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Wing-body interference at supersonic speeds with an application to combinations with rectangular wings

Description: Report presenting the development of an exact theoretical method that permits the determination of the pressure field of a wing-body combination with a circular body and a wing with supersonic leading and trailing edges. Detailed calculations were performed for wing-body combinations composed of rectangular wings mounted at incidence on bodies at zero angle of attack for effective chord-radius ratios of 4 or less.
Date: April 1952
Creator: Nielsen, Jack N. & Pitts, William C.
Partner: UNT Libraries Government Documents Department

Comparison between prediction and experiment for all-movable wing and body combinations at supersonic speeds: Lift, pitching moment, and hinge moment

Description: From Summary: "A simple method is presented for estimating lift, pitching-moment, and hinge-moment characteristics of all-movable wings in the presence of a body as well as the characteristics of wing-body combinations employing such wings. In general, good agreement between the method and experiment was obtained for the lift and pitching moment of the entire wing-body combination and for the lift of the wing in the presence of the body. The method is valid for moderate angles of attack, wing deflection angles, and width of gap between wing and body."
Date: August 8, 1952
Creator: Nielsen, Jack N.; Kaattari, George E. & Drake, William C.
Partner: UNT Libraries Government Documents Department

The Interference Effects of a Body on the Spanwise Load Distributions of Two 45 Degree Sweptback Wings of Aspect Ratio 8.02 from Low-Speed Tests

Description: From Summary: "Tests of two wing-body combinations have been conducted in the Langley 19-foot pressure tunnel at a Reynolds number of 4 x 10(exp 6) and a Mach number of 0.19 to determine the effects of the bodies on the wing span load distributions. The wings had 45 degrees sweepback of the quarter-chord line, aspect ratio 8.02, taper ratio 0.45, and incorporated 12-percent-thick airfoil sections streamwise. One wing was untwisted and uncambered whereas the second wing incorporated both twist and camber. Identical bodies of revolution, of 10:1 fineness ratio, having diameter-to-span ratios of 0.10, were mounted in mid-high-wing arrangements."
Date: April 1956
Creator: Martina, Albert P.
Partner: UNT Libraries Government Documents Department

A transonic wind-tunnel investigation of the effects of body indentation, as specified by the transonic drag-rise rule, on the aerodynamic characteristics and flow phenomena of an unswept-wing-body combination

Description: Report presenting comparisons of the aerodynamic characteristics and flow phenomena at transonic speeds for two unswept zero-taper-ratio wing-body combinations. The first had a cylindrical afterbody, while the second had an indented afterbody in the region of the wing-body juncture. Results regarding force characteristics, flow surveys, and an interpretation of the results are provided.
Date: January 28, 1953
Creator: Williams, Claude V.
Partner: UNT Libraries Government Documents Department

A pressure-distribution investigation of the aerodynamic characteristics of a body of revolution in the vicinity of a reflection plane at Mach numbers of 1.41 and 2.01

Description: The changes in the aerodynamic characteristics of a body of revolution with a fineness ratio of 8 have been determined at Mach numbers of 1.41 and 2.01, a Reynolds number, based on body length, of 4.54 x 10 to the 6th power, and angles of incidence of 0 degrees and plus or minus 3 degrees as the position of the body is varied with respect to a reflection plane. The data are compared with theoretical results.
Date: January 20, 1955
Creator: Gapcynski, John P. & Carlson, Harry W.
Partner: UNT Libraries Government Documents Department

A study of the zero-lift drag-rise characteristics of wing-body combinations near the speed of sound

Description: Comparisons of the shock phenomena and drag-rise increments for representative wing and central-body combinations with those for bodies of revolution with the same axial distributions of cross-sectional area normal to the air stream. An investigation was also presented of representative wing-body combinations with the body so indented that the axial distributions of cross-sectional areas for the combinations were the same as that for the original body. Results regarding unswept wing and cylindrical body, delta wing and cylindrical body, swept wing and cylindrical body, swept wing and curved body, and applications of the transonic drag-rise concept are provided.
Date: September 3, 1952
Creator: Whitcomb, Richard T.
Partner: UNT Libraries Government Documents Department

Lift, drag, and pitching moment of low-aspect-ratio wings at subsonic and supersonic speeds : plane triangular wing of aspect ratio 2 with NACA 0008-63 section

Description: Report presenting an investigation of a wing-body combination with a plane triangular wing of aspect ratio 2 and NACA 0008-63 sections in streamwise planes at subsonic and supersonic Mach numbers. Lift, drag, and pitching moment are presented for a range of Mach and Reynolds numbers.
Date: February 1, 1951
Creator: Smith, Donald W. & Heitmeyer, John C.
Partner: UNT Libraries Government Documents Department

An experimental investigation of two methods for reducing transonic drag of swept-wing and body combinations

Description: Report presenting an investigation of a wing swept back 35 degrees in combination with one basic body and three modified bodies at a range of Mach numbers from 0.60 to 1.20. Results regarding force studies and pressure studies are provided. The bodies modified according to the Kuchenmann ring-vortex method resulted in superior aerodynamic characteristics except with regard to zero-lift drag at high supersonic Mach numbers.
Date: April 29, 1955
Creator: McDevitt, John B.
Partner: UNT Libraries Government Documents Department

