and dihedral angle to determine which geometry had the best predicted performance. For the computational analysis, an available Euler marching technique was used. The results indicated that the possibility existed for wing-winglet geometries to equal the performance of wing-alone bodies in supersonic flows with both bodies having the same semispan. The first wing with winglet used NACA 1402 airfoils for the base wing and was shown to have lift-to-pressure drag ratios within 0.136 percent to 0.360 percent of the NACA 1402 wing-alone. The other base wing was a natural flow wing which was previously designed specifically for a Mach number of 1.62. The results obtained showed that the natural wing-alone had a slightly higher lift-to-pressure drag than the natural wing with winglets.

[1]  Bernard Etkin,et al.  Dynamics of flight , 1959 .

[2]  C. W. Boppe.  Transonic Flow Field Analysis for Wing-Fuselage Configurations , 1980 .

[3]  Harry H. Heyson,et al.  Theoretical parametric study of the relative advantages of winglets and wing-tip extensions , 1977 .

[4]  S. G. Flechner,et al.  A high subsonic speed wind tunnel investigation of winglets on a representative second-generation jet transport wing , 1976 .

[5]  Richard T. Whitcomb,et al.  A design approach and selected wind tunnel results at high subsonic speeds for wing-tip mounted winglets , 1976 .

[6]  P. Sweby.  High Resolution Schemes Using Flux Limiters for Hyperbolic Conservation Laws , 1984 .

[7]  C. Angelopoulos.  High resolution schemes for hyperbolic conservation laws , 1992 .

[8]  John M. Kuhlman,et al.  Winglets on low-aspect-ratio wings , 1987 .

[9]  K. Asai.  Theoretical considerations in the aerodynamic effectiveness of winglets , 1985 .

[10]  S. F. Davis,et al.  A simplified TVD finite difference sheme via artificial viscousity , 1987 .

[11]  Richard M. Wood,et al.  A natural flow wing design employing 3-D nonlinear analysis applied at supersonic speeds , 1989 .

[12]  W. J. Monta,et al.  Description and calibration of the Langley unitary plan wind tunnel , 1981 .

[13]  B. McGrath,et al.  Euler code evaluation of a conical vehicle at supersonic speeds , 1989 .

[14]  Steven X. S. Bauer,et al.  Evaluation of a three-dimensional empirically derived wing at supersonic speeds , 1988 .