National Advisory Committee for Aeronautics (NACA) - 742 Matching Results

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Tests of the NACA 64(Sub 1)-012 and 64(Sub 1)A012 Airfoils at High Subsonic Mach Numbers

Description: Memorandum presenting an investigation on NACA 64(sub 1)-012 and 64(sub 1)A012 airfoils at a range of Mach numbers and low Reynolds numbers, which indicated that the effect of increasing the trailing-edge angle was inappreciable on the Mach number for the normal-force break, to decrease the normal-force-curve slope, to reduce the effects of compressibility, and to decrease the minimum drag coefficient and to increase maximum normal-force to drag ratio.
Date: July 9, 1948
Creator: Lindsey, W. F. & Humphreys, Milton D.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Effect of High-Lift Devices on the Low-Speed Static Lateral and Yawing Stability Characteristics of an Untapered 45 Degrees Sweptback Wing

Description: Memorandum presenting a wind-tunnel investigation made in the stability tunnel to determine the effects of lift flaps on the static lateral stability derivatives and the yawing derivatives of an untapered 45 degree sweptback wing at low speeds. Results regarding straight flow and yawing characteristics are provided.
Date: September 30, 1948
Creator: Lichtenstein, Jacob H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Performance of a Ram-Jet-Type Combustor With Flame Holders Immersed in the Combustion Zone

Description: Memorandum presenting the beneficial effects on stability limits and combustion efficiency produced by the application of surfaces immersed in the combustion zone to a ram-jet-type burner. Investigations were made with one, two, three, and four rows of wedges at simulated sea-level and altitude subsonic ram-jet flight conditions. The addition of rows of wedges immersed in the combustion zone regularly extended the stability limits of combustion.
Date: November 1948
Creator: Breitwieser, Roland
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Experimental investigation at supersonic speeds of twin-scoop duct inlets of equal area 3: inlet enclosing 37.2 percent of the maximum circumference of the forebody

Description: Report presenting testing of a twin-scoop duct inlet that enclosed 37.2 percent of the forebody circumference at Mach numbers between 1.36 and 2.01. The approach to each scoop consisted of a ramp that deflected the flow to create an oblique shock wave in front of the duct entrance. Results regarding the inlet proportions, ramp angle, slots, and angle of incidence are provided.
Date: July 22, 1948
Creator: Davis, Wallace F. & Edwards, Sherman S.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Control requirements and control parameters for a ram jet with variable-area exhaust nozzle

Description: Report presenting control requirements and parameters for a ram jet with a variable-area exhaust nozzle, which have been analyzed from calculated performance charts covering flight Mach numbers from 0.6 to 3.0 and altitudes from sea level to 30,000 feet. Requirements for maximum efficiency, safe and stable operation, maximum range of thrust at a given flight Mach number, and control of fuel flow are discussed and control parameters are selected.
Date: November 17, 1948
Creator: Boksenbom, Aaron S. & Novik, David
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Downwash and Dynamic Pressure at the Horizontal Tail of a Six-Engine Pusher-Propelled Airplane

Description: Report discussing an investigation of the vertical plane of the elevator hinge line of a powered model of a bomber to determine the values of downwash and the dynamic-pressure ratio. The equations for calculating these values and the testing procedures are described.
Date: July 19, 1948
Creator: Furlong, G. Chester
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Wind-tunnel investigation of transonic aileron flutter of a semispan wing model with an NACA 23013 section

Description: Report presenting the results of a wind-tunnel investigation of aileron flutter up to 0.822 Mach number. The testing indicated the absence of flutter of significant amplitude when a considerable amount of wing-tip relief existed and the presence of flutter when the relief was minimized. Results regarding the testing without the end plate, with end plate, and comparison with theory are provided.
Date: July 12, 1948
Creator: Perone, Angelo & Erickson, Albert L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Residual Stress Analysis of Overspeeded Disk With Central Hole by X-Ray Diffraction

Description: An X-ray - diffraction analysis of residual surface stresses after plastic strain was introduced in a parallel-sided 3S-O aluminum disk with a central hole by two types of centrifugal overspeed is reported. Both tangential and radial stresses were generally tensile with large local variations near the hole where surface stresses may have been partly superficial. These stresses were both tensile and compressive dependent on the distance from the disk center when mass compression was effected nea… more
Date: July 23, 1948
Creator: Good, James N.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Investigation of Horn Balances on a 45 Degree Sweptback Horizontal Tail Surface at High Subsonic Speeds

