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  Partner: UNT Libraries Government Documents Department
 Decade: 1950-1959
 Serial/Series Title: NACA Technical Notes
 Collection: National Advisory Committee for Aeronautics Collection
Two-Dimensional Subsonic Compressible Flows Past Arbitrary Bodies by the Variational Method

Two-Dimensional Subsonic Compressible Flows Past Arbitrary Bodies by the Variational Method

Date: March 1951
Creator: Wang, Chi-Teh
Description: Instead of solving the nonlinear differential equation which governs the compressible flow, an approximate method of solution by means of the variational method is used. The general problem of steady irrotational flow past an arbitrary body is formulated. Two examples were carried out, namely, the flow past a circular cylinder and the flow past a thin curved surface. The variational method yields results of velocity and pressure distributions which compare excellently with those found by existing methods. These results indicate that the variational method will yield good approximate solution for flow past both thick and thin bodies at both high and low Mach numbers.
Contributing Partner: UNT Libraries Government Documents Department
Summary of 65-Series Compressor-Blade Low-Speed Cascade Data by Use of the Carpet-Plotting Technique

Summary of 65-Series Compressor-Blade Low-Speed Cascade Data by Use of the Carpet-Plotting Technique

Date: February 1957
Creator: Felix, A. Richard
Description: Carpet plots included permit the selection of the blade camber and the design angle of attack required to fulfill a design vector diagram. Other carpet plots provide means for the prediction of off-design turning angles.
Contributing Partner: UNT Libraries Government Documents Department
Tables for the Computation of Wave Drag of Arrow Wings of Arbitrary Airfoil Section

Tables for the Computation of Wave Drag of Arrow Wings of Arbitrary Airfoil Section

Date: June 1954
Creator: Grant, Fredrick C. & Cooper, Morton
Description: Tables and computing instructions for the rapid evaluation of the wave drag of delta wings and of arrow wings having a ration of the tangent of the trailing-edge sweep angle to the tangent of the leading-edge sweep angle in the range from -1.0 to 0.8. The tables cover a range of both subsonic and supersonic leading edges.
Contributing Partner: UNT Libraries Government Documents Department
A low-speed experimental investigation of the effect of a sandpaper type of roughness on boundary-layer transition

A low-speed experimental investigation of the effect of a sandpaper type of roughness on boundary-layer transition

Date: January 1, 1958
Creator: Horton, E. A. & Vondoenhoff, A. E.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Reciprocity relations in aerodynamics

Reciprocity relations in aerodynamics

Date: May 1, 1952
Creator: Spreiter, John R & Heaslet, Max A
Description: None
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: September 1, 1956
Creator: Meyer, Andre J , Jr; Kaufman, Albert & Caywood, William C
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Drag coefficients for droplets and solid spheres in clouds accelerating in airstreams

Drag coefficients for droplets and solid spheres in clouds accelerating in airstreams

Date: September 1, 1956
Creator: Ingebo, Robert D
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Drop-size distribution for cross current breakup of liquid jets in airstreams

Drop-size distribution for cross current breakup of liquid jets in airstreams

Date: October 1, 1957
Creator: Ingebo, Robert D & Foster, Hampton H
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Drop-size distributions for impinging-jet breakup in airstreams simulating the velocity conditions in rocket combustors

Drop-size distributions for impinging-jet breakup in airstreams simulating the velocity conditions in rocket combustors

Date: March 1, 1958
Creator: Ingebo, Robert D
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Cloud-droplet ingestion in engine inlets with inlet velocity ratios of 1.0 and 0.7

Cloud-droplet ingestion in engine inlets with inlet velocity ratios of 1.0 and 0.7

Date: January 1, 1956
Creator: Brun, Rinaldo J
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Central automatic data processing system

Central automatic data processing system

Date: April 1, 1958
Creator: unknown
Description: None
Contributing Partner: UNT Libraries Government Documents Department
A cooled-gas pyrometer for use in high-temperature gas streams

