National Advisory Committee for Aeronautics (NACA) - 75 Matching Results

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Some effects of gutter flame-holder dimensions on combustion-chamber performance of 20-inch ram jet

Description: Report presenting the operational characteristics of a 20-inch ramjet with four different gutter-grid flame holders and a three-gutter flame holder with an adjustable gutter angle. The flame holders were compared on the basis of operating ranges of fuel-air ratio, combustion-chamber-inlet velocity, and the combustion efficiencies obtainable.
Date: July 30, 1948
Creator: Wilcox, Fred A.; Perchonok, Eugene & Wishnek, George
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Vibration Survey of NACA 24-Inch Supersonic Axial-Flow Compressor

Description: "Vibration investigations were made of two blade cascades in wind tunnels and of blades operated in the NACA 24-inch supersonic compressor. The results showed that the blade vibrations were present at all tunnel and compressor air velocities and were influenced primarily by tunnel design, simulated centrifugal loading, surging, angle of attack, and possible critical Mach numbers" (p. 1).
Date: July 30, 1948
Creator: Meyer, André J., Jr. & Hanson, Morgan P.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Free-Flight-Tunnel Tests of a Target-Seeking Glide-Bomb Model With Flicker Lateral Control

Description: Report presenting an investigation of control systems suitable for target-seeking missiles. Testing occurred in the free-flight tunnel of the GB-5 glide bomb equipped with a light-seeker control unit which applied flicker control. Results indicated that good stability could be obtained with the control system, but was somewhat less stable than with a proportional control system.
Date: July 28, 1948
Creator: McKinney, Marion O., Jr. & Drake, Hubert M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Investigation of effects of movable exhaust-nozzle plug on operational performance of 20-inch ram jet

Description: Report presenting the effects of a movable exhaust-nozzle plug on the operational performance of a 20-inch ramjet in the altitude wind tunnel. Results were obtained at various exhaust-nozzle-plug positions over a range of fuel-air ratios, combustion-chamber-inlet velocities and static pressures, and ambient-air static pressures.
Date: July 27, 1948
Creator: Sterbentz, William H. & Wilcox, Fred A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Theoretical Characteristics of Two-Dimensional Supersonic Control Surfaces

Description: Report presenting aerodynamic characteristics of uncambered symmetrical parabolic and double-wedge airfoils with leading-edge and trailing-edge flaps using the Busemann second-order-approximation theory. Characteristics presented include aileron effectiveness factor, rate of change of hinge-moment coefficient with aileron deflection, rate of change of the pitching-moment coefficient, and the location of the center of pressure of the airfoil-aileron combination.
Date: July 27, 1948
Creator: Morrissette, Robert R. & Oborny, Lester F.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Application of Theodorsen's Theory to Propeller Design

Description: "A theoretical analysis is presented for obtaining by use of Theodorsen's propeller theory the load distribution along a propeller radius to give the optimum propeller efficiency for any design condition. Examples are included to illustrate the method of obtaining the optimum load distributions for both single-rotating and dual-rotating propellers" (p. 1).
Date: July 26, 1948
Creator: Crigler, John L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Free-flight investigation of the rolling effectiveness at high subsonic, transonic, and supersonic speeds of leading-edge and trailing-edge ailerons in conjunction with tapered and untapered plan forms

Description: Report presenting several rectangular and tapered wing configurations with leading-edge and trailing-edge ailerons tested as part of a general investigation of an aerodynamic control at supersonic speeds. Results indicated that the use of the leading-edge aileron alone was ineffective or caused negative control until a high Mach number was attained. Results for the untapered configurations, tapered configurations, and drag measurements are provided.
Date: July 23, 1948
Creator: Strass, H. Kurt
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Longitudinal Stability and Control Characteristics of a Semispan Airplane Model With a Sweptback Wing and Tail From Tests at Transonic Speeds by the NACA Wing-Flow Method

