National Advisory Committee for Aeronautics (NACA) - 775 Matching Results

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Characteristics of Four Nose Inlets as Measured at Mach Numbers Between 1.4 and 2.0

Description: Memorandum presenting the pressure recovery, mass flow, and axial force of four bodies with nose inlets measured at Mach numbers between 1.4 and 2.0 and angles of attack of 0, 3, 6, and 9 degrees. The drag coefficients of axially symmetric diffusers operating at the maximum mass-flow rates were calculated from schileren photographs of the head shock waves and frictional drag considerations. Results regarding open-nose diffusers and conical-shock diffusers are provided.
Date: June 25, 1951
Creator: Brajnikoff, George B. & Rogers, Arthur W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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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.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Charts and tables for use in calculations of downwash of wings of arbitrary plan form

Description: From Summary: "Values of the downwash of a horseshoe vortex in compressible flow are presented in the form of charts and tables. The use of the charts and tables in the calculations of the downwash of wings of arbitrary plan form is discussed. The results of a few calculations are compared with experimental results."
Date: May 1951
Creator: Diederich, Franklin W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Charts for estimation of longitudinal-stability derivatives for a helicopter rotor in forward flight

Description: Report presenting charts to provide a convenient means for obtaining the derivatives of rotor resultant force, rotor pitching amount about the helicopter center of gravity, and rotor torque with respect to rotor angle of attack, forward speed, rotor speed, and collective pitch.
Date: March 1951
Creator: Amer, Kenneth B. & Gustafson, Frederic Bowen
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Charts Giving Critical Compressive Stress of Continuous Flat Sheet Divided Into Parallelogram-Shaped Panels

Description: "Charts giving the compressive-buckling stress coefficients for sheet panels of a shape occurring in swept-wing plan forms are presented. The panels are assumed to be a part of a continuous flat sheet divided by nondeflecting supports into parallelogram-shaped areas. The stability analysis was performed by the energy method and the results show that, over a wide range of panel aspect ratio, such panels are decidedly more stable than equivalent rectangular panels of the same area" (p. 1).
Date: July 1951
Creator: Anderson, Roger A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Combustion-Chamber Performance Characteristics of a Python Turbine-Propeller Engine Investigated in Altitude Wind Tunnel

Description: Combustion-chamber performance characteristics of a Python turbine-propeller engine were determined from investigation of a complete engine over a range of engine speeds and shaft horsepowers at simulated altitudes. Results indicated the effect of engine operating conditions and altitude on combustion efficiency and combustion-chamber total pressure losses. Performance of this vaporizing type combustion chamber was also compared with several atomizing type combustion chambers.
Date: November 16, 1951
Creator: Campbell, Carl E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Combustion Instability in an Acid-Heptane Rocket with a Pressurized-Gas Propellant Pumping System

Description: Results of experimental measurements of low-frequency combustion instability of a 300-pound thrust acid-heptane rocket engine were compared to the trends predicted by an analysis of combustion instability in a rocket engine with a pressurized-gas propellant pumping system. The simplified analysis, which assumes a monopropellant model, was based on the concept of a combustion the delay occurring from the moment of propellant injection to the moment of propellant combustion. This combustion time … more
Date: September 27, 1951
Creator: Tischler, Adelbert O. & Bellman, Donald R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Combustion performance evaluation of magnesium-hydrocarbon slurry blends in a simulated tail-pipe burner

Description: Report presenting an experimental investigation to determine the combustion properties of several magnesium-hydrocarbon slurry blends and to indicate the feasibility of the application of slurry-type fuels to high-speed aircraft. High-concentration magnesium slurries showed large improvements in combustion stability and tail-pipe-burner net thrust.
Date: May 15, 1951
Creator: Tower, Leonard K. & Branstetter, J. Robert
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Combustion properties of aluminum as ram-jet fuel

Description: Report presenting an experimental investigation to determine the combustion properties of aluminum as a fuel for use in high-speed aircraft. The aluminum fuel was injected both in powder and wire form into 2-inch-diameter ramjet-type combustors. Results regarding operational problems, thrust, and combustion efficiency are provided.
Date: March 28, 1951
Creator: Branstetter, J. Robert; Lord, Albert M. & Gerstein, Melvin
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Comparison of airfoil sections on two triangular-wing-fuselage configurations at transonic speeds from tests by the NACA wing-flow method