A cooled-gas pyrometer for use in high-temperature gas streams

Date: September 1, 1958
Creator: Krause, Lloyd N; Johnson, Robert C & Glawe, George E
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Compressible laminar flow and heat transfer about a rotating isothermal disk

Compressible laminar flow and heat transfer about a rotating isothermal disk

Date: August 1, 1958
Creator: Ostrach, Simon & Thornton, Philip R
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Cross flows in laminar incompressible boundary layers

Cross flows in laminar incompressible boundary layers

Date: February 1, 1956
Creator: Hansen, Arthur G & Herzig, Howard Z
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Approximate solutions of a class of similarity equations for three-dimensional, laminar, incompressible boundary-layer flows

Approximate solutions of a class of similarity equations for three-dimensional, laminar, incompressible boundary-layer flows

Date: September 1, 1958
Creator: Hansen, Arthur G & Herzig, Howard Z
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Crash injury

Crash injury

Date: November 1, 1956
Creator: Pesman, Gerard J & Eiband, Martin A
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Corrosion resistance of nickel alloys in molten sodium hydroxide

Corrosion resistance of nickel alloys in molten sodium hydroxide

Date: January 1, 1958
Creator: Probst, H B; May, C E & Mchenry, Howard T
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Effect of initial mixture temperature on flame speed of methane-air, propane-air and ethylene-air mixtures

Effect of initial mixture temperature on flame speed of methane-air, propane-air and ethylene-air mixtures

Date: May 1, 1951
Creator: Dugger, Gordon L
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Effect of initial mixture-temperature on burning velocity of hydrogen-air mixtures with preheating and simulated preburning

Effect of initial mixture-temperature on burning velocity of hydrogen-air mixtures with preheating and simulated preburning

Date: October 1, 1957
Creator: Heimel, Sheldon
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Effect of bluntness on transition for a cone and a hollow cylinder at Mach 3.1

Effect of bluntness on transition for a cone and a hollow cylinder at Mach 3.1

Date: May 1, 1957
Creator: Brinich, Paul F & Sands, Norman
Description: Bluntness was more effective in displacing transition downstream on a cylinder than on a cone. The downstream displacement of transition is related to the formation of a shock layer within which the Reynolds and Mach numbers are reduced and to pressure gradients that exist over the forward part of the model. Round bluntness in general had a favorable effect, whereas sharp-cornered flat bluntness above a certain size had unfavorable effects on the location of the transition point.
Contributing Partner: UNT Libraries Government Documents Department
Effect of ambient-temperature variation on the matching requirements of inlet-engine combinations at supersonic speeds

Effect of ambient-temperature variation on the matching requirements of inlet-engine combinations at supersonic speeds

Date: January 1, 1957
Creator: Perchonok, Eugene & Hearth, Donald P
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Discharge coefficients for combustor-liner air-entry holes II : flush rectangular holes, step louvers, and scoops

Discharge coefficients for combustor-liner air-entry holes II : flush rectangular holes, step louvers, and scoops

Date: April 1, 1958
Creator: Dittrich, Ralph T
Description: Experimental discharge coefficients for various types of combustor-liner air-entry holes are presented as a function of a dimensionless flow parameter. In general, scoops and step louvers have higher discharge coefficients and wider flow ranges than flush holes. The effects of size or shape of a given type of hole are small. The proximity of multiple flush holes or the wall inclination of a convergent duct has a negligible effect on discharge coefficient.
Contributing Partner: UNT Libraries Government Documents Department
Discharge coefficients for combustor-liner air-entry holes

Discharge coefficients for combustor-liner air-entry holes

Date: April 1, 1956
Creator: Dittrich, Ralph T & Graves, Charles C
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Effect of environments of sodium hydroxide, air, and argon on the stress-rupture properties of nickel at 1500 F

Effect of environments of sodium hydroxide, air, and argon on the stress-rupture properties of nickel at 1500 F

Date: January 1, 1958
Creator: Mchenry, Howard T & Probst, H B
Description: None
Contributing Partner: UNT Libraries Government Documents Department
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