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Exploratory investigation at high and low subsonic Mach numbers of two experimental 6-percent-thick airfoil sections designed to have high maximum lift coefficients

Description: Report presenting an investigation to determine if thin airfoils with increased values of low-speed maximum lift coefficient but also retain the basic advantages of thin sections at high Mach numbers can be developed. Several experimental thin airfoil sections were developed from an analysis of airfoil data and two of them were investigated at high and low subsonic Mach numbers. Results regarding the low-speed characteristics and high-speed characteristics are provided.
Date: December 14, 1951
Creator: Loftin, Laurence K., Jr. & von Doenhoff, Albert E.
Partner: UNT Libraries Government Documents Department

Further comparisons of theoretical and experimental lift and pressure distributions on airfoils in cascade at low-subsonic speed

Description: Report presenting comparisons of theoretical and experimental lift coefficients and pressure distributions for five compressor-type cascades of highly cambered NACA 6-series airfoils. The experimental lift coefficients were generally less than the theoretical values for the same mean-flow direction. A justification of the experimental and analytical methods are also provided.
Date: August 1951
Creator: Katzoff, Samuel & Hannah, Margery E.
Partner: UNT Libraries Government Documents Department

Investigation of NACA 64,2-432 and 64,3-440 airfoil sections with boundary-layer control and an analytical study of their possible applications

Description: Report presenting testing of NACA 64-series airfoil sections to determine the effect of boundary-layer control by means of suction through an airfoil chord on the pressure distribution, lift, and drag characteristics of two different types of airfoil sections. Substantial reductions in wake drag were obtained through a wide range of lift coefficients with relatively moderate flow coefficients and pressure-loss coefficients. Results regarding airfoil-section data and effect of boundary-layer control on lift-drag ratio are provided.
Date: July 1951
Creator: Horton, Elmer A.; Racisz, Stanley Frank & Paradiso, Nicholas J.
Partner: UNT Libraries Government Documents Department

Low-speed characteristics of four cambered, 10-percent-thick NACA airfoil sections

Description: Report presenting a two-dimensional low-speed investigation of four thin, cambered airfoil sections. The data included measurements of lift, drag, pitching moment, and chordwise distribution of pressure. The maximum lift section coefficients, stall, effect of Reynolds number on maximum lift, surface roughness, and increment of maximum lift by a simulated split flap are described in detail.
Date: August 1950
Creator: McCullough, George B. & Haire, William M.
Partner: UNT Libraries Government Documents Department

Boundary-layer-control tests of two wings in the Langley Propeller-Research Tunnel

Description: Report presenting tests of two wings, one stubbed and one regular-sized, in the propeller-research tunnel to determine the increase in lift obtainable by boundary-layer control and to determine the power required for the blower. Lift coefficients of about 3.2 were obtainable for both wings, but the pressure method required several times more power than the suction method.
Date: January 1946
Creator: Freeman, Hugh B.
Partner: UNT Libraries Government Documents Department

The effect of rate of change of angle of attack on the maximum lift coefficient of a pursuit airplane

Description: Report presenting a study of the effect of rate of change of angle of attack on the maximum lift coefficient of a pursuit airplane equipped with a low-drag-type wing in stalls of varying abruptness over a range of Mach and Reynolds numbers. Maximum lift coefficients were found to increase linearly with increasing rate of change of angle of attack per chord length of travel up to the maximum rate attained in the tests.
Date: October 1951
Creator: Gadeberg, Burnett L.
Partner: UNT Libraries Government Documents Department

Preliminary Investigation of the Effect of Compressibility on the Maximum Lift Coefficient, Special Report

Description: Preliminary data are presented on the variation of the maximum lift coefficient with Mach number. The data were obtained from tests in the 8-foot high-speed tunnel of three NACA 16-series airfoils of 1-foot chord. Measurements consisted primarily of pressure-distribution measurements in order to illustrate the nature of the phenomena. It was found that the maximum lift coefficient of airfoils is markedly affected by compressibility even at Mach numbers as low as 0.2. At high Mach numbers pronounced decrease of the maximum lift coefficient was found. The magnitude of the effects of compressibility on the maximum lift coefficient and the low speeds at which these effects first appear indicate clearly that consideration of the take-off thrust for propellers will give results seriously in error if these considerations are based on the usual low-speed maximum-lift-coefficient data generally used.
Date: February 1943
Creator: Stack, John; Fedziuk, Henry A. & Cleary, Harold E.
Partner: UNT Libraries Government Documents Department