Description: Report presenting tests using the NACA wing-flow method at a range of Mach numbers to determine the aerodynamic characteristics of four triangular-wing-fuselage models. Measurements of the normal force, chord force, and pitching moment for various angles of attack. Two models had wings of aspect ratio 2.31, one with an NACA 65-009 airfoil section and one with a 9-percent-thick biconvex section, and two with wings of aspect ratio 4, one with an NACA 65-006 airfoil and one with a 6-percent-thick … more
Date: August 8, 1951
Creator: Hall, Albert W. & McKay, James M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Comparison of drag, pressure recovery, and surface pressure of a scoop-type inlet and an NACA submerged inlet at transonic speeds

Description: Report presenting an investigation of a solid half body modified to mount a scoop inlet and a submerged inlet while maintaining the same entrance geometry, afterbody, and diffuser for both inlets. Comparative pressure-recovery, pressure-distribution, and drag data were obtained for the two inlet types.
Date: December 17, 1951
Creator: Frank, Joseph L. & Taylor, Robert A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Comparison of Heat Transfer from Airfoil in Natural and Simulated Icing Conditions

Description: "An investigation of the heat transfer from an airfoil in clear air and in simulated icing conditions was conducted in the NACA Lewis 6- by 9-foot icing-research tunnel in order to determine the validity of heat-transfer data as obtained in the tunnel. This investigation was made on the same model NACA 65,2-016 airfoil section used in a previous flight study, under similar heating, icing, and operating conditions. The effect of tunnel turbulence, in clear air and in icing was indicated by the f… more
Date: September 1951
Creator: Gelder, Thomas F. & Lewis, James P.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Comparison of High-Speed Operating Characteristics of Size 215 Cylindrical-Roller Bearings as Determined in Turbojet Engine and in Laboratory Test Rig

Description: "A comparison of the operating characteristics of 75-millimeter-bore (size 215) cylindrical-roller one-piece inner-race-riding cage-type bearings was made using a laboratory test rig and a turbojet engine. Cooling correlation parameters were determined by means of dimensional analysis, and the generalized results for both the inner- and outer-race bearing operating temperatures are compared for the laboratory test rig and the turbojet engine. Inner- and outer-race cooling-correlation curves wer… more
Date: November 28, 1951
Creator: Macks, E. Fred & Nemeth, Zolton N.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Comparison of Measured Efficiencies of Nine Turbine Designs with Efficiencies Predicted by Two Empirical Methods

Description: Empirical methods of Ainley and Kochendorfer and Nettles were used to predict performances of nine turbine designs. Measured and predicted performances were compared. Appropriate values of blade-loss parameter were determined for the method of Kochendorfer and Nettles. The measured design-point efficiencies were lower than predicted by as much as 0.09 (Ainley and 0.07 (Kochendorfer and Nettles).
Date: August 20, 1951
Creator: English, Robert E. & Cavicchi, Richard H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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A Comparison of Predicted and Experimentally Determined Longitudinal Dynamic Responses of a Stabilized Airplane

Description: Report presenting predictions of the dynamic longitudinal stability of an airplane with autopilot and comaprisons with measured flight frequency and transient responses for three airspeeds and various autopilot settings of displacement and rate of displacement feedback. Results regarding the aircraft transfer function, autopilot frequency response, hinge moment, autopilot gearing, and autopilot-aircraft combination are provided.
Date: December 1951
Creator: Smaus, Louis H.; Gore, Marvin R. & Waugh, Merle G.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Comparison of Semispan and Full-Span Tests of a 47.5 Degrees Sweptback Wing With Symmetrical Circular-Arc Sections and Having Drooped-Nose Flaps, Trailing-Edge Flaps, and Ailerons

Description: Report presenting an investigation to compare the characteristics of a full-span and a semispan highly swept wing in order to evaluate the general validity of the semispan wing testing technique. Results regarding the lift, drag, and pitching-moment characteristics are provided.
Date: December 5, 1951
Creator: Lipson, Stanley & Barnett, U. Reed, Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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A comparison of the calculated maximum-maneuver response characteristics of three air-to-air, beam-rider, guided missiles having different lift ratios

