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  Partner: UNT Libraries Government Documents Department
 Serial/Series Title: NACA Research Memorandums
 Collection: Technical Report Archive and Image Library
Average Outside-Surface Heat-Transfer Coefficients and Velocity Distributions for Heated and Cooled Impulse Turbine Blades in Static Cascades

Average Outside-Surface Heat-Transfer Coefficients and Velocity Distributions for Heated and Cooled Impulse Turbine Blades in Static Cascades

Date: March 9, 1951
Creator: Hubbartt, James E. & Schum, Eugene F.
Description: Heat-transfer investigation conducted on cooled as well heated impulse-type turbine blades in a static cascade to determine the effect of direction of heat flow on convective heat-transfer coefficients.
Contributing Partner: UNT Libraries Government Documents Department
Comparison of the performance of a helicopter-type ram-jet engine under various centrifugal loadings

Comparison of the performance of a helicopter-type ram-jet engine under various centrifugal loadings

Date: October 7, 1953
Creator: Radin, Edward J & Carpenter, Paul J
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Investigations toward simplification of missile control systems

Investigations toward simplification of missile control systems

Date: November 12, 1953
Creator: Strass, H Kurt; Crane, Harold L & Curfman, Howard J , Jr
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Large-scale low-speed wind-tunnel tests of a model having a 60 degree delta horizontal canard control surface and wing to obtain static-longitudinal-stability and canard surface hinge-moment data

Large-scale low-speed wind-tunnel tests of a model having a 60 degree delta horizontal canard control surface and wing to obtain static-longitudinal-stability and canard surface hinge-moment data

Date: June 17, 1954
Creator: Burrows, Dale L
Description: None
Contributing Partner: UNT Libraries Government Documents Department
A study of the use of various high-lift devices on the horizontal tail of a canard airplane model as a means of increasing the allowable center-of-gravity travel

A study of the use of various high-lift devices on the horizontal tail of a canard airplane model as a means of increasing the allowable center-of-gravity travel

Date: January 21, 1953
Creator: Johnson, Joseph L , Jr
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Wind-tunnel investigation to determine the horizontal- and vertical-tail contributions to the static lateral stability characteristics of a complete-model swept-wing configuration at high subsonic speeds

Wind-tunnel investigation to determine the horizontal- and vertical-tail contributions to the static lateral stability characteristics of a complete-model swept-wing configuration at high subsonic speeds

Date: July 10, 1953
Creator: Kuhn, Richard E; Fournier, Paul G & Wiggins, James W
Description: None
Contributing Partner: UNT Libraries Government Documents Department
A pressure-distribution investigation of a fineness-ratio-12.2 parabolic body of revolution (NACA RM-10) at M = 1.59 and angles of attack up to 36 degrees

A pressure-distribution investigation of a fineness-ratio-12.2 parabolic body of revolution (NACA RM-10) at M = 1.59 and angles of attack up to 36 degrees

Date: October 30, 1952
Creator: Gapcynski, John P; Hasel, Lowell E & Cooper, Morton
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Investigation of the aerodynamic characteristics of the NACA RM-10 missile (with fins) at a Mach number of 1.62 in the Langley 9-inch supersonic tunnel

Investigation of the aerodynamic characteristics of the NACA RM-10 missile (with fins) at a Mach number of 1.62 in the Langley 9-inch supersonic tunnel

Date: December 19, 1952
Creator: Coletti, Donald E
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Rocket-model investigation to determine the hinge-moment and normal-force properties of a full-span, constant-chord, partially balanced trailing-edge control on a 60 degree clipped delta wing between Mach numbers of 0.50 and 1.26

Rocket-model investigation to determine the hinge-moment and normal-force properties of a full-span, constant-chord, partially balanced trailing-edge control on a 60 degree clipped delta wing between Mach numbers of 0.50 and 1.26

Date: October 30, 1953
Creator: Martz, C William & Goslee, John W
Description: None
Contributing Partner: UNT Libraries Government Documents Department
An experimental study of five annular air inlet configurations at subsonic and transonic speeds

An experimental study of five annular air inlet configurations at subsonic and transonic speeds

Date: August 19, 1953
Creator: Pendley, Robert E; Bryan, Carroll R; Fleming, Frank F & Milillo, Joseph R
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The effects of a small jet of air exhausting from the nose of a body of revolution in supersonic flow

The effects of a small jet of air exhausting from the nose of a body of revolution in supersonic flow

Date: November 12, 1952
Creator: Love, Eugene S
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Effect of ice formations on section drag of swept NACA 63A-009 airfoil with partical-span leading-edge slat for various modes of thermal ice protection

Effect of ice formations on section drag of swept NACA 63A-009 airfoil with partical-span leading-edge slat for various modes of thermal ice protection

Date: March 15, 1954
Creator: Von Glahn, Uwe H & Gray, Vernon H
Description: Studies were made to determine the effect of ice formations on the section drag of a 6.9-foot-chord 36 degree swept NACA 63A-009 airfoil with partial-span leading-edge slat. In general, the icing of a thin swept airfoil will result in greater aerodynamic penalties than for a thick unswept airfoil. Glaze-ice formations at the leading edge of the airfoil caused large increases in section drag even at liquid-water content of 0.39 gram per cubic meter. The use of an ice-free parting strip in the stagnation region caused a negligible change in drag compared with a completely unheated airfoil. Cyclic de-icing when properly applied caused the drag to decrease almost to the bare-airfoil drag value.
Contributing Partner: UNT Libraries Government Documents Department
Investigation of turbines for driving supersonic compressors II : performance of first configuration with 2.2 percent reduction in nozzle flow area / Warner L. Stewart, Harold J. Schum, Robert Y. Wong