Lift, drag, and pitching moment of low-aspect-ratio wings at subsonic and supersonic speeds: twisted and cambered triangular wing of aspect ratio 2 with NACA 0003-63 thickness distribution

Description: This report presents the results of an investigation to ascertain the lift, drag, and pitching moment of a wing-body combination having a triangular wing of aspect ratio 2 with NACA 0003-63 thickness distribution in streamwise planes and twisted and cambered for a nearly elliptical span load distribution. Results are shown for Mach numbers from 0.60 to 0.90 and from 1.30 to 1.70 at Reynolds numbers of 3.0 million and 7.5 million.
Date: June 12, 1951
Creator: Hall, Charles F. & Heitmeyer, John C.
Partner: UNT Libraries Government Documents Department

Aerodynamic study of a wing-fuselage combination employing a wing swept back 63 degrees: effect of Reynolds number at supersonic Mach numbers on the longitudinal characteristics of a wing twisted and cambered for uniform load

Description: Report presenting a wind-tunnel investigation of the longitudinal characteristics of a wing-body combination with a wing with leading edge swept back 63 degrees. Lift, drag, and pitching-moment measurements were made over a range of Mach and Reynolds numbers. Results regarding the general characteristics and effect of Reynolds number are provided.
Date: October 9, 1950
Creator: Heitmeyer, John C.
Partner: UNT Libraries Government Documents Department

Lift, drag, and pitching moment of low-aspect-ratio wings at subsonic and supersonic speeds : plane triangular wing of aspect ratio 2 with NACA 0005-63 section

Description: Report presenting a wing-body combination with a plane triangular wing of aspect ratio 2 and NACA 0005-63 sections in streamwise planes has been investigated at subsonic and supersonic Mach numbers. Lift, drag, and pitching moment are presented for a range of Mach and Reynolds numbers.
Date: February 1, 1951
Creator: Smith, Donald W. & Heitmeyer, John C.
Partner: UNT Libraries Government Documents Department

Lift, drag and pitching moment of low-aspect-ratio wings at subsonic and supersonic speeds: Plane tapered wing of aspect ratio 3.1 with 3-percent-thick rounded-nose section

Description: Report presenting a wing-body combination with a plane tapered wing of aspect ratio 3.1, taper ratio of 0.39, and 3-percent-thick, rounded-nose sections in streamwise planes at subsonic and supersonic Mach numbers. The lift, drag, and pitching moment are presented for a range of Mach numbers and Reynolds numbers.
Date: July 9, 1952
Creator: Heitmeyer, John C.
Partner: UNT Libraries Government Documents Department

Lift, drag, and pitching moment of low-aspect-ratio wings at subsonic and supersonic speeds: Plane triangular wing of aspect ratio 2 with NACA 0003-63 section

Description: Report presenting testing of a wing-body combination with a plane triangular wing of aspect ratio 2 and NACA 0003-63 sections in streamwise planes at subsonic and supersonic Mach numbers. Lift, drag, and pitching moment are presented for a range of Mach and Reynolds numbers.
Date: February 2, 1951
Creator: Heitmeyer, John C. & Smith, Willard G.
Partner: UNT Libraries Government Documents Department

Lift, drag, and pitching moment of low-aspect-ratio wings at subsonic and supersonic speeds: Twisted and cambered triangular wing of aspect ratio 2 with NACA 0005-63 thickness distribution

Description: Report presenting the results of a wind-tunnel investigation at subsonic and supersonic Mach numbers to determine the aerodynamic characteristics of a wing-body combination with a triangular wing of aspect ratio 2. The mean surface of the wing was twisted and cambered to support a nearly elliptical span load distribution at Mach number 1.53 and a lift coefficient of 0.25. Lift, drag, and pitching moment are presented for a range of Mach and Reynolds numbers.
Date: April 10, 1952
Creator: Heitmeyer, John C. & Petersen, Robert B.
Partner: UNT Libraries Government Documents Department

Lift, drag, and pitching moment of low-aspect-ratio wings at subsonic and supersonic speeds: Plane triangular wing of aspect ratio 4 with 3-percent-thick rounded nose section

Description: Report presenting an investigation of a wing-body combination with a plane triangular wing of aspect ratio 4 and 3-percent-thick rounded nose sections in streamwise planes at subsonic and supersonic Mach numbers. Lift, drag, and pitching moment are presented for a range of Mach and Reynolds numbers.
Date: August 29, 1951
Creator: Heitmeyer, John C. & Hightower, Ronald C.
Partner: UNT Libraries Government Documents Department

Lift, drag, and pitching moment of low-aspect-ratio wings at subsonic and supersonic speeds : plane triangular wing of aspect ratio 3 with NACA 0003-63 section

Description: Report presenting a wing-body combination with a plane triangular wing of aspect ratio 3 and NACA 0003-63 sections in streamwise planes at subsonic and supersonic Mach numbers. Lift, drag, and pitching moment are presented for a range of Mach and Reynolds numbers.
Date: September 13, 1951
Creator: Heitmeyer, John C.
Partner: UNT Libraries Government Documents Department

