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  Partner: UNT Libraries Government Documents Department
 Serial/Series Title: NACA Research Memorandums
 Collection: Technical Report Archive and Image Library
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
Free-flight Investigation at Transonic Speeds of the Stability Characteristics of a Tailless Missile Configuration Having a 45 Deg Sweptback Wing of Aspect Ratio 4

Free-flight Investigation at Transonic Speeds of the Stability Characteristics of a Tailless Missile Configuration Having a 45 Deg Sweptback Wing of Aspect Ratio 4

Date: August 28, 1956
Creator: Arbic, R. G.
Description: Free flight test of tailless missile configuration with 45-deg sweptback wing of aspect ratio 4 - stability at transonic speeds.
Contributing Partner: UNT Libraries Government Documents Department
Effect of Control Trailing-edge Thickness or Aspect Ratio on the Oscillating Hinge-moment and Flutter Characteristics of a Flaptype Control at Transonic Speeds

Effect of Control Trailing-edge Thickness or Aspect Ratio on the Oscillating Hinge-moment and Flutter Characteristics of a Flaptype Control at Transonic Speeds

Date: April 23, 1958
Creator: Moseley, W. C., Jr. & Thompson, R. F.
Description: Control trailing-edge thickness and aspect ratio effect on oscillating hinge-moment and flutter characteristics of flap-type controls.
Contributing Partner: UNT Libraries Government Documents Department
Investigation of an Air-cooled, Plug-type, Variable-area Exhaust Nozzle

Investigation of an Air-cooled, Plug-type, Variable-area Exhaust Nozzle

Date: April 10, 1957
Creator: Koffel, W. K. & Smolak, G. R.
Description: Investigation of air-cooled, plug-type, variable- area exhaust nozzle at high temperature.
Contributing Partner: UNT Libraries Government Documents Department
Investigation of a 0.6 Hub-tip Radius-ratio Transonic Turbine Designed for Secondary-flow Study. Iii - Experimental Performance With Two Stator Configurations Designed to Eliminate Blade Wakes and Secondary-flow Effects and Conclusions From Entire Stator Investigation

Investigation of a 0.6 Hub-tip Radius-ratio Transonic Turbine Designed for Secondary-flow Study. Iii - Experimental Performance With Two Stator Configurations Designed to Eliminate Blade Wakes and Secondary-flow Effects and Conclusions From Entire Stator Investigation

Date: September 17, 1957
Creator: Moffitt, T. P.; Rohlik, H. E. & Wintucky, W. T.
Description: Hub-tip radius ratio transonic turbine for secondary flow - stator configurations designed to eliminate blade wakes and secondary-flow effects.
Contributing Partner: UNT Libraries Government Documents Department
Heat Transfer in Regions of Separated and Reattached Flows

Heat Transfer in Regions of Separated and Reattached Flows

Date: June 10, 1957
Creator: Crawford, D. H. & Rumsey, C. B.
Description: Heat transfer in regions of separated and reattached flows.
Contributing Partner: UNT Libraries Government Documents Department
Comparison of Injectors With a 200-pound-thrust Ammonia-oxygen Engine

Comparison of Injectors With a 200-pound-thrust Ammonia-oxygen Engine

Date: September 4, 1958
Creator: Clark, B. J. & Priem, R. J.
Description: Injection techniques for 200-pound thrust ammonia- oxygen rocket engine.
Contributing Partner: UNT Libraries Government Documents Department
Flight Investigation of Pentaborane Fuel in 9.75-inch-diameter Ram-jet Engine With Downstream Fuel Injection

Flight Investigation of Pentaborane Fuel in 9.75-inch-diameter Ram-jet Engine With Downstream Fuel Injection

Date: April 22, 1957
Creator: Disher, J. H. & Jones, M. L.
Description: Flight investigation of pentaborane fuel in 9.75- inch-diameter ramjet engine with downstream fuel injection.
Contributing Partner: UNT Libraries Government Documents Department
Experimental Study of Ballistic-Missile Base Heating with Operating Rocket

Experimental Study of Ballistic-Missile Base Heating with Operating Rocket

Date: September 23, 1958
Creator: Nettle, J. Cary
Description: A rocket of the 1000-pound-thrust class using liquid oxygen and JP-4 fuel as propellant was installed in the Lewis 8- by 6-foot tunnel to permit a controlled study of some of the factors affecting the heating of a rocket-missile base. Temperatures measured in the base region are presented from findings of three motor extension lengths relative to the base. Data are also presented for two combustion efficiency levels in the rocket motor. Temperature as high as 1200 F was measured in the base region because of the ignition of burnable rocket gases. combustibles that are dumped into the base by accessories seriously aggravate the base-burning temperature rise.
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