National Advisory Committee for Aeronautics (NACA) - 42 Matching Results

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Aerodynamic characteristics at transonic speeds of a 69 degree delta wing with a triangular plan-form control having a skewed hinge axis and an overhang balance: transonic-bump method

Description: From Introduction: "Presented in this paper are the results of an investigation of a semispan model of a delta wing with 60^o sweepback at the leading edge which was equipped with a large triangular control having an overhang balance mounted on a skewed hinge axis. The purpose of this investigation was to determine the aerodynamic characteristics of a delta wing with a control which was designed to provide aerodynamic balance at zero control deflection based on the span load distribution of ref… more
Date: February 6, 1951
Creator: Wiley, Harleth G.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Aerodynamic characteristics including pressure distribution of a fuselage and three combinations of the fuselage with swept-back wings at high subsonic speeds

Description: From Introduction: "The wings were tested in combination with fuselage similar to the one used in the 7- by 10-foot wind-tunnel investigations. The results are reported herein and are compared with results for three similar model wings on the transonic bump (references 1, 2, and 3)."
Date: February 6, 1951
Creator: Sutton, Fred B. & Martin, Andrew
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Altitude-test-chamber investigation of performance of a 28-inch ram-jet engine 3: combustion and operational performance of three flame holders with a center pilot burner

Description: Report presenting a direct-connect altitude test chamber investigation of the combustion performance of a 28-inch-diameter ramjet engine with a can-type center pilot burner. Combustion-chamber configurations with three different flame holders were investigated at a simulated flight Mach number of 2.0 and several different altitudes.
Date: February 6, 1951
Creator: Shillito, Thomas B.; Younger, George G. & Henzel, James G., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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An Analytical and Experimental Investigation of the Skin Friction of the Turbulent Boundary Layer on a Flat Plate at Supersonic Speeds

Description: Report presenting a review of turbulent-boundary-layer analyses and experimental data for average skin-friction coefficients on a flat plate in high-speed flow. New solutions are presented which show the effect of using a continuous velocity gradient and the effect of the extent of the laminar sublayer on the average skin-friction coefficient.
Date: February 1951
Creator: Rubesin, Morris W.; Maydew, Randall C. & Varga, Steven A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Basic Differential Equations in General Theory of Elastic Shells

Description: "The shell shall be considered as a three-dimensional continuous medium; for the coordinate surface, the middle surface of the shell shall be assumed parallel to the bounding surfaces. Let alpha and beta be the curvilinear orthogonal coordinates of this surface, coinciding with the lines of principal curvatures, and gamma the distance along the normal from the point (alpha,beta) of the coordinate surface to any point (alpha, beta, gamma) of the shell" (p. 1).
Date: February 1951
Creator: Vlasov, V. S.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Calculated Performance of a Direct-Air Nuclear Turbojet-Powered Airplane Using a Split-Flow Reactor and a Separated-Type Shield

Description: Memorandum presenting an analysis made to estimate the performance of a direct-air nuclear turbojet-powered airplane using a split-flow reactor and a separated-type shield. The analysis was for flight Mach numbers of 0.9 and 1.5 and covered a range of altitudes, reactor-wall temperatures, turbine-inlet temperatures, compressor pressure ratios, and airplane lift-drag ratios.
Date: February 1951
Creator: Doyle, R. B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Calculated Performance of a Direct-Air Nuclear Turbojet-Powered Airplane Using a Split-Flow Reactor and a Separated-Type Shield

Description: Memorandum presenting an analysis made to estimate the performance of a direct-air nuclear turbojet-powered airplane with a split-flow reactor and a separated-type shield. The analysis was for flight Mach numbers of 0.9 and 1.5 and covered a range of altitudes, reactor-wall temperatures, turbine-inlet temperatures, compressor pressure ratios, and airplane lift-drag ratios.
Date: February 1, 1951
Creator: Doyle, R. B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Dynamic stability and control characteristics of a vertically rising airplane model in hovering flight

Description: Report presenting an investigation to determine the stability and control characteristics of a vertically rising airplane model. Results of preliminary hovering flight tests are made in still air, away from the interference effects of the ground and side walls, and with normal airplane-type controls operating in the slipstream.
Date: February 23, 1951
Creator: Bates, William R.; Lovell, Powell M., Jr. & Smith, Charles C., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Effect of an Increase in Angle of Dead Rise on the Hydrodynamic Characteristics of a High-Length-Beam-Ratio Hull