Description: Report presenting an investigation using the NACA wing-flow method to determine the longitudinal stability and control characteristics at transonic speeds of a semispan airplane with a 45 degree sweptback wing and tail. Measurements of the lift and angle of attack for trim were made for several stabilizer and elevator settings. Testing was also performed to investigate the effects of transition wires mounted on the wing and tail, the effect of increasing the boundary-layer thickness on the test… more
Date: July 23, 1948
Creator: Sawyer, Richard H. & Lina, Lindsay J.
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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Some Flight Measurements of Pressure-Distribution and Boundary-Layer Characteristics in the Presence of Shock

Description: Memorandum presenting some pressure-distribution and boundary-layer measurements made in flight in the presence of shock on two modifications of the local contour of the wings of a high-speed airplane. Results regarding the pressure distribution, boundary-layer surveys, and effects on test airplane are provided.
Date: July 23, 1948
Creator: Zalovcik, John A. & Luke, Ernest P.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Effect of Inlet-Air Parameters on Combustion Limit and Flame Length in 8-Inch-Diameter Ram-Jet Combustion Chamber

Description: Report presenting an investigation with a ram-jet combustion chamber to determine the effect of fuel-air ratio and the inlet-air parameters of pressure, temperature, and velocity on combustion limit, combustion efficiency, and flame length.
Date: July 22, 1948
Creator: Cervenka, A. J. & Miller, R. C.
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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Investigation of High-Temperature Operation of Liquid-Cooled Gas Turbines 1: Turbine Wheel of Aluminum Alloy, a High-Conductivity Nonstrategic Material

Description: Report presenting an investigation of turbine operating temperatures as affected by liquid cooling, especially if materials of high conductivity are used, at gas temperatures up to 1925 degrees Fahrenheit. Results regarding the statio heat-transfer rig and turbine rig are provided. The investigation showed that nonstrategic material such as aluminum alloy can be used in liquid-cooled turbine wheels at high gas temperatures.
Date: July 22, 1948
Creator: Kottas, Harry & Sheflin, Bob W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Longitudinal Stability Characteristics of a 42 Degree Sweptback Wing and Tail Combination at a Reynolds Number of 6.8 X 10 (Exp 6)

Description: Results of a wind-tunnel investigation at a Reynolds number of 6.8 x 10(exp 6) to determine the static longitudinal stability characteristics of a 42 degree sweptback wing and fuselage combination with a sweptback horizontal tail are provided. Included are the effects of vertical position of fuselage and tail with respect to wing for several combinations of high-lift and staff-control devices. Also included is the effect of a simulated ground.
Date: July 22, 1948
Creator: Spooner, Stanley H. & Martina, Albert P.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Tank spray tests of a jet-powered model fitted with NACA hydro-skis

Description: Report presenting tank results for take-off tests with a powered dynamic model of a hypothetical jet-propelled high-speed airplane fitted with NACA hydro-skis and with flush turbojet intakes on the upper part of the fuselage near the nose. Some of the investigations included were the possibility of making take-offs without spray entering the intakes, the effect of turbojet air inflow on the tendency of spray to enter the intakes, and the effect of jet power on trim.
Date: July 22, 1948
Creator: Wadlin, Kenneth L. & Ramsen, John A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Effect of a nacelle on the low-speed aerodynamic characteristics of a swept-back wing

Description: Wind-tunnel tests of a simplified nacelle on a semispan wing having approximately 35 degrees of sweepback were made at low speeds to evaluate the effects of the nacelle on the aerodynamic characteristics of the wing. Force, moment, and pressure-distribution measurements are presented for the nacelle underslung and centrally mounted on the wing and mounted on a strut below the wing.
Date: July 21, 1948
Creator: Hanson, Frederick H., Jr. & Dannenberg, Robert E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Free-Flight Investigation at Transonic and Supersonic Speeds of a Wing-Aileron Configuration Simulating the D-558-2 Airplane

