National Advisory Committee for Aeronautics (NACA) - 37 Matching Results

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An Investigation at Low Speed of a Large-Scale Triangular Wing of Aspect Ratio Two 1: Characteristics of a Wing Having a Double-Wedge Airfoil Section With Maximum Thickness at 20-Percent Chord

Description: Report presenting an investigation of the low-speed characteristics of a 25-foot span triangular wing with an aspect ratio of 2. the airfoil section of the wing was a symmetrical double wedge with 5-percent maximum thickness at 20-percent chord. Results regarding the longitudinal characteristics, lateral characteristics, and directional characteristics are provided.
Date: November 13, 1947
Creator: Anderson, Adrien E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Effect of afterbody length and keel angle on minimum depth of step for landing stability and on take-off stability of a flying boat

Description: From Summary: "Tests were made to fill partly the need for information on the effect of afterbody dimensions on the hydrodynamic stability of a flying boat in smooth water. The dimensions investigated were depth of step, angle of afterbody keel, and length of afterbody. An analysis of the data showed that as either the afterbody length or keel angle was increased an accompanying increase in depth of step was required in order to maintain adequate landing stability."
Date: November 13, 1947
Creator: Olson, Roland E. & Land, Norman S.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Analysis of effect of basic design variables on subsonic axial-flow-compressor performance

Description: From Summary: "A blade-element theory for axial-flow compressors has been developed and applied to the analysis of the effects of basic design variables such as Mach number, blade loading, and velocity distribution on compressor performance. The relations among several efficiencies useful in compressor design are derived and discussed. The possible gains in useful operating range obtainable by the use of adjustable stator blades are discussed and a rapid approximate method of calculating blade-… more
Date: November 26, 1947
Creator: Sinnette, John T., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Stability derivatives of triangular wings at supersonic speeds

Description: "The analysis of the stability derivatives of low-aspect-ratio triangular wings at subsonic and supersonic speeds, given in NACA TN no. 1423, is extended to apply to triangular wings having large vertex angles and traveling at supersonic speeds. The lift, rolling moment due to sideslip, and damping in roll and pitch for this more general case have been treated elsewhere on the basis of the theory of small disturbances. The surface potentials for angle of attack and rolling taken therefrom are u… more
Date: November 6, 1947
Creator: Ribner, Herbert S. & Malvestuto, Frank S., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Free-Spinning-Tunnel Tests of a 1/24-Scale Model of the McDonnell XP-88 Airplane with a Vee Tail

Description: "An investigation of the spin and recovery characteristics of a 1/24-scale model of the McDonnell XP-88 airplane has been conducted in the Langley 20-ft free-spinning tunnel. Results of tests with a conventional tail have been previously reported; the results presented herein are for the model with a vee tail installed. The effects of control settings and movements on the erect and inverted spin and recovery characteristics of the model. In the normal loading were determined" (p. 1).
Date: November 28, 1947
Creator: Berman, Theodore
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Stability and Control Characteristics of a 1/10-Scale Model of the McDonnell XP-85 Airplane While Attached to the Trapeze

Description: "At the request of the Air Materiel Command, Army Air Forces, an investigation of the low-speed, power-off, stability and control characteristics of the McDonnell XP-85 airplane has been conducted in the Langley free-flight tunnel. The results of the portion of the investigation consisting of tests of a 1/10-scale model to study the stability of the XP-85 when attached to the trapeze and during retraction into the B-36 bomb bay are presented herein. In the power-off condition the stability was … more
Date: November 17, 1947
Creator: Johnson, Joseph L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Investigation of the Stability and Control Characteristics of a 1/20-Scale Model of the Consolidated Vultee XB-53 Airplane in the Langley Free-Flight Tunnel

Description: "An investigation of the low-speed, power-off stability and control characteristics of a 1/20-scale model of the Consolidated Vultee XB-53 airplane has been conducted in the Langley free-flight tunnel. In the investigation it was found that with flaps neutral satisfactory flight behavior at low speeds was obtainable with an increase in height of the vertical tail and with the inboard slats opened. In the flap-down slat-open condition the longitudinal stability was satisfactory, but it was impos… more
Date: November 17, 1947
Creator: Bennett, Charles V.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Preliminary Results of an Altitude-Wind-Tunnel Investigation of a TG-100A Gas Turbine-Propeller Engine 4 - Compressor and Turbine Performance Characteristics

