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Effects of independent variations of mach number and reynolds number on the maximum lift coefficients of four NACA 6-series airfoil sections

Description: Report presenting an investigation in the low-turbulence pressure tunnel to determine the effects of Mach and Reynolds number on the maximum lift characteristics of the NACA 65-006, 64-009, 64-210, and 64(sub 2)-215 airfoil sections in smooth and leading-edge roughness conditions. A range of Mach and Reynolds numbers were explored.
Date: November 1952
Creator: Racisz, Stanley F.
Partner: UNT Libraries Government Documents Department

The effect of rate of change of angle of attack on the maximum lift of a small model

Description: Report presenting a wind-tunnel investigation of a partial model of a conventional fighter airplane to determine the effects of rate of change of angle of attack on its maximum lift. The results indicated that the maximum lift coefficient increased linearly with pitching velocity up to a limit value of the lift coefficient which depended on the Mach number.
Date: March 1950
Creator: Harper, Paul W. & Flanigan, Roy E.
Partner: UNT Libraries Government Documents Department

Effects of sweep on the maximum-lift characteristics of four aspect-ratio-4 wings at transonic speeds

Description: Report presenting an investigation at transonic speeds in the high-speed 7- by 10-foot tunnel to determine the effect of wing sweep on the maximum-lift characteristics of a series of wings having aspect ratio of 4, taper ratio of 0.6, and NACA 65A006 airfoil sections. Testing occurred over a range of Mach and Reynolds numbers. Results regarding lift, drag, and pitching-moment characteristics are provided.
Date: July 1955
Creator: Turner, Thomas R.
Partner: UNT Libraries Government Documents Department

Two-Dimensional Wind-Tunnel Investigation of Modified NACA 65(sub 112)-111 Airfoil with 35-Percent-Chord Slotted Flap at Reynolds Numbers up to 25 Million

Description: From Summary: "An investigation has been made in the Langley two-dimensional low-turbulence tunnels to develop the optimum configuration of a .035-chord slotted flap on an NACA 65(sub(112)-111 airfoil section modified by removing the trailing-edge cusp. Included in the investigation were measurements to determine the scale effects on the section lift and drag characteristics of the airfoil with the flap retracted for Reynolds numbers ranging from 3.0 X 10(exp 6) to 2.5 X 10(exp 6). The scale effects on the lift characteristics were also determined for the same Reynolds numbers for the flap deflected in the rotation found to be optimum at a Reynolds number of 9.0 X 10(exp 6)."
Date: January 20, 1947
Creator: Racisz, Stanley F.
Partner: UNT Libraries Government Documents Department

Characteristics throughout the subsonic speed range of a plane wing and of a cambered and twisted wing, both having 45 degrees of sweepback

Description: Report presenting a wind-tunnel investigation of two semispan wing models with 45 degrees of sweepback, an aspect ratio of 5, and a taper ratio of 0.565. One wing had no camber or twist while the other was cambered for a design lift coefficient of 0.4 and twisted to relieve loading at the tip. Results regarding the plane wing, cambered and twisted wing, wing-body combinations, effect of camber and twist, effect of fences, effect of surface roughness, and lift-drag ratio are provided.
Date: July 12, 1951
Creator: Johnson, Ben H., Jr. & Shibata, Harry H.
Partner: UNT Libraries Government Documents Department

An investigation of the subsonic speed range of a full-span and a semispan model of a plane wing and of a cambered and twisted wing, all having 45 degrees of sweepback

Description: Report presenting a wind-tunnel investigation of two full-span and two semispan models with 45 degrees of sweepback, an aspect ratio of 5.5, and a taper ratio of 0.53. The lift and drag data obtained from tests of the semispan agreed well with data obtained on the full-span model. Results regarding a comparison of the data for the full-span and semispan models, full-span model data, and effect of surface roughness are provided.
Date: June 26, 1952
Creator: Shibata, Harry H.; Bandettini, Angelo & Cleary, Joseph
Partner: UNT Libraries Government Documents Department

Investigation of the downwash and wake behind a triangular wing of aspect ratio 4 at subsonic and supersonic Mach numbers

Description: Report presenting the effects of Mach number between 0.50 and 0.95 and between 1.09 and 1.29 on the characteristics of the downwash and on the location of the wake behind a triangular wing of aspect ratio 4 as determined from semispan model tests.
Date: December 12, 1950
Creator: Walker, Harold J. & Stivers, Louis S., Jr.
Partner: UNT Libraries Government Documents Department

Hydrodynamic tares and interference effects for a 12-percent-thick surface-piercing strut and an aspect-ratio-0.25 lifting surface

