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Computation of Cantilever Airplane Wings

Description: The purpose of this treatise is, first of all, the determination of the effect of variously loaded spars on one another, since the neglect of this effect would present an economically very unfavorable computation method. The system of spars and cross-bars alone (whether solid or built-up) does not matter at first, the original assumption being that the spars are rigidly braced by the cross-bars.
Date: July 1925
Creator: Thalau, K.
Partner: UNT Libraries Government Documents Department

Comparison of low-lift drag at Mach numbers from 0.74 to 1.37 of rocket-boosted models having externally braced wings and cantilever wings

Description: Report presenting an investigation to determine whether the low-lift drag of a rocket-model airplane-like configuration could be reduced at transonic and low supersonic Mach numbers by reducing wing thickness while external braces were used to provide the necessary bending strength. The investigation was conducted with two rocket models of aspect ratio 3.04, and unswept braced tapered wings mounted on fuselages with the same fineness ratios and cross-sectional area distributions. Data was compared to a previous study involving a model with a thicker cantilever wing.
Date: September 25, 1957
Creator: Dickens, Waldo L. & Hastings, Earl C., Jr.
Partner: UNT Libraries Government Documents Department

Flight tests at supersonic speeds to determine the effect of taper on the zero-lift drag of sweptback low-aspect-ratio wings

Description: Report presenting testing using rocket-powered models to provide an experimental comparison with linearized theoretical calculations for zero-lift drag of sweptback tapered wings with thin, symmetrical, double-wedge airfoil sections. The theory compared favorably with experimental results over most of the test range. Taper was generally found to increase wing drag at low supersonic speeds but reduced drag at higher speeds.
Date: September 5, 1950
Creator: Pittel, Murray
Partner: UNT Libraries Government Documents Department

Flow around wings accompanied by separation of vortices

Description: The flow around wings computed by the usual method leads in the case of a finite trailing edge to a stagnation point in the trailing edge due to the Kutta-Joukowsky condition of flow governing this region. As a result, the theoretical pressure distribution differs substantially from the experimental values in the vicinity of the trailing edge. The present report describes an alternative method of calculation in which the rear stagnation point no longer appears. The stream leaves the trailing edge tangentially on the pressure side and a similar tangential separation occurs on the suction side of the profile at a point slightly in front of the trailing edge.
Date: December 1940
Creator: Schmieden, C.
Partner: UNT Libraries Government Documents Department

Wind-tunnel investigation of ailerons on a low-drag airfoil 1: The effect of aileron profile

Description: Report presenting an investigation in the 7- by 10-foot wind tunnel of the effects of various modifications to the profile of a 0.20-chord plain sealed aileron and a 0.15-chord plain sealed aileron on an NACA 66,2-216 airfoil. Thickening of the aileron was found to reduce the aileron effectiveness, reduce the slope of the wing section lift curve, and reduce the hinge-moment coefficients. Results regarding the section data, aileron effectiveness, aileron hinge moments, lift, pitching moment, drag, and Reynolds number are provided.
Date: January 1944
Creator: Crane, Robert M. & Holtzclaw, Ralph W.
Partner: UNT Libraries Government Documents Department

Effects of the spanwise, chordwise and vertical location of an external store on the aerodynamic characteristics of a 60 degree delta wing at Mach numbers of 1.41, 1.62, and 1.96

Description: Report presenting an investigation in the supersonic blowdown tunnel to determine the effects of external store location on the lift, drag, and pitching-moment characteristics of a 60 degree delta wing at Mach numbers of 1.41, 1.62, and 1.96. Brief comparative tests were also made to determine the effect of changing the sweep of the strut attaching the store to the wing and of changing the chordwise location of the swept strut.
Date: October 27, 1952
Creator: Jacobsen, Carl R.
Partner: UNT Libraries Government Documents Department

Control characteristics of trailing-edge spoilers on untapered blunt trailing-edge wings of aspect ratio 2.7 with 0 degree and 45 degrees sweepback at Mach numbers of 1.41 and 1.96

Description: Report presenting an investigation in the supersonic blowdown tunnel to determine the control characteristics of full-span trailing-edge spoilers on two related full-blunt wings with the same aspect ratio but differing angles of sweepback. A similar unswept wing that was larger and had a partially blunt trailing edge was also tested with a full-span trailing-edge spoiler. Results regarding the lift, rolling-moment, and pitching-moment coefficients for unswept wings, the 45-degree sweptback wing, and a comparison of spoiler data with flap data are provided.
Date: December 3, 1952
Creator: Jacobsen, Carl R.
Partner: UNT Libraries Government Documents Department

Tests of two models representing intermediate inboard and outboard wing sections of the XB-36 airplane

