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 Collection: National Advisory Committee for Aeronautics Collection
Experimental investigation of air-cooled turbine blades in turbojet engine.  2:  Rotor blades with 15 fins in cooling-air passages

Experimental investigation of air-cooled turbine blades in turbojet engine. 2: Rotor blades with 15 fins in cooling-air passages

Date: August 1, 1950
Creator: Hickel, R. O. & Ellerbrock, H. H., Jr.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Experimental Investigation of Effects of Combustion-chamber Length and Inlet Total Temperature, Total Pressure, and Velocity on Afterburner Performance

Experimental Investigation of Effects of Combustion-chamber Length and Inlet Total Temperature, Total Pressure, and Velocity on Afterburner Performance

Date: June 3, 1957
Creator: King, C. R.
Description: Afterburner combustion efficiency - effects of chamber length, temperature, pressure and velocity.
Contributing Partner: UNT Libraries Government Documents Department
Experimental investigation of diffuser pressure ratio control with shock positioning limit on 28 inch ram-jet engine

Experimental investigation of diffuser pressure ratio control with shock positioning limit on 28 inch ram-jet engine

Date: January 15, 1957
Creator: Crowl, R. J.; Dunbar, W. R. & Wentworth, C. B.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Experimental performance of a 5000-pound- thrust rocket chamber using a 20-percent- fluorine - 80-percent-oxygen mixture with RP-1

Experimental performance of a 5000-pound- thrust rocket chamber using a 20-percent- fluorine - 80-percent-oxygen mixture with RP-1

Date: April 24, 1957
Creator: Kutina, F. J., Jr.; Rothenberg, E. A. & Tomazic, W. A.
Description: Increased performance of rocket engine using fluorine-oxygen mixture with RP-1 fuel.
Contributing Partner: UNT Libraries Government Documents Department
Experimental investigation of air-cooled turbine blades in turbojet engine.  1:  Rotor blades with 10 tubes in cooling-air passages

Experimental investigation of air-cooled turbine blades in turbojet engine. 1: Rotor blades with 10 tubes in cooling-air passages

Date: July 30, 1950
Creator: Ellerbrock, H. H., Jr. & Stepka, F. S.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Experimental investigation of extreme internal flow turning at the cowl lip of an axisymetric inlet at a Mach number of 2.95

Experimental investigation of extreme internal flow turning at the cowl lip of an axisymetric inlet at a Mach number of 2.95

Date: May 13, 1958
Creator: Kowalski, K. L. & Weston, K. C.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Experimental Sea-level Static Investigation of a Short Afterburner

Experimental Sea-level Static Investigation of a Short Afterburner

Date: May 11, 1954
Creator: Harp, J. L., Jr.; Mallett, W. E. & Shillito, T. B.
Description: Sea-level static testing of turbojet engine afterburner.
Contributing Partner: UNT Libraries Government Documents Department
Exploratory Investigation of Performance of Experimental Fuelrich Hydrogen Combustion System

Exploratory Investigation of Performance of Experimental Fuelrich Hydrogen Combustion System

Date: June 25, 1958
Creator: Grobman, J. S. & Smith, A. L.
Description: Exploratory investigation of performance characteristics of fuel-rich hydrogen combustor.
Contributing Partner: UNT Libraries Government Documents Department
Flight investigation of a liquid hydrogen fuel system

Flight investigation of a liquid hydrogen fuel system

Date: August 19, 1957
Creator: Acker, L. W.; Christenson, H. H.; Gough, W. V. & Mulholland, D. R.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Performance of an Inlet Having a Variable-angle Two-dimensional Compression Surface and a Fixed-geometry Subsonic Diffuser for Application to Reduced Engine Rotative Speeds- Mach Numbers 0.66, 1.5, 1.7, and 2.0

Performance of an Inlet Having a Variable-angle Two-dimensional Compression Surface and a Fixed-geometry Subsonic Diffuser for Application to Reduced Engine Rotative Speeds- Mach Numbers 0.66, 1.5, 1.7, and 2.0

Date: January 30, 1958
Creator: Allen, J. L.
Description: Air inlet for turbojet engines having variable angle two-dimensional compression surface and fixed-geometry subsonic diffuser.
Contributing Partner: UNT Libraries Government Documents Department
Performance of an All-internal Conical Compression Inlet With Annular Throat Bleed at Mach Number 5.0

Performance of an All-internal Conical Compression Inlet With Annular Throat Bleed at Mach Number 5.0

Date: August 6, 1958
Creator: Obery, L. J. & Stitt, L. E.
Description: Internal compression inlet with throat bleed-off at hypersonic flow.
Contributing Partner: UNT Libraries Government Documents Department
Performance of an isentropic, all-internal- contraction, axisymmetric inlet designed for mach 2.50

Performance of an isentropic, all-internal- contraction, axisymmetric inlet designed for mach 2.50