Description: Report presenting an investigation to determine the hydrodynamic tares and interference effects on lift, drag, and pitching moment for an NACA 66(sub 1)-012 airfoil-section surface-piercing strut operating with an aspect-ratio-0.25 modified-flat-plat rectangular lifting surface. The interference effects of the struct on lift were negligible at all depths for drag and at all but very shallow depths for lift and pitching moment.
Date: April 1955
Creator: Ramsen, John A. & Vaughan, Victor L., Jr.
Partner: UNT Libraries Government Documents Department

The unsteady lift of a wing of finite aspect ratio

Description: "Unsteady-lift functions for wings of finite aspect ratio have been calculated by correcting the aerodynamic inertia and the angle of attack of the infinite wing. The calculations are based on the operational method. The starting lift of the finite wing is found to be only slightly less than that of the infinite wing; whereas the final lift may be considerably less" (p. 1).
Date: June 15, 1939
Creator: Jones, Robert T.
Partner: UNT Libraries Government Documents Department

Transient effects of the wing wake on the horizontal tail

Description: "An investigation was made of the effect of the wing wake on the lift of the horizontal tail surfaces. In the development of expressions for this effect, the growth of wing circulation and wing wake, the time interval represented by the tail length, and the development of lift by the rail were considered. The theory has been applied to a specific case to show the magnitude of the effect to be expected. It is shown that, for motions below a certain frequency, the development of lift by the tail may be represented by a simple lag function. The lag is, however, somewhat greater than that indicated by the rail length" (p. 1).
Date: August 1940
Creator: Jones, Robert T. & Fehlner, Leo F.
Partner: UNT Libraries Government Documents Department

Theoretical symmetric span loading due to flap deflection for wings of arbitrary plan form at subsonic speeds

Description: From Summary: "A simplified lifting-surface theory is applied to the problem of evaluating span loading due to flap deflection for arbitrary wing plan forms. With the resulting procedure, the effects of flap deflection on the span loading and associated aerodynamic characteristics can be easily computed for any wing which is symmetrical about the root chord and which has a straight quarter-chord line over the wing semispan. The effects of compressibility and spanwise variation of section lift-curve slope are taken into account by the procedure. The method presented can also be used to calculate the downwash in the vertical center of the wake of a wing which has arbitrary spanwise loading."
Date: September 22, 1950
Creator: DeYoung, John
Partner: UNT Libraries Government Documents Department

Effect of aerofoil aspect ratio on the slope of the lift curve

Description: On of the most important characteristics of an airfoil is the rate of change of lift with angle of attack, (sup dC)L/d alpha. This factor determines the effectiveness of a tail plane in securing static longitudinal stability. The application of the Gottingen formulas given here for calculating the variation of (sup Dc)L/d alpha with aspect ratio should be of interest to many aeronautical engineers. For the convenience of the engineer, a set of curves calculated by the method set forth here are given in graphical form. Also, the observed values of (sup dC)L/d alpha for the same airfoil at various aspect ratios follow the calculated curves closely.
Date: January 1922
Creator: Diehl, Walter S.
Partner: UNT Libraries Government Documents Department

The determination of downwash

Description: It is obvious that, in accordance with Newton's second law, the lift on an aerofoil must be equal to the vertical momentum communicated per second to the air mass affected. Consequently a lifting aerofoil in flight is trailed by a wash which has a definite inclination corresponding to the factors producing the lift. It is thought that sufficient data, theoretical and experimental, are now available for a complete determination of this wash with respect to the variation of its angle of inclination to the originating aerofoil and with respect to the law which governs its decay in space.
Date: January 1921
Creator: Diehl, Walter S.
Partner: UNT Libraries Government Documents Department

Influence of airfoil trailing-edge angle and trailing-edge-thickness variation on the effectiveness of a plain flap at high subsonic Mach numbers

Description: Report presenting the effects of variation of trailing-edge angle and trailing-edge thickness on the lift characteristics of a 10-percent-chord thick symmetrical airfoil section with a 25-percent-chord plain flap as obtained from wind-tunnel testing at a range of Mach numbers.
Date: June 1954
Creator: Hemenover, Albert D. & Graham, Donald J.
Partner: UNT Libraries Government Documents Department

The development of cambered airfoil sections having favorable lift characteristics at supercritical Mach numbers

Description: Several groups of new airfoil sections, designated as the NACA 8-series, are derived analytically to have lift characteristics at supercritical Mach numbers which are favorable in the sense that the abrupt loss of lift, characteristic of the usual airfoil section at Mach numbers above the critical, is avoided. Aerodynamic characteristics determined from two-dimensional wind-tunnel tests at Mach numbers up to approximately 0.9 are presented for each of the derived airfoils. Comparisons are made between the characteristics of these airfoils and the corresponding characteristics of representative NACA 6-series airfoils.
Date: 1949
Creator: Graham, Donald J.
Partner: UNT Libraries Government Documents Department