Description: Report presenting testing in the two-dimensional low-turbulence pressure tunnel and the two-dimensional low-turbulence tunnel of two models made by the Consolidated Aircraft Corporation, one of the outboard section and one of the inboard section.
Date: January 1943
Creator: Bogdonoff, Seymour M.
Partner: UNT Libraries Government Documents Department

High-speed aerodynamic characteristics of a lateral-control model 3: section characteristics, fence studies, and tabulated pressure coefficients with modified NACA 0012-64 section, 26.6-percent-chord, plain aileron, 0 and 45 degree sweepback

Description: Report presenting wind-tunnel measurements of the pressure distribution on a semispan wing with a modified NACA 0012-64 airfoil section and a plain trailing-edge aileron with the wing unswept and also swept back 45 degrees. Adverse changes in loading and loss of aileron effectiveness developed with the wing unswept as the Mach number was increased, but did not occur at Mach numbers up to 0.925 with the swept wing. Results regarding section characteristics and effect of fences are provided.
Date: November 22, 1950
Creator: Krumm, Walter J. & Cleary, Joseph W.
Partner: UNT Libraries Government Documents Department

An investigation of four wings of square plan form at a Mach number of 6.86 in the Langley 11-inch hypersonic tunnel

Description: Report presenting the results of pressure-distribution and force tests on four wings at Mach number 6.86 and Reynolds number 980,000 in the 11-inch hypersonic tunnel. Characteristics of the wings tested included a 4-inch square plan form, a 5-percent maximum thickness, and diamond, half-diamond, wedge, and half-circular-arc sections. Information about pressure measurements, wing characteristics, and Schlieren photographs is provided.
Date: June 29, 1951
Creator: McLellan, Charles H.; Bertram, Mitchel H. & Moore, John A.
Partner: UNT Libraries Government Documents Department

Interference of multiplane wings having elliptical lift distribution

Description: In calculating the self-induction of a wing surface, elliptical lift distribution is assumed, while in calculating the mutual induction or interference of two wing surfaces, a uniform distribution of the lift along the wing has hitherto been assumed. Whether the results of these calculations are substantially altered by assuming an elliptical lift distribution (which is just as probable as uniform distribution) is examined here.
Date: February 1924
Creator: von Sanden, H.
Partner: UNT Libraries Government Documents Department

Investigation of interference lift, drag, and pitching moment of a series of triangular wing and body combinations at a Mach number of 1.62

Description: Report presenting an investigation at Mach number 1.62 of a series of triangular wing and body combinations to determine the interference lift, drag, and pitching moment. Testing was conducted on seven flat-plate triangular wings of varying scale, four with a half-apex angle of 30 degrees and three with a half-apex angle of 45 degrees. Results regarding wing alone, wing in the presence of the body, basic quantities for interference evaluation, interference quantities, and contributions of both types of quantities are provided.
Date: May 27, 1955
Creator: Coletti, Donard E.
Partner: UNT Libraries Government Documents Department

The transonic characteristics of a low-aspect-ratio triangular wing with a constant-chord flap as determined by wing-flow tests, including correlation with large-scale tests

Description: Report presenting wing-flow-method measurements for 0.47 to 1.15 Mach number of the longitudinal-stability and -control characteristics of a triangular wing of aspect ratio 2 equipped with a constant-chord flap. Changes in the lift-curve slope and aerodynamic-center position through the transonic speed range were moderate and gradual. Results regarding triangular-wing characteristics, flap characteristics, and a comparison of the wind-tunnel and free-flight-test results at higher Reynolds numbers are provided.
Date: August 18, 1950
Creator: Rathert, George A., Jr.; Rolls, L. Stewart & Hanson, Carl M.
Partner: UNT Libraries Government Documents Department

Exploratory investigation of leading-edge chord-extensions to improve the longitudinal stability characteristics of two 52 degree sweptback wings

Description: Report presenting exploratory testing obtained with leading-edge wing chord-extensions on two 52 degree sweptback wings. The wings had the same aspect ratio but different airfoil sections. Results regarding force characteristics and flow characteristics are provided.
Date: March 10, 1950
Creator: Furlong, G. Chester
Partner: UNT Libraries Government Documents Department

Influence of wing flexibility on force-time relation in shock strut following vertical landing impact

Description: Report presenting testing to determine the force developed in a shock strut as a function of the flexibility of the attached wing structure. Both the experiment and analysis indicated that wing flexibility had some effect on the shape and peak value of the force-time curve in a shock strut.
Date: November 1949
Creator: McPherson, Albert E.; Evans, J., Jr. & Levy, Samuel
Partner: UNT Libraries Government Documents Department

The effects of scale and test technique on the validity of small-scale measurements of the aerodynamic characteristics of a wing with the leading edge swept back 63 degrees

