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open access

Preliminary Evaluation of Flight-Weight XRJ47-W-5 Ram-Jet Engine at a Mach Number of 2.75

Description: Report presenting a free-jet investigation of the performance, burner-shell cooling, and ignition characteristics of a flight-weight 48-inch-diameter XRJ47-W-5 ramjet engine at an inlet Mach number of 2.75 and an angle of attack of 3 degrees. Data were obtained over a range of altitudes, inlet temperatures, and fuel-air ratios.
Date: July 26, 1955
Creator: Welna, Harry J. & Reilly, Dwight H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Combustion of gaseous hydrogen at low pressures in a 35 degree sector of a 28-inch-diameter ramjet combustor

Description: Report presenting testing of gaseous hydrogen fuel burned in a connected-pipe combustor with a cross section equal to 35 degrees sector of a 28-inch diameter. Eleven shrouded fuel-injector configurations were used to obtain combustion data at specified high-altitude ramjet combustor conditions. Results regarding shroud air blockage, mixing tabs, higher equivalence-ratio burning, injector size, flameholder durability, burner length, combustion efficiency, and temperature profile are provided.
Date: April 22, 1958
Creator: Kerslake, William R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Altitude Performance of a Turbojet Engine Using Pentaborane Fuel

Description: Memorandum presenting a turbojet engine with a two-stage turbine operated with pentaborane fuel continuously for 11.5 minutes at a simulated altitude of 55,000 feet at a flight Mach number of 0.8. The engine incorporated an NACA combustor designed specifically for use with pentaborane fuel. Results regarding oxide formation and deposition, engine operating point, effect of oxide deposits on component performance, effect of oxide deposition on overall performance, and some operational comments a… more
Date: May 20, 1957
Creator: Sivo, Joseph N.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

A Low-Pressure-Loss Short Afterburner for Sea-Level Thrust Augmentation

Description: Memorandum presenting an investigation of the problems associated with the design of a low-pressure-loss, short afterburner for sea-level thrust augmentation in a static, sea-level test stand. Results regarding diffuser pressure losses, afterburner pressure losses, and afterburner performance are provided.
Date: June 7, 1955
Creator: Ciepluch, Carl C.; Velie, Wallace W. & Burley, Richard R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

The results of wind-tunnel tests to a Mach number of 0.90 of a four-engine, propeller-driven airplane configuration having a wing with 40 degrees of sweepback and an aspect ratio of 10

Description: Report presenting a wind-tunnel investigation to provide data for the study of the effects of operating propellers on the longitudinal characteristics of a four-engine tractor airplane configuration with a wing of 40 degrees of sweepback and an aspect ratio of 10. Coefficients of lift, longitudinal force, pitching moment, propeller thrust, and propeller power are presented in tabular form for various values of advance ratio at constant angles of attack.
Date: September 1956
Creator: Edwards, George G.; Dickson, Jerald K.; Sutton, Fred B. & Demele, Fred A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Performance at Simulated High Altitudes of a Prevaporizing Annular Turbojet Combustor Having Low Pressure Loss

Description: Memorandum presenting an investigation conducted to reduce the pressure drop in an experimental combustor designed to operate with high efficiencies at high altitude. The combustor utilized a previously designed prevaporizing fuel system that supplied vapor fuel to the injectors for high-altitude operation. Results regarding combustor development and performance of final combustor model 47L are provided.
Date: December 6, 1956
Creator: Norgren, Carl T.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

A Method for Prevention of Screaming in Rocket Engines

Description: From Summary: "Lateral and longitudinal combustion-pressure oscillations that occurred in screaming combustion of a 1000-pound-thrust rocket engine using white fuming nitric acid and JP-4 fuel as propellants were successfully prevented by means of longitudinal fins in the combustion chamber. Fin position was critical, and complete attenuation was achieved only when the fins were located in a zone approximately 8 to 16 inches from the injector. Fins located in other zones, that is, near the inje… more
Date: August 19, 1954
Creator: Male, Theodore & Kerslake, William R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Investigation of an on-off inlet shock-position control on a 16-inch ram-jet engine