Description: "An investigation of the rolling effectiveness at transonic and supersonic speeds of a wing-aileron configuration simulating the D-558-2 airplane has been made by means of a rocket-propelled test vehicle. The variation of rolling effectiveness with Mach number is similar to that obtained previously for tapered sweptback wings having full-span, 0.2-chord ailerons" (p. 1).
Date: July 21, 1948
Creator: Sandahl, Carl A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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An investigation at low speed of a 51.3 degrees sweptback semispan wing with a raked tip and with 16.7-percent-chord ailerons having three spans and three trailing-edge angles

Description: Report presenting a wind-tunnel investigation at low speed to determine the aerodynamic characteristics of a 51.3 degree sweptback semispan wing with a raked tip and with 16.7-percent-chord sealed plain ailerons. Lift, drag, pitching-moment, and hinge-moment data were obtained for the wing with transition free and fixed with various spans of aileron deflected as lift flaps. The rolling moment, yawing moment, hinge moment, and aileron seal pressure characteristics were determined for each of the… more
Date: July 21, 1948
Creator: Fischel, Jack & Schneiter, Leslie E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Measurement Through the Speed of Sound of Static Pressures on the Rear of Unswept and Sweptback Circular Cylinders and on the Rear and Sides of a Wedge by the NACA Wing-Flow Method

Description: Report presenting static-pressure measurements made through the speed of sound by the NACA wing-flow method at the back of two unswept circular cylinders and one sweptback cylinder. Static pressures were found to decrease considerably with an increase in Mach number. Information about the length and diameter of the cylinders and how it affects measurements is provided.
Date: July 21, 1948
Creator: Sawyer, Richard H. & Daum, Fred L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Study of stress states in gas-turbine disk as determined from measured operating-temperature distributions

Description: Report presenting results of an experimental investigation to determine the temperature distribution in an aircraft-engine gas-turbine disk. Calculated stresses based on the measured temperature distributions are presented. Results regarding stresses in the inner region of the disk and stresses in the rim of the disk are provided.
Date: July 21, 1948
Creator: Farmer, J. Elmo; Millenson, M. B. & Manson, S. S.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Flight Test of NACA FR-1-B, a Low-Acceleration Rocket-Propelled Vehicle for Transonic Flutter Research

Description: Report presenting testing of a low-acceleration transonic flutter test vehicle to obtain flutter data on two similar sweptback wings which indicated that wing flutter was symmetrical in mode. Results regarding flight and flutter characteristics for the FR-1-B are provided.
Date: July 20, 1948
Creator: Angle, Ellwyn E.; Clevenson, Sherman A. & Lundstrom, Reginald R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Longitudinal Trim and Tumble Characteristics of a 0.057-Scale Model of the Chance Vought XF7U-1 Airplane, TED NO. NACA DE311

Description: Based on results of longitudinal trim and tumble tests of a 0.057-scale model of the Chance Vought XF7U-1 airplane, the following conclusions regarding the trim and tumble characteristics of the airplane have been drawn: 1. The airplane will not trim at any unusual or uncontrolled angles of attack. 2. The airplane will not tumble with the center of gravity located forward of 24 percent of the mean aerodynamic chord. When the center of gravity is located at 24 percent of the mean aerodynamic cho… more
Date: July 20, 1948
Creator: Bryant, Robert L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The NACA 2000-horsepower propeller dynamometer and tests at high speed of an NACA 10-(3)(08)-03 two-blade propeller

Description: This paper contains a detailed description of a 2,000-horsepower propeller dynamometer used to make wind-tunnel tests of a two-blade NACA 10-(3)(08)-03 propeller for a range of blade angles from 20 degrees to 55 degrees at airspeeds up to 500 miles per hour. The results of these tests and comparisons with results obtained from a theoretical analysis and from previous tests made in other wind tunnels are presented.
Date: July 20, 1948
Creator: Corson, Blake W., Jr. & Maynard, Julian D.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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