Flight determination of wing and tail loads on a fighter-type airplane by means of strain-gage measurements

Description: Report presenting a flight investigation to determine the contributions of wing, tail, and fuselage to the total airplane lift of a propeller-driven fighter-type airplane. The tests occurred over a range of Mach numbers. The loads on the various airplane components were measured by the use of calibrated strain-gage installations located at the roots of the wings and horizontal tail surfaces.
Date: October 1948
Creator: Aiken, William S., Jr.
Partner: UNT Libraries Government Documents Department

Tests of the NACA 653-018 airfoil section with boundary-layer control by suction

Description: Report presenting tests of the NACA 65(sub 3)-018 airfoil section with boundary-layer control by suction in the two-dimensional low-turbulence and two-dimensional low-turbulence pressure tunnels. Results regarding the lift characteristics, flow coefficient, maximum lift, amount of air removed by boundary-layer control, pressure distributions, and boundary layer shape are provided.
Date: October 1944
Creator: Quinn, John H., Jr.
Partner: UNT Libraries Government Documents Department

Experimental investigation of a flat plate paddle jet vane operating on a rocket jet

Description: Report presenting the results of static tests conducted for the purpose of determining the lift forces and hinge moments associated with a flat-plate paddle vane, externally hinged near a rocket-nozzle exit and operating on the jet for vane deflection angles ranging from -4 degrees to 25 degrees. Results regarding vane aerodynamic characteristics, performance of rocket motor, and vane erosion
Date: November 15, 1950
Creator: Bond, Aleck C.
Partner: UNT Libraries Government Documents Department

Investigation of the planing lift of a flat plate at speeds up to 170 feet per second

Description: Report presenting an investigation in the high-speed hydrodynamics facility to determine whether planing lift coefficient of a flat-bottom planing surface remains constant with increasing speed at the high towing speeds obtainable. The generally accepted assumption that there is no effect of speed on the lift coefficient of positive-pressure lifting surfaces is valid at least up to 170 fps.
Date: March 1957
Creator: Christopher, Kenneth W.
Partner: UNT Libraries Government Documents Department

Two-dimensional wind-tunnel investigation of an NACA 64-009 airfoil equipped with two types of leading-edge flap

Description: Report presenting an investigation to determine the effect of leading-edge flaps on the maximum lift coefficient of an NACA 64-009 airfoil and to compare the results with data obtained from previous testing of a similar flap. Two types of flaps, one intended to slide forward on the upper surface and one hinged at the center of the airfoil leading-edge radius, were tested. Results regarding lift characteristics, pitching-moment characteristics, and effect of leading-edge roughness are provided.
Date: June 1948
Creator: Fullmer, Felicien F., Jr.
Partner: UNT Libraries Government Documents Department

Some effects of frequency on the contribution of a vertical tail to the free aerodynamic damping of a model oscillating in yaw

Description: The damping in yaw and the directional stability of a model freely oscillating in yaw were measured tail-off and tail-on and compared with the values obtained by theoretical consideration of the unsteady lift associated with an oscillating vertical tail. A range of low frequencies comparable to those of the lateral motions of airplanes was covered. The analysis includes the effects of vertical-tail aspect ratio and the two-dimensional effects of compressibility.
Date: November 26, 1951
Creator: Bird, John D.; Fisher, Lewis R. & Hubbard, Sadie M.
Partner: UNT Libraries Government Documents Department

A proof of the theorem regarding the distribution of lift over the span for minimum induced drag

Description: The proof of the theorem that the elliptical distribution of lift over the span is that which will give rise to the minimum induced drag has been given in a variety of ways, generally speaking too difficult to be readily followed by the graduate of the average good technical school of the present day. In the form of proof this report makes an effort to bring the matter more readily within the grasp of this class of readers.
Date: 1931
Creator: Durand, W. F.
Partner: UNT Libraries Government Documents Department

An experimental investigation of the NACA 631-012 airfoil section with leading-edge and midchord suction slots

Description: Report presenting an investigation of using two suction slots in order to determine the effectiveness of a nose slot at higher values of lift. The suction through the midchord slot in conjunction with the nose slot resulted in substantial gains in the maximum lift over that obtainable with nose suction alone. Results regarding the lift, drag, and moment characteristics, pressure distribution, boundary-layer measurements, and plenum-chamber pressures are provided.
Date: February 1950
Creator: McCullough, George B. & Gault, Donald E.
Partner: UNT Libraries Government Documents Department