Description: "As part of an investigation of the performance and operational characteristics of the TG-100A gas turbine-propeller engine, conducted in the Cleveland altitude wind tunnel, the performance characteristics of the compressor and the turbine were obtained. The data presented were obtained at a compressor-inlet ram-pressure ratio of 1.00 for altitudes from 5000 to 35,000 feet, engine speeds from 8000 to 13,000 rpm, and turbine-inlet temperatures from 1400 to 2100R. The highest compressor pressure … more
Date: November 13, 1947
Creator: Wallner, Lewis E. & Saari, Martin J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Preliminary Results of an Altitude-Wind-Tunnel Investigation of a TG-100A Gas Turbine-Propeller Engine 3 - Pressure and Temperature Distributions

Description: An altitude-wind-tunnel investigation of a TG-100A gas turbine-propeller engine was performed. Pressure and temperature data were obtained at altitudes from 5000 to 35000 feet, compressor inlet ram-pressure ratios from 1.00 to 1.17, and engine speeds from 800 to 13000 rpm. The effect of engine speed, shaft horsepower, and compressor-inlet ram-pressure ratio on pressure and temperature distribution at each measuring station are presented graphically.
Date: November 13, 1947
Creator: Geisenheyner, Robert M. & Berdysz, Joseph J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Simulated Altitude Performance of Combustors for the 24C Jet Engine: 2: 24C-4 Combustor

Description: "The performance of a 24C-4 combustor was investigated with three different combustor baskets and five modifications of these baskets at conditions simulating static (zero-ram) operation of the 24C jet engine over ranges of altitude and engine speed to determine and improve the altitude operational limits of the 24C combustor. Information was also obtained regarding combustion characteristics, the fuel-flow characteristics of the fuel manifolds, and the combustor total-pressure drop. NACA modif… more
Date: November 12, 1947
Creator: Bernardo, Everett; Schroeter, Thomas T. & Miller, Robert C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Aerodynamic Characteristics of a Number of Modified NACA Four-Digit-Series Airfoil Sections

Description: Theoretical pressure distributions and measured lift, drag, and pitching moment characteristics at three values of Reynolds number are presented for a group of NACA four-digit-series airfoil sections modified for high-speed applications. The effectiveness of flaps applied to these airfoils and the effect of standard leading-edge roughness were also investigated at one value of Reynolds number. Results are also presented of tests of three conventional NACA four-digit-series airfoil sections.
Date: November 14, 1947
Creator: Loftin, Laurence K., Jr. & Cohen, Kenneth S.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Effect of Chordwise Vanes on Amplitude of Tail Buffeting

Description: "Flight tests have been made with a P-51D airplane to determine the effect of chordwise vanes on the amplitude of tail buffeting. The tests made during abrupt pull-ups to the buffeting boundary included strain measurements on wing and tail and tuft studies over the wing. The results indicate that the vanes tested have no appreciable effect on the amplitude of tail buffeting" (p. 1).
Date: November 10, 1947
Creator: Stokke, Allen R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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An investigation of the effect of tip shape on the low-speed aerodynamic characteristics of large-scale swept wings

Description: Report presenting an investigation of the effect of tip shape on the aerodynamic characteristics of large-scale 45 degrees swept-forward and 45 degrees swept-back wings. The results show that none of the variations of tip shape investigated nor the addition of bodies of revolution at the tips produced major changes in the characteristics of the swept wings.
Date: November 13, 1947
Creator: Walling, Walter C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Flight Investigation to Determine the Hinge Moments of a Beveled-Edge Aileron on a 45 Degree Sweptback Wing at Transonic and Low Supersonic Speeds

Description: Report discussing testing of a model of the pilotless aircraft RM-1 to measure aileron hinge moments in flight in order to determine the reason for loss of roll stabilization at supercritical speeds in flight. The aileron was found to become quickly underbalanced over the full deflection range at supercritical speeds. Information about the general flight behavior, aileron hinge moments, and roll stabilization of the model is provided.
Date: November 12, 1947
Creator: Gardner, William N. & Curfman, Howard J., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Aerodynamic characteristics at subcritical and supercritical Mach numbers of two airfoil sections having sharp leading edges and extreme rearward positions of maximum thickness

Description: From Introduction: "A 12-percent-chord-thick wedge section and a reversed NACA 0012 section were chosen for these tests as they are representative of sections having no boat tailing and appreciable boat tailing (i.e., blunt and rounded trailing edges, respectively), and the results of this investigation are compared with those obtained from a previous investigation of the NACA 0012 section. Conclusions are drawn regarding the relative merits of the two unconventional sections and the convention… more
Date: November 6, 1947
Creator: Eggers, A. J., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Preliminary evaluation of the performance of a uniflow two-stroke-cycle spark-ignition engine combined with a blowdown turbine and a steady-flow turbine