Lift, drag, and pitching moment of low-aspect-ratio wings at subsonic and supersonic speeds: Plane triangular wing of aspect ratio 4 with 3-percent-thick, biconvex section

Description: Report presenting a wing-body combination with a plane triangular wing of aspect ratio 4 and 3-percent-thick, biconvex sections in streamwise planes at subsonic and supersonic Mach numbers. Lift, drag, and pitching moment are presented for a range of Mach and Reynolds numbers.
Date: June 8, 1951
Creator: Heitmeyer, John C.
Partner: UNT Libraries Government Documents Department

A transonic wind-tunnel investigation of the longitudinal force and moment characteristics of a plane and a cambered 3-percent-thick delta wing of aspect ratio 3 on a slender body

Description: Report presenting an investigation of the effects of leading-edge camber without twist on an aspect-ratio-3 delta wing of thickness ratio 3, a body with an ogive nose, and a cylindrical afterbody. Results regarding the base pressures and body characteristics and wing-body combinations are provided.
Date: November 15, 1954
Creator: Burrows, Dale L. & Palmer, William E.
Partner: UNT Libraries Government Documents Department

Lift, drag and pitching moment of low-aspect-ratio wings at subsonic and supersonic speeds: comparison of three wings of aspect ratio 2 of rectangular, swept-back and triangular plan form, including effects of thickness distribution

Description: Report presenting the aerodynamic characteristics of three wing-body combinations with wings of aspect ratio 2 and rectangular, swept-back, and triangular plan form and a comparison at subsonic and supersonic speeds. All three wings had 3-percent-thick airfoil sections and were investigated with biconvex and rounded-nose airfoil sections. Results regarding the effects of wing plan form, effects of airfoil-section thickness distribution, and effects of Reynolds number are provided.
Date: February 16, 1953
Creator: Hightower, Ronald C.
Partner: UNT Libraries Government Documents Department

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 0 degrees sweepback, aspect ratio 4.0,taper ratio 0.6, and NACA 65A006 ai

Description: Report presenting an analysis of a series of wing-body combinations in the 8-foot high-speed tunnel. The paper presents the results of an investigation of a wing-fuselage combination with a wing of unswept quarter-chord line, aspect ratio 4, taper ratio 0.6, and an NACA 65A006 airfoil section. Results regarding force and moment characteristics and wake and downwash characteristics are provided.
Date: March 6, 1951
Creator: Cahn, Maurice S. & Bryan, Carroll R.
Partner: UNT Libraries Government Documents Department

Effects of fixing transition on the transonic aerodynamic characteristics of a wing-body configuration at Reynolds numbers from 2.4 to 12 million

Description: Report presenting a wind-tunnel investigation of the effects of fixing boundary-layer transition with wires on the aerodynamic characteristics of a wing-body configuration at a range of Mach numbers. The model consisted of an aspect-ratio-3 trapezoidal wing with a 3-percent-thick biconvex section in combination with a Sears-Haack body of revolution. Results regarding lift characteristics, pitching-moment characteristics, and drag characteristics are provided.
Date: July 1958
Creator: Hunton, Lynn W.
Partner: UNT Libraries Government Documents Department

On the Mutual Reaction of Wings and Body

Description: "At the suggestion of Professor Von Karman, I have made a few theoretical investigations of the mutual reaction of the wings and body of an airplane. There was assumed as the basis of my calculations, a strongly idealized body shape, namely, a cylinder extended to infinity at both ends and having its axis parallel to the direction of motion of the airplane. The results are to be regarded as rough approximations for a long airplane body and also for an airship with fins. In my calculations, I have considered only a monoplane in which the axis of the wing is rectilinear" (p. 1).
Date: February 1927
Creator: Lennertz, J.
Partner: UNT Libraries Government Documents Department

A Method for Estimating the Components of Lift of Wing-Body Combinations at Supersonic Speeds

Description: Report presenting the lift of wing-body combinations at supersonic speeds as obtained by means of an approximate linearized-theory analysis involving an assumption concerning the geometry of the body. A comparison with several groups of data is provided to show the accuracy of the method.
Date: September 16, 1952
Creator: Tucker, Warren A.
Partner: UNT Libraries Government Documents Department

Additional Experiments With Flat-Top Wing- Body Combinations at High Supersonic Speeds

Description: Memorandum presenting an experimental study of the effects of several variations in configuration geometry on the aerodynamic characteristics of flat-top wing-body combinations. Generally, the configurations consist of one half of a body of revolution mounted beneath a wing of essentially arrow plan form. Results regarding the effect of trailing-edge sweep, effect of the addition of auxiliary bodies, effect of tip-flap deflection, effect of dihedral, effect of leading-edge sweep, effect of fuselage fineness ratio, effect of fuselage profile shape, and static longitudinal stability characteristics are provided.
Date: February 19, 1957
Creator: Syvertson, Clarence A.; Wong, Thomas J. & Gloria, Hermilo R.
Partner: UNT Libraries Government Documents Department