Description: Report presenting an investigation in Langley tank no. 1 to determine the effects of increasing the angle of dead rise on various hydrodynamic qualities of a flying-boat hull with a length-beam ratio of 15. Results regarding the longitudinal stability, spray characteristics, take-off performance, rough-water landing characteristics, and a summary chart are provided.
Date: February 1951
Creator: Whitaker, Walter E., Jr. & Bryce, Paul W., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The effects of centrally mounted wing-tip tanks on the subsonic aerodynamic characteristics of a wing of aspect ratio 10 with 35 degrees of sweepback

Description: Report presenting an investigation of the effects of three centrally mounted wing-tip tanks on the aerodynamic characteristics of a cambered wing with an aspect ratio of 10 and 35 degrees of sweepback. Testing occurred over a range of Mach and Reynolds numbers and lift, drag, and pitching-moment were measured.
Date: February 21, 1951
Creator: Tinling, Bruce E. & Kolk, W. Richard
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The Effects of Increasing the Leading-Edge Radius and Adding Forward Camber on the Aerodynamic Characteristics of a Wing With 35 Degrees of Sweepback

Description: Report presenting a wind-tunnel investigation to determine the effects of a section modification on the aerodynamic characteristics of a wing with 35 degrees of sweepback. The wing was modified by increasing the leading-edge radius of the NACA 64A010 section and adding a small amount of camber to the forward portion of the chord. Lift, drag, pitching-moment, and trailing-edge-flap hinge-moment characteristics of the modified wing are compared with results from the original wing.
Date: February 9, 1951
Creator: Demele, Fred A. & Sutton, Fred B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The effects of Mach number and Reynolds number on the aerodynamic characteristics of several 12-percent-thick wings having 35 degrees of sweepback and various amounts of camber

Description: Report presenting a comparison of the lift, drag, and pitching-moment characteristics of several wings with 35 degrees of sweepback and various amounts of camber in wind-tunnel testing. Six semispan model wings were tested, three with an aspect ratio of 10 and three with an aspect ratio of 5. Results regarding model distortion under aerodynamic loads, effects of Reynolds number, effects of Mach number, and effects of camber are provided.
Date: February 23, 1951
Creator: Tinling, Bruce E. & Kolk, W. Richard
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Effects of Several Arrangements of Rectangular Vortex Generators on the Static-Pressure Rise Through a Short 2:1 Diffuser

Description: Memorandum presenting an investigation of a 2:1 area-ratio diffuser of length equal to the inlet diameter with several arrangements of simple rectangular vortex generators over a speed range up to an inlet Mach number of 0.5. The investigation was for an inlet boundary layer of 5 percent of the inlet diameter, a condition for which this diffuser had substantial separated areas with no vortex generators. Results regarding the diffuser with no vortex generators, counterrotating vortex generators,… more
Date: February 20, 1951
Creator: Valentine, E. Floyd & Carroll, Raymond B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Effects on longitudinal stability and control characteristics of a B-29 airplane of variations in stick-force and control-rate characteristics obtained through use of a booster in the elevator-control system

Description: The longitudinal stability and control characteristics of a B-29 airplane have been measured with a control surface booster incorporated in the elevator-control system. The measurements were obtained with the booster operating to provide various control-force gradients and various maximum rates of control motion. Results are presented which show the effect of these booster parameters on the handling qualities of the test airplane.
Date: February 1951
Creator: Mathews, Charles W.; Talmage, Donald B. & Whitten, James B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Elastic Constants for Corrugated-Core Sandwich Plates

Description: "The sandwich plate consisting of corrugated sheet fastened between two face sheets is considered. Application of existing theories to the analysis of such a sandwich plate requires the knowledge of certain elastic constants. Formulas and charts are presented for the evaluation of these constants" (p. 1).
Date: February 1951
Creator: Libove, Charles & Hubka, Ralph E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Estimation of Low-Speed Lift and Hinge-Moment Parameters for Full-Span Trailing-Edge Flaps on Lifting Surfaces With and Without Sweepback

Description: Note presenting comparisons of the low-speed experimental lift and hinge-moment parameters of flapped lifting surfaces with and without sweepback with values computed by several theoretical procedures. Based on these limited results, one theoretical method appears to be more satisfactory than the other methods investigated and is therefore recommended fore preliminary design estimates. Sample calculations are included.
Date: February 1951
Creator: Dods, Jules B., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Experimental Pressure Distributions Over Two Wing-Body Combinations at Mach Number 1.9