Description: A wind-tunnel investigation of horn balances on a 45 degree sweptback, semispan, horizontal tail surface was made to determine the effects of horn size and inboard-edge fairing at a Mach number of 0.30 and to determine the effects of compressibility up to a Mach number of 0.89. Presented are lift, drag, pitching-moment, and hinge-moment data and lift and hinge-moment parameters.
Date: December 3, 1948
Creator: Johnson, Harold S. & Thompson, Robert F.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Stability and control characteristics of a free-flying model with an unswept wing of aspect ratio 3 (XS-3)

Description: The results of power-off force tests and flight tests of a model with a thin unswept low-aspect-ratio wing are presented. The tests were made with the flaps retracted and deflected. The effects on the lateral flight characteristics of decreasing directional stability were noted.
Date: November 15, 1948
Creator: Bennett, Charles V. & Hassell, James L., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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NACA Transonic Wing-Tunnel Test Sections

Description: Memorandum presenting an approximate subsonic theory developed for the solid blockage interference in circular wind tunnels with walls slotted in the direction of flow. The theory indicated the possibility of obtaining zero blockage interference. Tests in a circular slotted tunnel based on the theory confirmed the theoretical predictions.
Date: October 25, 1948
Creator: Wright, Ray H. & Ward, Vernon G.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The effect of negative dihedral, tip droop, and wing-tip shape on the low-speed aerodynamic characteristics of a complete model having a 45 degrees sweptback wing

Description: "An investigation has been conducted in the Langley 300 MPH 7- by 10-foot tunnel to determine the effect of negative dihedral, tip droop, and wing-tip shape on the low-speed aerodynamic characteristics of a complete model having a 45 degrees sweptback wing. Longitudinal and lateral stability characteristics were obtained for the model with and without tail surfaces" (p .1).
Date: December 6, 1948
Creator: Spearman, M. Leroy & Becht, Robert E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Inlet Icing and Effectiveness of Hot-Gas Bleedback for Ice Protection of Turbojet Engine

Description: Report presenting an investigation of icing and ice protection at the inlet of a turbojet engine in the altitude wind tunnel. A method of ice protection was studied that uses hot gas bled from a turbine inlet and injected into the air stream ahead of the compressor inlet. Ice was either prevented or accumulated slowly at various engine speed levels.
Date: November 26, 1948
Creator: Fleming, William A. & Saari, Martin J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Ditching tests of a 1/15-scale model of the Fairchild C-82 airplane

Description: Given here are results of tests made in calm water at various landing attitudes, speeds, and simulated conditions of damage. It was concluded that the best ditching could be made by contacting the water as near the stall angle as possible without losing adequate control. The landing flaps should be full down. If the paratainer hatch and aft-cargo doors fail as expected in a ditching, there will be a large inrush of water into the cargo compartment which makes this location a very hazardous ditc… more
Date: October 7, 1948
Creator: Fisher, Lloyd J. & Hoffman, Edward L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Measurements of the chordwise pressure distributions over the wing of the XS-1 research airplane in flight

Description: Report presenting measurements of the chordwise pressure distributions over the 8-percent-thick wing of the XS-1 research airplane at a section near the midspan of the left wing. Data are presented for a Mach number range and a normal-force coefficient of about 0.33. Results regarding the upper-surface pressure distribution, lower-surface pressure distributions, and total section loads are provided.
Date: August 4, 1948
Creator: Beeler, De E.; McLaughlin, Milton D. & Clift, Dorothy C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Visual Observations of the Shock Wave in Flight

Description: "This report presents the results of pilot observations and photographs of the compression shock wave on the wing of an airplane in flight. A detailed description of the test conditions necessary and the procedure to be following in producing the visible shock are presented. The pilot's observations of the occurrence of an oscillating shock wave and its possible relationship with the airplane buffeting are also presented" (p. 1).
Date: May 24, 1948
Creator: Cooper, George E. & Rathert, George A., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Evaluation of Gust and Draft Velocities From Flights of P-61C Airplanes Within Thunderstorms July 31, 1947 to August 6, 1947 at Clinton County Army Air Field, Ohio