Description: Report presenting the lift and pitching-moment characteristics of two wings of the same plan form measured over a range of Mach and Reynolds numbers using the wing-flow method. One wing had a symmetrical airfoil section and no twist, while the other was cambered and twisted to support a uniform load distribution at a lift coefficient of 0.25 at Mach number 1.5. A comparison with previous testing is also provided.
Date: December 9, 1949
Creator: Rolls, L. Stewart
Partner: UNT Libraries Government Documents Department

Investigation to determine effects of center-of-gravity location on the transonic flutter characteristics of a 45 degree sweptback wing

Description: Report presenting an experimental investigation in the transonic blowdown tunnel to determine effects of center-of-gravity location on the transonic flutter characteristics of a 45 degree sweptback-wing plan form of aspect ratio 4.0 and taper ratio 0.6. Solid-construction models with streamwise NACA 65A004 airfoil sections and center-of-gravity locations at three different chords were fluttered at a range of Mach numbers.
Date: February 20, 1956
Creator: Jones, George W., Jr. & Unangst, John R.
Partner: UNT Libraries Government Documents Department

Investigation of wing-tip ailerons on a 51.3 degrees sweptback wing at transonic speeds by the transonic-bump method

Description: Report presenting an investigation to determine the aerodynamic characteristics of deflectable wing-tip ailerons on a sweptback wing in the Langley high-speed tunnel by means of the transonic bump technique. Three ailerons were investigated, one with a basic wing-plan form and two with an extended-tip plan form. Results regarding the longitudinal aerodynamic characteristics, rolling-moment data, control effectiveness, and lift effectiveness are provided.
Date: November 26, 1951
Creator: Moseley, William C., Jr. & Watson, James M.
Partner: UNT Libraries Government Documents Department

Drag interference between a pointed cylindrical body and triangular wings of various aspect ratios at Mach numbers of 1.50 and 2.02

Description: The drag of a body alone, six triangular wings of various aspect ratios, and the combinations were measured at Mach numbers of 1.50 and 2.02 at a Reynolds number of 5.5 million (based on the body length). The experimental drag-interference results were in accordance with calculations based on NACA RM A9E19, 1949, with skin-friction effects taken into account, the interference effect being principally the result of fixing transition on the body by adding a wing.
Date: November 1956
Creator: Katzen, Elliott D. & Kaattari, George E.
Partner: UNT Libraries Government Documents Department

Drag interference between a pointed cylindrical body and triangular wings of various aspect ratios at Mach numbers of 1.50 and 2.02

Description: The drag of a body alone, six triangular wings of various aspect ratios, and the combinations were measured at Mach numbers of 1.50 and 2.02 at a Reynolds number of 5.5 million (based on the body length). The experimental drag-interference results were in accordance with calculations based on NACA RM A9E19, 1949, with skin-friction effects taken into account, the interference effect being principally the result of fixing transition on the body by adding a wing.
Date: May 23, 1951
Creator: Katzen, Elliott D. & Kaattari, George E.
Partner: UNT Libraries Government Documents Department

Method for calculating the rolling and yawing moments due to rolling for unswept wings with or without flaps or ailerons by use of nonlinear section lift data

Description: From Summary: "The methods of NACA reports 865 and 1090 have been applied to the calculation of the rolling-moment and yawing-moment coefficients due to rolling for unswept wings with or without flaps or ailerons. The methods are based on lifting-line theory and allow the use of nonlinear section lift data. The method presented in this report permits calculations to be made somewhat beyond maximum lift for wings having no twist or continuous twist and employing airfoil sections which do not display large discontinuities in the lift curves. Calculations can be made up to maximum lift for wings with discontinuous twist such as that produced by partial-span flaps or ailerons, or both. Two calculated examples are presented in simplified computing forms in order to illustrate the procedures involved."
Date: January 29, 1953
Creator: Martina, Albert P.
Partner: UNT Libraries Government Documents Department

Pressure distributions on triangular and rectangular wings to high angles of attack Mach numbers 1.45 and 1.97

Description: Pressure distributions were measured over rectangular wings of aspect ratio 2 and triangular wings of aspect ratios 2 and 4 at Mach numbers of 1.45 and 1.97. The investigation includes some comparison of the effects of Reynolds number and of thickening the wing root sections on the loading.
Date: June 25, 1954
Creator: Kaattari, George E.
Partner: UNT Libraries Government Documents Department

Pressure distributions on triangular and rectangular wings to high angles of attack Mach numbers 2.46 and 3.36

Description: Pressure distributions were measured over rectangular wings of aspect ratio 2 and triangular wings of aspect ratios 2 and 4 at Mach numbers of 2.46 and 3.36. The investigation includes some comparison of the effects of Mach number, Reynolds number, and thickening the wing root sections on the loading.
Date: January 18, 1955
Creator: Kaattari, George E.
Partner: UNT Libraries Government Documents Department