Description: Memorandum presenting pressure distributions on two wing-body combinations obtained at a Mach number of 1.9 to investigate the wing-body interference. A rectangular wing, a triangular wing, and a cylindrical body with an ogive nose were studied alone and in combination. The pressure distributions over the wing-body combination compared favorably with theoretical calculations based primarily on a generalization of the method of Nielsen and Matteson, except at the root section of the wings where … more
Date: February 5, 1951
Creator: Moskowitz, Barry & Maslen, Stephen H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Factors Affecting the Starting Characteristics of Gas-Turbine Engines

Description: "This report summarizes the effects of fuel volatility and engine design variables on the problem of starting gas-turbine engines at sea-level and altitude conditions. The starting operation for engines with tubular combustors is considered as three steps; namely, (1) ignition of a fuel-air mixture in the combustor, (2) propagation of flame through cross-fire tubes to all combustors, and (3) acceleration of the engine from windmilling or starting speed to the operating speed range. Pertinent da… more
Date: February 8, 1951
Creator: Lewis Laboratory Fuels Panel
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Flight Performance of a Twin-Engine Supersonic Ram Jet From 2,300 to 67,200 Feet Altitude

Description: Report presenting a flight investigation of a ground-launched supersonic twin ram-jet test vehicle using short flame-length burners. Results were obtained for a range of Mach numbers, altitudes, and fuel-air-ratios. Engine performance, gross thrust, fuel rate, total impulse, values of combustion efficiency and impulse, and overall combustion efficiency are also included.
Date: February 19, 1951
Creator: Dettwyler, H. Rudolph & Bond, Aleck C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Force and pressure characteristics for a series of nose inlets at Mach numbers from 1.59 to 1.99 3: conical-spike all-external-compression inlet with supersonic cowl lip

Description: Memorandum presenting an investigation conducted in the Lewis 8- by 6-foot supersonic wind tunnel to determine the force and pressure characteristics of an all-external compression inlet with a conical spike and a supersonic cowl lip. Measurements of lift, drag, pitching moment, and internal and external pressures were made at free-stream Mach numbers of 1.59, 1.79, and 1.99 for a range of mass-flow ratios and angles of attack to 10 degrees.
Date: February 14, 1951
Creator: Weinstein, Maynard I. & Davids, Joseph
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Free-flight performance of 16-inch diameter supersonic ram-jet units 4: performance of ram-jet units designed for combustion chamber inlet Mach number of 0.21 at free-stream Mach number of 1.6 over a range flight conditions

Description: Report presenting an investigation of 16-inch-diameter ram-jet units under free-flight conditions to determine performance at high subsonic, transonic, and supersonic velocities. Full-scale units were released from the airplane at high altitudes and accelerated by the engine thrust and force of gravity. Results regarding the diffuser total-pressure recovery, drag, thrust coefficient, and combustion are provided.
Date: February 26, 1951
Creator: Rabb, Leonard & North, Warren J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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An investigation of convergent-divergent diffusers at Mach number 1.85

Description: Report presenting an investigation in the supersonic tunnel at Mach number 1.85 and angles of attack from 0 to 5 degrees to determine optimum design configurations for a convergent-divergent type of supersonic diffusers with a subsonic diffuser of 5 degrees included divergence angle. Total-pressure recoveries in excess of the theoretical recovery across a normal shock at a free-stream Mach number of 1.85 were obtained with a number of configurations.
Date: February 2, 1951
Creator: Wyatt, DeMarquis D. & Hunczak, Henry R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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An investigation of the spray characteristics of a jet-powered dynamic model of the drag flying boat with a vee tail : TED No. NACA DE 328

Description: An investigation was made of the spray characteristics of a jet-powered dynamic model of the Bureau of Aeronautics DR 56 flying-boat design with a vee tail. A limited investigation was made to determine the effect of the change in tail design on the take-off and landing behavior in smooth water and in waves 8 feet high (full size).
Date: February 28, 1951
Creator: Carter, Arthur W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Lift and Pitching Derivatives of Thin Sweptback Tapered Wings with Streamwise Tips and Subsonic Leading Edges at Supersonic Speeds

Description: Note presenting the lift-due-to-pitching derivative and the damping-in-pitch derivative, which were derived for a series of thin sweptback tapered wings with streamwise tips and subsonic leading edges. The effects of camber and thickness were not considered.
Date: February 1951
Creator: Malvestuto, Frank S., Jr. & Hoover, Dorothy M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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