Determination of the theoretical pressure distribution for twenty airfoils

Description: This report gives the theoretical distribution of pressure at lift coefficients of 0, 0.5, 1.0, and 1.5 for 20 airfoils, calculated on the basis of a rigorous potential theory of arbitrary airfoils. It also provides tables from which the characteristics of the airfoils for any angle of attack in 2-dimensional potential flow are readily calculable. The theoretical values of the angles of zero lift, the lift and moment coefficients, and the ideal angles of attack are listed and some comparisons with experiment are indicated. The results presented may be of value in predicting structural loads and also in a correlation of theoretical pressure gradients with profile resistance.
Date: June 2, 1933
Creator: Garrick, I. E.
Partner: UNT Libraries Government Documents Department

The effect of several jet-engine air-inlet configurations on the low-speed static lateral stability characteristics of a 1/6-scale model of the MX-1764 airplane

Description: Report presenting an investigation in the 300 mph 7- by 10-foot tunnel to determine the effect of wing-root leading-edge- and scoop-type jet-engine air-inlet configurations on the static lateral stability characteristics of a scale model of the MX-1764 airplane. The inlet configurations generally had only small effects on the lateral stability.
Date: March 4, 1954
Creator: Croom, Delwin R.
Partner: UNT Libraries Government Documents Department

Wind-tunnel investigation at low speeds to determine flow-field characteristics and ground influence on a model with jet-augmented flaps

Description: Report presenting a wind-tunnel investigation at low speeds to determine the flow-field characteristics and ground influence on an airplane model with an untapered, unswept wing with an aspect ratio of 8.3 equipped with jet-augmented flaps. Results regarding the effect of ground-board distance and flow-field characteristics are provided.
Date: September 1957
Creator: Vogler, Raymond D. & Turner, Thomas R.
Partner: UNT Libraries Government Documents Department

Effects of Mach number variation between 0.07 and 0.34 and Reynolds number variation between 0.97 x 10(exp 6) and 8.10 x 10(exp 6) power on the maximum lift coefficient of a wing of NACA 64-210 airfoil sections

Description: Report presenting an investigation of the effects of Mach and Reynolds number on the maximum lift coefficient of a wing of NACA 64-210 airfoil section. The maximum lift coefficient was found to the a function of two independent variables, Mach number and Reynolds number, and both parameters have an important effect on the maximum lift coefficient in the ranges investigated. Results regarding observations of data and nature of Reynolds and Mach number effects are provided.
Date: August 1952
Creator: Fitzpatrick, James E. & Schneider, William C.
Partner: UNT Libraries Government Documents Department

Profile-Drag Coefficients of Conventional and Low-Drag Airfoils as Obtained in Flight

Description: Results of flight tests indicate that profile-drag coefficients which were obtained with the low-drag airfoils were lower than with the conventional types over the range of light coefficients tested. For comparable conditions of the lift coefficient and Reynolds Number, the low-drag airfoils have profile-drag coefficients which may be 27 percent lower than the profile drag of the conventional airfoils tested. Detailed results are presented graphically.
Date: May 1944
Creator: Zalovcik, John A.
Partner: UNT Libraries Government Documents Department

Low-speed tests of five NACA 66-series airfoils having mean lines designed to give high critical Mach numbers

Description: Report presenting an investigation of the possibility of developing an airfoil to carry lift without decreasing the critical Mach number below that of the basic thickness form at zero lift. Low-speed testing of five NACA 66-series airfoil sections with a thickness-chord ratio of 0.16 was carried out in the two-dimensional low-turbulence pressure tunnel. Results regarding the design lift coefficient, maximum lift coefficient, low-drag range, and pitching-moment coefficients are provided.
Date: May 1947
Creator: von Doenhoff, Albert E.; Stivers, Louis S., Jr. & O'Connor, James M.
Partner: UNT Libraries Government Documents Department

A study of the use of experimental stability derivatives in the calculation of the lateral disturbed motions of a swept-wing airplane and comparison with flight results

Description: An investigation was made to determine the accuracy with which the lateral flight motions of a swept-wing airplane could be predicted from experimental stability derivatives, determined in the 6-foot-diameter rolling-flow test section and 6 by 6-foot curved-flow test section of the Langley stability tunnel. In addition, determination of the significance of including the nonlinear aerodynamic effects of sideslip in the calculations of the motions was desired. All experimental aerodynamic data necessary for prediction of the lateral flight motions are presented along with a number of comparisons between flight and calculated motions caused by rudder and aileron disturbances.
Date: 1951
Creator: Bird, John D. & Jaquet, Byron M.
Partner: UNT Libraries Government Documents Department

Investigation at high and low subsonic Mach numbers of two symmetrical 6-percent-thick airfoil sections designed to have high maximum lift coefficients at low speeds