Description: Report presenting a comparison of the calculated response characteristics corresponding to the maximum maneuver of a variable-incidence, a canard, and a conventional tail-aft-control, beam-rider, guided missile. All the configurations were designed to be the same except for the effects of changes in lift ratio. Results regarding limited control-surface deflection, limited angle of attack of the critical surface, servo energy, surface-deflection interference, and size of surfaces are provided.
Date: September 25, 1951
Creator: Matthews, Howard F. & Stewart, Elwood C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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A comparison of the experimental and theoretical loading over triangular wings at supersonic speeds

Description: Report presenting the results of an experimental investigation of the pressure distribution over two triangular wings at supersonic speeds. The two wings which were tested had identical plan forms, 45 degrees of sweepback of the leading edge, and an aspect ratio of 4.0, but different airfoil sections. Results regarding the pressure distribution at zero lift, flow characteristics and pressure distribution at angles of attack, normal-force coefficients, and application of results to other triangu… more
Date: January 3, 1951
Creator: Boyd, John W. & Phelps, E. Ray
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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A comparison of the experimental and theoretical loading over triangular wings in sideslip at supersonic speeds

Description: The results of an experimental investigation of the load distribution over two triangular wings in sideslip at Mach numbers from 1.20 to 1.79 are presented and compared with theory. The two wings tested have identical plan form, 45 degrees sweepback of the leading edge, and an aspect ratio of 4.0. One model was composed of round-nose airfoil sections and the other of sharp-nose, biconvex sections. For both wings the maximum thickness of streamwise sections was 6 percent and was located at the 3… more
Date: May 18, 1951
Creator: Boyd, John W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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A comparison of the experimental subsonic pressure distributions about several bodies of revolution with pressure distributions computed by means of the linearized theory

Description: "An analysis is made of the effects of compressibility on the pressure coefficients about several bodies of revolution by comparing experimentally determined pressure coefficients with corresponding pressure coefficients calculated by the use of the linearized equations of compressible flow. The results show that the theoretical methods predict the subsonic pressure-coefficient changes over the central part of the body but do not predict the pressure-coefficient changes near the nose. Extrapola… more
Date: November 5, 1951
Creator: Matthews, Clarence W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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A Comparison of the Spanwise Loading Calculated by Various Methods With Experimental Loadings Obtained on a 45 Degree Sweptback Wing of Aspect Ratio 8.02 at a Reynolds Number of 4.0 X 10(6)

Description: "This report compares the experimental force and moment data obtained by pressure measurements on a wing of aspect ratio 8.02, 45 degree sweptback of the quarter-chord line, taper ratio of 0.45, and NACA 63(sub 1)A012 airfoil sections with the calculated loadings obtained by the standard methods proposed by Weissinger, Falkner, and Multopp, as well as by several variations of these methods" (p. 1175).
Date: August 14, 1951
Creator: Schneider, William C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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A Comparison of the Turbulent Boundary-Layer Growth on an Unswept and a Swept Wing

Description: Note presenting an experimental investigation in which measurements were made of the turbulent boundary layer of a two-dimensional unswept wing and a comparable wing swept 45 degrees. The results indicate the applicability of simple sweep theory for determining turbulent boundary-layer growth on the swept wing for a lift coefficient of zero.
Date: September 1951
Creator: Altman, John M. & Hayter, Nora-Lee F.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Comparison of Transonic Characteristics of Lifting Wings From Experiments in a Small Slotted Tunnel and the Langley High-Speed 7- by 10-Foot Tunnel

Description: Report presenting a comparison of the transonic aerodynamic characteristics of unswept and 45 degree sweptback wings in the high-speed tunnel and slotted tunnel. The purpose of the investigation was to explore the possibilities and limitations associated with transonic testing of relatively large wings in a rectangular slotted tunnel. Results regarding lift, pitching moments, drag, bending moments, and Schileren photographs are provided.
Date: November 5, 1951
Creator: Sleeman, William C., Jr.; Klevatt, Paul L. & Linsley, Edward L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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