Investigation of turbines for driving supersonic compressors II : performance of first configuration with 2.2 percent reduction in nozzle flow area / Warner L. Stewart, Harold J. Schum, Robert Y. Wong

Date: July 22, 1952
Creator: Stewart, Warner L; Schum, Harold J & Wong, Robert Y
Description: The experimental performance of a modified turbine for driving a supersonic compressor is presented and compared with the performance of the original configuration to illustrate the effect of small changes in the ratio of nozzle-throat area to rotor-throat area. Performance is based on the performance of turbines designed to operate with both blade rows close to choking. On the basis of the results of this investigation, the ratio of areas is concluded to become especially critical in the design of turbines such as those designed to drive high-speed, high-specific weight-flow compressors where the turbine nozzles and rotor are both very close to choking.
Contributing Partner: UNT Libraries Government Documents Department
Design considerations for mixed-flow centrifugal compressors with high weight-flow rates per unit frontal area

Design considerations for mixed-flow centrifugal compressors with high weight-flow rates per unit frontal area

Date: March 5, 1953
Creator: Stanitz, John D
Description: An analysis is made of the factors affecting the weight-flow rate per unit frontal area of centrifugal compressors with axial-flow vaned diffusers preceded by mixed-flow vaneless sections. It is shown that, for specified inlet conditions to the impeller and vaned diffuser, the weight-flow rate is increased at the expense of pressure ratio and vice versa. Charts are presented to help the designer make a satisfactory compromise between weight-flow rate and pressure ratio. Some conclusions of the investigation are : (1) Prewhirl is of negligible value in centrifugal compressors designed for high weight-flow rates.
Contributing Partner: UNT Libraries Government Documents Department
Design considerations of a condensing system for vaporized magnesium

Design considerations of a condensing system for vaporized magnesium

Date: November 30, 1955
Creator: Witzke, Walter R; Prok, George M & Keller, Thomas A
Description: The effect of the design characteristics of various condensing chambers on magnesium build-up at the chamber inlet was investigated. The condensing chambers are used in the vapor-condensation process for making magnesium slurries. A complete description of the various chamber designs and the procedure used in testing the chambers is given. The results are evaluated on the basis of clogging and total magnesium distilled per run. Orifice design was also considered.
Contributing Partner: UNT Libraries Government Documents Department
The design of brittle-material blade roots based on theory and rupture tests of plastic models

The design of brittle-material blade roots based on theory and rupture tests of plastic models

Date: April 6, 1953
Creator: Meyer, Andre J , Jr; Kaufman, Albert & Caywood, William C
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Cascade investigation of cooling characteristics of a cast-finned air-cooled turbine blade for use in a turboprop engine

Cascade investigation of cooling characteristics of a cast-finned air-cooled turbine blade for use in a turboprop engine

Date: June 12, 1957
Creator: Stepka, Francis S; Richards, Hadley T & Hickel, Robert O
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Effect of fuels on combustion efficiency of 5-inch ram-jet-type combustor

Effect of fuels on combustion efficiency of 5-inch ram-jet-type combustor

Date: May 22, 1953
Creator: Reynolds, Thaine W
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Effect of fuel volatility characteristics on ignition-energy requirements in a turbojet combustor

Effect of fuel volatility characteristics on ignition-energy requirements in a turbojet combustor

Date: January 13, 1953
Creator: Foster, Hampton H & Straight, David M
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Drag data for 16-inch-diameter ram-jet engine with double-cone inlet in free flight at Mach numbers from 0.7 to 1.8

Drag data for 16-inch-diameter ram-jet engine with double-cone inlet in free flight at Mach numbers from 0.7 to 1.8

Date: October 25, 1954
Creator: Jones, Merle L; Rabb, Leonard & Simpkins, Scott H
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Drop burning rates of hydrocarbon and nonhydrocarbon fuels

Drop burning rates of hydrocarbon and nonhydrocarbon fuels

Date: August 6, 1957
Creator: Smith, Arthur L & Graves, Charles C
Description: None
Contributing Partner: UNT Libraries Government Documents Department
A drop test for the evaluation of the impact strength of cermets

A drop test for the evaluation of the impact strength of cermets

Date: March 15, 1955
Creator: Pinkel, B; Deutsch, G C & Katz, N H
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Chemical igniters for starting jet fuel - nitric acid rockets

Chemical igniters for starting jet fuel - nitric acid rockets

Date: October 8, 1957
Creator: Morrell, Gerald & Ladanyi, Dezso J
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Chordwise pressures and section moment force and moment coefficients at high subsonic speeds near midspan of a tapered 35 degree sweptback wing with a flap-type control and an attached tab

Chordwise pressures and section moment force and moment coefficients at high subsonic speeds near midspan of a tapered 35 degree sweptback wing with a flap-type control and an attached tab

Date: March 29, 1954
Creator: Hammond, Alexander D & Keffer, Barbara M
Description: None
Contributing Partner: UNT Libraries Government Documents Department
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