Description: Memorandum presenting the results of measurements of gust and draft velocities within thunderstorms at an air field over a 7-day period. The data are summarized in tables and compared to previous flights.
Date: February 13, 1948
Creator: Funk, Jack
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Preliminary Investigation at a Mach Number of 1.9 and a Reynolds Number of 2,200,000 of Three Ailerons Applicable to the Bell XS-2 Airplane Design

Description: Report presenting testing of a 42.7 degree sweptback tapered wing with three types of ailerons tested at a Mach number of 1.9 and a Reynolds number of 2,200,000; the wing geometry was similar to that of an XS-2 airplane. The purpose of the investigation was to determine the effectiveness of ailerons at these specified flight characteristics. Results regarding the aerodynamic characteristics of the wing are also provided.
Date: May 25, 1948
Creator: Sivells, James C. & Conner, D. William
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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An investigation of submerged air inlets on a 1/4-scale model of a typical fighter-type airplane

Description: Report presenting wind-tunnel testing of submerged air inlets on the fuselage of a scale model of a typical fighter-type airplane. The results are presented for ramp plan forms with parallel and with diverging walls and show the effect of the duct-entrance location, internal ducting efficiency, and deflectors.
Date: June 2, 1948
Creator: Delany, Noel K.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Notes on the Application of Airfoil Studies to Helicopter Rotor Design

Description: Report presenting a discussion of a number of the problems that most frequently arise with airfoils on helicopters. A reference list of published reports on airfoil section characteristics which are useful in regards to these helicopter problems is also included.
Date: September 22, 1948
Creator: Gustafson, F. B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Preliminary Investigation to Determine Propeller Section Characteristics by Measuring the Pressure Distribution on an NACA 10-(3)(08)-03 Propeller Under Operating Conditions

Description: "An investigation has been made in the Langley 16-foot high-speed tunnel to determine the propeller-section characteristics by measuring the pressure distribution on the airfoil sections of a rotating propeller. The pressures were measured at nine radial stations on an NACA 10-(3)(08)-03 design two-blade propeller. This paper presents the results of the pressure measurements in the form of normal-force and moment coefficients and covers a range of nominal angle of attack (simple blade element t… more
Date: July 14, 1948
Creator: Evans, Albert J. & Liner, George
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Effect of High-Lift Devices on the Longitudinal and Lateral Characteristics of a 45 Degrees Sweptback Wing with Symmetrical Circular-Arc Sections

Description: Memorandum presenting an investigation conducted in the full-scale tunnel to determine the longitudinal characteristics of several leading-edge and trailing-edge flap configurations and the lateral characteristics of one flapped configuration on a 45 degree sweptback wing with circular-arc sections, an aspect ratio of 3.5, and a taper ratio of 0.5. Results regarding stall studies, leading-edge flaps, trailing-edge flaps, flap combinations, rounded leading-edge modification and fences, landing-p… more
Date: October 1948
Creator: Guryansky, Eugene R. & Lipson, Stanley
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Flight Investigation of Loads on a Bubble-Type Canopy

Description: Report presenting the results of pressure-distribution measurements obtained in flight over the free-blown canopy of a fighter-type airplane. The measurements were compared to those of the same canopy in wind-tunnel testing to determine the degree of correlation and effects of Mach number and distortion on the pressure distribution.
Date: October 29, 1948
Creator: Matheny, Cloyce E. & Huston, Wilber B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Investigation of a Thin Wing of Aspect Ratio 4 in the Ames 12-Foot Pressure Wind Tunnel 1: Characteristics of a Plain Wing

Description: Memorandum presenting wind-tunnel tests of a semispan model of an unswept wing of aspect ratio 4 and taper ratio 0.5 at Mach numbers up to 0.94 to determine its aerodynamic characteristics as influenced by Mach number, Reynolds number, and modification of the basic diamond profile by rounding the ridge. Lift, drag, and pitching-moment data are presented for a range of Reynolds and Mach numbers. The results indicated that no severe static-longitudinal-stability problems up to Mach number 0.94.
Date: June 2, 1948
Creator: Johnson, Ben H., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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