Description: Report presenting an investigation of a shock-positioning control on a 16-inch ramjet engine at a range of Mach numbers and angles of attack in the supersonic wind tunnel. The control operated at all conditions under which the engine could be manually operated. Prediction of the control-system dynamic behavior can be applied by treating the system as having pure dead time.
Date: November 29, 1954
Creator: Wilcox, Fred A.; Perchonok, Eugene & Hearth, Donald P.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Performance of a 28-Inch Ramjet Utilizing Gaseous Hydrogen at a Mach Number of 3.6, Angles of Attack Up to 12 Degrees, and Pressure Altitudes Up to 110,000 Feet

Description: Memorandum presenting an investigation conducted in the 10- by 10-foot supersonic wind tunnel to evaluate the performance of a shrouded injector burner with perforated domes employed in a 28-inch ramjet using gaseous hydrogen as fuel. Steady-state data were obtained at a pressure altitude of 77,000 feet and zero angle of attack. Results of the investigation showed that burning could be initiated under severe distortion conditions and that satisfactory combustor operation was accomplished up to … more
Date: May 19, 1958
Creator: Musial, Norman T.; Ward, James J. & Wasserbauer, Joseph F.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

An Acceleration Schedule Control for Accelerating a Turbojet Engine and Its Use With a Speed Control

Description: Memorandum presenting a study of an acceleration-limiting control on a turbojet engine in order to determine its feasibility as an acceleration control. A proportional-plus-integral type of controller was used in the investigation. Results regarding the one-loop control and two-loop control are provided.
Date: May 12, 1958
Creator: Gerus, Theodore F.; Powers, Albert G. & Heppler, Herbert J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Afterburner Performance With Combustion-Chamber Lengths From 10 to 62 Inches at Several Afterburner-Inlet Temperatures

Description: Effect of variation of combustion chamber length and inlet temperature on low pressure-loss sea level afterburner. A 70-percentage-point reduction in combustion efficiency resulted when the combustion-chamber length was reduced from 62 to 10 inches.
Date: February 1, 1956
Creator: Ciepluch, Carl C.; Velie, Wallace W. & Burley, Richard R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Low-Pressure Performance of a Tubular Combustor With Gaseous Hydrogen

Description: Memorandum presenting an investigation to determine the combustion performance characteristics of gaseous hydrogen fuel in a single tubular turbojet combustor. The combustor was operated over a range of inlet-air pressures from 3.3 to 14.3 inches of mercury absolute. Results regarding stability limits and combustion efficiency are provided.
Date: May 9, 1955
Creator: Jonash, Edmund R.; Smith, Arthur L. & Hlavin, Vincent F.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Investigation of Afterburner Combustion Screech and Methods of Its Control at High Combustor Pressure Levels

Description: Memorandum presenting an experimental investigation of various methods for the control of afterburner combustion screech at afterburner-inlet total pressures from 4000 to 6400 pounds per square foot absolute. Generally, the range of afterburner fuel-air ratios in which screech occurred and the intensity of screech did not vary appreciably in the range of pressures covered.
Date: May 14, 1956
Creator: Trout, Arthur M.; Koffel, William K. & Smolak, George R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Preliminary Report on Experimental Investigation of Engine Dynamics and Controls for a 48-Inch Ramjet Engine

Description: Experimental investigation of engine dynamics and controls for 48-inch ramjet engine in free jet facility at Mach number 2.76 and altitudes 68,000 to 82,000 feet. The engine data presented include steady-state performance, indical response, frequency response, and ignition characteristics. Ignition data are presented for representative fuel-air ratios which show that the normal shock overshoots its final position by several feet during ignition transients.
Date: March 16, 1956
Creator: Vasu, George; Hart, Clint E. & Dunbar, William R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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