Description: Report presenting an investigation at high and low subsonic Mach numbers of two symmetrical 6-percent-thick airfoil sections derived to have high maximum lift at low speeds. The high-speed portion of the investigation included lift, drag, and pitching moment measurements.
Date: October 17, 1952
Creator: Paradiso, Nicholas J.
Partner: UNT Libraries Government Documents Department

Effects of high-lift devices and horizontal-tail location on the low-speed characteristics of a large-scale 45 degree swept-wing airplane configuration

Description: Report presenting a low-speed investigation of a large-scale model with a 45 degree swept wing of aspect ratio 3.5 and taper ratio 0.3. Wing-fuselage configurations with high-lift devices designed to delay the occurrence of stalled flow to a specific high lift coefficient at a specific angle of attack were tested. Results regarding the lift and drag characteristics, pitching-moment characteristics and effective downwash, rolling-moment characteristics, and performance characteristics are provided.
Date: August 18, 1954
Creator: Maki, Ralph L. & Embry, Ursel R.
Partner: UNT Libraries Government Documents Department

Lift and Drag of Wings with Small Span

Description: The lift coefficient of a wing of small span at first shows a linear increase for the increasing angle of attack, but to a lesser degree then was to be expected according to the theory of the lifting line; thereafter the lift coefficient increases more rapidly than linearity, as contrasted with the the theory of the lifting line. The induced drag coefficient for a given lift coefficient, on the other hand, is obviously much smaller than it would be according to the theory. A mall change in the theory of the lifting line will cover these deviations.
Date: August 1947
Creator: Weinig, F.
Partner: UNT Libraries Government Documents Department

An investigation at subsonic speeds of several modifications to the leading-edge region of the NACA 64A010 airfoil section designed to increase maximum lift

Description: Report presenting three modifications to the leading-edge region of the NACA 64A010 airfoil section, which were designed and tested two-dimensionally at both low and high subsonic speeds. The modifications increased the low-speed maximum lift coefficient of the symmetrical reference section, largely by increasing the angle of attack at which stall occurred.
Date: December 1956
Creator: Maki, Ralph L. & Hunton, Lynn W.
Partner: UNT Libraries Government Documents Department

Some fundamental considerations in regard to the use of power in landing an airplane

Description: From Summary: "This note is concerned with the effect of power on landing speed and apparent maximum lift coefficient. It is shown that when secondary effects are neglected, the maximum available increase in lift due to power is equal to the thrust being developed. If the increase in lift due to power is expressed in coefficient form, very high values may be shown under conditions which, on analysis, are found to be wholly impracticable in flight."
Date: March 1939
Creator: Diehl, Walter S.
Partner: UNT Libraries Government Documents Department

Summary of measurements in Langley full-scale tunnel of maximum lift coefficients and stalling characteristics of airplanes

Description: "The results of measurements in the Langley full-scale tunnel of the maximum lift coefficients and stalling characteristics of airplanes have been collected. The data have been analyzed to show the nature of the effects on maximum lift and stall of wing geometry, fuselages and nacelles, propeller slipstream, surface roughness, and wing leading-edge appendages such as ducts, armaments, tip slats, and airspeed heads. Comparisons of full-scale-tunnel and flight measurements of maximum lift and stall are included in some cases, and the effects of the different testing techniques on the maximum-lift measurements are also given (p. 1)".
Date: May 19, 1944
Creator: Sweberg, Harold H. & Dingeldein, Richard C.
Partner: UNT Libraries Government Documents Department

Summary of measurements in Langley full-scale tunnel of maximum lift coefficients and stalling characteristics of airplanes

Description: Report presenting the results of measurements in the full-scale tunnel of the maximum lift coefficients and stalling characteristics of airplanes. The data are analyzed to show the nature of the effects on maximum lift and stall of wing geometry, fuselages and nacelles, propeller slipstream, surface roughness, and wing leading-edge appendages like ducts, armament, tip slats, and airspeed heads.
Date: April 1945
Creator: Sweberg, Harold H. & Dingeldein, Richard C.
Partner: UNT Libraries Government Documents Department

Low-speed investigation of the effects of single slotted and double slotted flaps on a 47.7 degree sweptback-wing: fuselage combination at a Reynolds number of 6.0 x 10(exp 6)

Description: Report presenting an investigation to determine the effects of partial-span single slotted and double slotted flaps at various deflections on the longitudinal aerodynamic characteristics of a sweptback-wing-fuselage combination. Results regarding the lift characteristics, pitching-moment characteristics, drag characteristics, and effect of flap-bracket alignment are provided.
Date: September 10, 1951
Creator: Mollenberg, Ernst F. & Spooner, Stanley H.
Partner: UNT Libraries Government Documents Department