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Performance of a short combustor at high altitudes using hydrogen fuel

Description: Performance characteristics of a 16-inch annular-type combustor installed in a full-scale engine using gaseous-hydrogen fuel were obtained at simulated altitudes from 66,000 to 86,000 feet at a flight Mach number of 0.8. Combustion efficiencies of 86 percent were obtained at 86,000 feet (combustor pressure, 420 lb/sq ft abs). Combustor blowout was not encountered during the investigation.
Date: August 7, 1956
Creator: Sivo, Joseph N. & Fenn, David B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

A study of a missile designed to fly at low speed with its longitudinal axis aligned with the flight path

Description: An experimental investigation to explore the practicability of a low-speed missile designed to fly with its longitudinal axis pointing along the flight path. The wing and tail surfaces were arranged in a cruciform pattern and the incidence was selected to trim the missile at the desired normal-force coefficient with the body at 0 degrees angle of attack. Results regarding the description of a self-balancing missile and experimental results are provided.
Date: February 7, 1956
Creator: Hopkins, Edward J. & Sorensen, Norman E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Aerodynamic Characteristics of a 0.04956-Scale Model of the Convair F-102B Airplane at Mach Numbers of 1.41, 1.61, and 2.01: Coord No. AF-231

Description: Report discussing testing of a scale model of the Convair F-102B to determine its aerodynamic characteristics at several Mach numbers. Four basic body modifications and two afterbody configurations were evaluated.The body modifications were all found to slightly reduce values of minimum drag, but did not cause a change in the static stability and lift-curve-slope values compared to the F-102A.
Date: February 7, 1956
Creator: Driver, Cornelius & Robinson, Ross B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Data From Large-Scale Low-Speed Tests of Airplane Configurations With a Thin 45 Degree Swept-Wing Incorporating Several Leading-Edge Contour Modifications

Description: Memorandum presenting force tests that have been made of airplane configurations with a thin swept wing incorporating several wing-contour modifications forward of maximum thickness. Both longitudinal and lateral characteristics are provided.
Date: May 7, 1956
Creator: Evans, William T.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Theoretical performance of JP-4 fuel and liquid oxygen as a rocket propellant 2: equilibrium composition

Description: Data were calculated for equivalence ratios of 1 to 3, chamber pressures of 300 and 600 pounds per square inch absolute, and pressure ratios of 1 to 1500. Parameters included are specific impulse, combustion and exit temperature, molecular weight, characteristic velocity, coefficient of thrust, ratio of nozzle-exit area to throat area, specific heat at constant pressure, isentropic exponent, viscosity, and thermal conductivity. A correlation is given which permits determination of performance f… more
Date: September 7, 1956
Creator: Huff, Vearl N.; Fortini, Anthony & Gordon, Sanford
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

A simulator study of some longitudinal stability and control problems of a piloted aircraft in flights to extreme altitude and high speed

Description: Report presenting a brief study utilizing pilots to fly a simulator of some longitudinal stability and control problems of an assumed aircraft capable of flights to altitudes essentially out of the atmosphere. The results show that more than the inherent longitudinal damping of the aircraft is necessary to affect a safe flight, particularly during entry into the atmosphere. Results regarding some preliminary considerations, entry, and control in ascent and the ballistics trajectory are provided. more
Date: September 7, 1956
Creator: Matthews, Howard F. & Merrick, Robert B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Turbojet Performance and Operation at High Altitudes With Hydrogen and JP-4 Fuels

Description: Two current turbojet engines were operated with gaseous-hydrogen and JP-4 fuels at very high altitudes and a simulated Mach number of 0.8. With gaseous hydrogen as the fuel stable operation was obtained at altitudes up to the facility limit of about 90,000 feet and the specific fuel consumption was only 40 percent of that with JP-4 fuel. With JP-4 as the fuel combustion was unstable at altitudes above 60,000 to 65,000 feet and blowout limits were reached at 75,000 to 80,000 feet. Over-all perfo… more
Date: August 7, 1956
Creator: Fleming, W. A.; Kaufman, H. R.; Harp, J. L., Jr. & Chelko, L. J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Wind-tunnel investigation of the damping in roll of the Douglas D-558-II research airplane and its components at supersonic speeds

Description: Experimental values of damping in roll at zero angle of attack of the Douglas D-558-II research airplane and its components have been obtained at five different Mach numbers. Large effects of Reynolds number, boundary layer, and wing-incidence angle on the damping in roll were obtained.
Date: September 7, 1956
Creator: McDearmon, Russell W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Effect of wing camber and twist at Mach numbers from 1.4 to 2.1 on the lift, drag, and longitudinal stability of a rocket-powered model having a 52.5 degree sweptback wing of aspect ratio 3 and inline tail surfaces

Description: Report presenting a free-flight investigation to determine the effect of wing camber and twist at Mach numbers from 1.4 to 2.1 on the lift, drag, and longitudinal stability of a configuration with 52.5 degrees sweptback wing of aspect ratio 3, and inline tail surfaces. Results regarding drag, total normal force and pitching moment, and wash at the horizontal tail are provided.
Date: May 7, 1956
Creator: Gillespie, Warren, Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Lift, drag, and static longitudinal stability characteristics of configurations consisting of three triangular wing panels and a body of equal length at Mach numbers from 3.00 to 6.28

Description: Report presenting lift, drag, and pitching-moment coefficients, lift-drag ratios, and center-of-pressure positions for three highly swept three-wing tailless configurations determined from tests at a range of Mach numbers and angles of attack.
Date: February 7, 1956
Creator: Savin, Raymond C. & Wong, Thomas J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Minimum Drag of Four Versions of a Swept-Wing Fighter Airplane Obtained From Flight Tests of Rocket-Boosted Models at Mach Numbers From 0.81 to 1.71

Description: Memorandum presenting tests conducted with four specific versions of a swept-wing fighter airplane, which indicate that a large reduction in external-drag coefficient was accomplished by redesigning the original configuration. The forebody modifications, which consisted of a smaller canopy, slimmer nose, and sharper inlet lip, reduced the value of the external-drag coefficient from 0.044 to 0.042 at a Mach number of 1.05 and from 0.042 to 0.040 at a Mach number of 1.28.
Date: September 7, 1956
Creator: Hastings, Earl C., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Performance of a Short Combustor at High Altitudes Using Hydrogen Fuel

Description: Report presenting an investigation in the altitude test chamber to evaluate the performance of a 16-inch-long combustor designed for use with gaseous-hydrogen fuel. The investigation covered a range of combustor pressures and simulated altitudes at Mach number 0.8. Results regarding operational characteristics, combustor performance, and temperature profiles are provided.
Date: August 7, 1956
Creator: Sivo, Joseph N. & Fenn, David B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Turbojet Performance and Operation at High Altitudes With Hydrogen and JP-4 Fuels

Description: An investigation of the effect of extremely high altitude operation on the performance and operating characteristics of two turbojet engines using gaseous hydrogen and JP-4 fuels. At extremely high altitude conditions, engine performance was significantly poorer than at low altitudes. The majority of performance losses were due to the compressor because of low Reynolds number and the combustor because of low combustion efficiency.
Date: August 7, 1956
Creator: Fleming, W. A.; Kaufman, H. R.; Harp, J. L., Jr. & Chelko, L. J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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