Date: September 15, 1958
Creator: Anderson, B. H. & Bowditch, D. N.
Description: Performance of internal contraction, axisymmetric inlet with isentropic compression surfaces on cowl and centerbody at Mach 2.0 to 2.7.
Contributing Partner: UNT Libraries Government Documents Department
Performance of JP-4 fuel with fluorine- oxygen mixtures in 1000-pound-thrust rocket engines

Performance of JP-4 fuel with fluorine- oxygen mixtures in 1000-pound-thrust rocket engines

Date: June 11, 1958
Creator: Douglass, H. W. & Nored, D. L.
Description: Fluorine-liquid oxygen mixture and injector design effects on JP-4 jet fuel performance in rocket engines.
Contributing Partner: UNT Libraries Government Documents Department
Performance of five short multielement turbojet combustors for hydrogen fuel in quarter-annulus duct

Performance of five short multielement turbojet combustors for hydrogen fuel in quarter-annulus duct

Date: July 22, 1958
Creator: Jones, R. E. & Rayle, W. D.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Performance of Isentropic Nose Inlets at Mach Number of 5.6

Performance of Isentropic Nose Inlets at Mach Number of 5.6

Date: May 6, 1954
Creator: Bernstein, H. & Haefeli, R. C.
Description: Isentropic nose inlet performance at mach 5.6.
Contributing Partner: UNT Libraries Government Documents Department
Performance of several half-conical side inlets at supersonic and subsonic speeds

Performance of several half-conical side inlets at supersonic and subsonic speeds

Date: February 1, 1956
Creator: Cubbison, R. W.; Flaherty, R. J. & Stitt, L. E.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Performance of twin-duct variable-geometry side inlets at mach numbers of 1.5 to 2.0

Performance of twin-duct variable-geometry side inlets at mach numbers of 1.5 to 2.0

Date: January 21, 1957
Creator: Beheim, M. A.; Klann, J. L. & Yeager, R. A.
Description: Supersonic wind tunnel test of twin-duct variable geometry side inlets.
Contributing Partner: UNT Libraries Government Documents Department
Performance of Pentaborane, Pentaborane - Jp-4 Fuel Mixtures, and Trimethylborate Azeotrope Fuel in a Full-scale Turbojet Engine

Performance of Pentaborane, Pentaborane - Jp-4 Fuel Mixtures, and Trimethylborate Azeotrope Fuel in a Full-scale Turbojet Engine

Date: November 20, 1956
Creator: Breitwieser, R. & Useller, J. W.
Description: Full scale turbojet engine testing of fuels - pentaborane-jp-4 mixtures and trimethylborate azeotrope performance.
Contributing Partner: UNT Libraries Government Documents Department
Performance of Variable Two-dimensional Inlet Designed for Engine-inlet Matching. I - Performance at Design Mach Number of 3.07

Performance of Variable Two-dimensional Inlet Designed for Engine-inlet Matching. I - Performance at Design Mach Number of 3.07

Date: November 20, 1956
Creator: Beheim, M. A. & Gertsma, L. W.
Description: Supersonic performance of variable two-dimensional inlets designed for engine-inlet matching.
Contributing Partner: UNT Libraries Government Documents Department
High altitude performance investigation of J65-B-3 turbojet engine with both JP-4 and gaseous hydrogen fuels

High altitude performance investigation of J65-B-3 turbojet engine with both JP-4 and gaseous hydrogen fuels

Date: April 2, 1957
Creator: Kaufman, H. R.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
High mach number, low-cowl-drag, external- compression inlet with subsonic dump diffuser

High mach number, low-cowl-drag, external- compression inlet with subsonic dump diffuser

Date: May 12, 1958
Creator: Connors, J. F. & Flaherty, R. J.
Description: Low cowl drag, external compression inlet with subsonic dump diffuser for high Mach number application.
Contributing Partner: UNT Libraries Government Documents Department
High-altitude performance of J71-A-11 turbojet engine and its components using JP-4 and gaseous-hydrogen fuels

High-altitude performance of J71-A-11 turbojet engine and its components using JP-4 and gaseous-hydrogen fuels

Date: May 29, 1957
Creator: Saari, M. J. & Smith, I. D.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Influence of boric oxide deposition on turbojet-engine operation

Influence of boric oxide deposition on turbojet-engine operation

Date: February 15, 1957
Creator: Burley, R. R.; Useller, J. W. & Velie, W. W.
Description: Influence of boric oxide deposition on turbojet engine operation.
Contributing Partner: UNT Libraries Government Documents Department
Interference effects of fuselage-stored missiles on inlet duct model of an interceptor-type aircraft at Mach numbers 1.5 to 1.9

Interference effects of fuselage-stored missiles on inlet duct model of an interceptor-type aircraft at Mach numbers 1.5 to 1.9

Date: April 24, 1957
Creator: Davis, O. H. & Piercy, T. G.
Description: None
Contributing Partner: UNT Libraries Government Documents Department