Description: Report presenting calculations based on a theoretical analysis for a composite engine consisting of a uniflow two-stroke-cycle spark-ignition engine, a compressor, a blowdown turbine, and a steady-flow turbine. Operation of the engine is considered for four cases of gas mixtures and steady-flow turbine temperatures.
Date: November 25, 1947
Creator: Sather, Bernard I. & Foster, Hampton H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Preliminary Tank Tests of NACA Hydro-Skis for High-Speed Airplanes

Description: Report presenting the results from tank landing and take-off tests with a dynamic model of a hypothetical jet-propelled airplane equipped with NACA hydro-skis. Results regarding landing tests, take-off tests, and practical considerations for the creation of hydro-ski configurations are provided. The hydro-skis suitable for flush retraction into streamline fuselages do appear to offer a practical means of water take-offs and landings.
Date: November 26, 1947
Creator: Dawson, John R. & Wadlin, Kenneth L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Precautions for Flight Testing Near the Speed of Sound

Description: From experience gained by NACA test pilots in flying at high subsonic Mach numbers and from interpretation of the data obtained, some general precautionary rules for test flying near sonic Mach numbers have been formulated. The reasons for these rules are discussed and observations are made with respect to the hazards arising from undesirable stability and control characteristics which have been noted in test flights of various airplanes. This paper, although written primarily for the attention… more
Date: November 5, 1947
Creator: Clousing, Lawrence A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Comparison between flight-measured and calculated span load distribution at high Mach numbers

Description: Report presenting an analysis of the spanwise loading using two different methods on the wing of an airplane for which pressure-distribution measurements were available from flight tests up to a Mach number of 0.866. A comparison between measured and calculated distributions was made on the basis of equal wing-panel normal-force coefficients.
Date: November 26, 1947
Creator: Rolls, L. Stewart
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Wing-flow tests of a triangular wing of aspect ratio two 1: effectiveness of several types of trailing-edge flaps on flat-plate models

Description: Report presenting an investigation of the problem of applying controls to low-aspect-ratio wings of triangular plan form by using the NACA wing-flow method with parallel-sided models with sharp leading and trailing edges. Results regarding the data analysis, Reynolds number and separation effects, flap effectiveness, plan-form characteristics, angle of zero lift, and triangular plan-form flying-wing characteristics are provided.
Date: November 14, 1947
Creator: Rathert, George A., Jr. & Cooper, George E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Low-Speed Characteristics in Pitch of a 42 Degree Sweptback Wing With Aspect Ratio 3.9 and Circular-Arc Airfoil Sections

Description: Report presenting tests in a pressure tunnel to determine the low-speed pitch characteristics of a 42 degree sweptback wing with circular-arc airfoil sections. Information regarding the characteristics of basic wing, leading-edge flap investigation, and effects of fuselage are provided.
Date: November 13, 1947
Creator: Neely, Robert H. & Koven, William
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The Spot Welding of Alclad 24S-T in Thicknesses of 0.064, 0.081, and 0.102 Inch

Description: Note presenting an investigation to determine the spot-welding characteristics of heavy gages of Alclad 24S-T aluminum alloy. The weldability of the alloy in thicknesses of 0.064, 0.081, and 0.102 inch was investigated in order to determine the capacity of the machine.
Date: November 1947
Creator: Hess, W. F.; Wyant, R. A. & Winsor, F. J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Stress-Strain and Elongation Graphs for Alclad Aluminum-Alloy 75S-T Sheet

Description: Note presenting results of tests on duplicate longitudinal and transverse specimens of Alclad aluminum-alloy 75S-T sheets with three nominal thicknesses. The stress-strain, stress-deviation, tangent-modulus, and reduced-modulus graphs are plotted on a dimensionless basis to make them applicable to material with yield strengths which differ from those of the test specimens.
Date: November 1947
Creator: Miller, James A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The 1350 F stress-rupture properties of two wrought alloys and three cast alloys

Description: From Summary: "These properties compare favorably with those of the strongest similar alloys previously investigated. However, compared with a 60Cr-25Fe-15Mo alloy, the three cobalt-chronium-nickel cast alloys are inferior. A correlation of NACA and OSRD (Project NRC-8) data is presented, showing the variation of rupture strengths with temperature in the range of 1350^o to 2000^o for alloys."
Date: November 1947
Creator: Reynolds, E. E.; Freeman, J. W. & White, A. E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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