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Performance of JP-4 Fuel With Fluorine-Oxygen Mixtures in 1000-Pound-Thrust Rocket Engines
Memorandum presenting seven injectors of four different types that were tested for use with JP-4-oxygen-fluorine propellant combinations. By using the best of the injectors, high characteristic velocities were obtained over the complete range of 0- to 70-percent fluorine in the oxidant. Results regarding injector performance, heat rejection, injector with triplet-jet elements in skewed array, and fluorine addition are provided.
Date:
June 11, 1958
Creator:
Nored, Donald L. & Douglass, Howard W.
System:
The UNT Digital Library
Drag and Static Stability at Low Lift of Rocket-Powered Models of the Convair MX-1626 Airplane at Mach Numbers From 0.7 to 1.5
Report presenting flight testing on models of the proposed Consolidated Vultee Aircraft Corporation MX-1626 airplane with nacelles and without nacelles. Results regarding drag level, design modifications, dampening, trimming, and the use of ventral boosters are provided.
Date:
June 11, 1953
Creator:
Hall, James R. & Hopko, Russell N.
System:
The UNT Digital Library
Effect of Dissociation on Exhaust-Nozzle Performance
Memorandum presenting net jet thrusts for stoichiometric hydrocarbon-air, hydrogen-air and pentaborane-air mixtures for equilibrium and frozen expansion in the exhaust nozzle at flight Mach numbers up to 10. Net jet thrusts for equilibrium flow were three to five times that for frozen flow at Mach 10 for the three fuels cited, a hydrocarbon, hydrogen, and pentaborane. Results regarding dissociation energies, reaction rate, residence time, and estimated minimum performance are provided.
Date:
June 11, 1958
Creator:
Reynolds, T. W.
System:
The UNT Digital Library
Effect of pressure level on afterburner-wall temperatures
Report presenting an investigation conducted on a full-scale afterburner and turbojet engine to determine the effect of pressure level on afterburner-wall temperature. For a given ratio of cooling airflow to afterburner gas flow, the afterburner-wall temperature increased as afterburner-outlet pressure was increased. The results indicated that heat transfer by luminous radiation was not significant any pressure level investigated.
Date:
June 11, 1958
Creator:
Shillito, Thomas B. & Smolak, George R.
System:
The UNT Digital Library
Low-speed longitudinal aerodynamic characteristics of a twisted and cambered wing of 45 degree sweepback and aspect ratio 8 with and without high-lift and stall-control devices and a fuselage at Reynolds numbers from 1.5 x 10(exp 6) to 4.8 x 10(exp 6
Report presenting a low-speed investigation of the static longitudinal aerodynamic characteristics of a twisted and cambered wing with 45 degrees of sweepback and an aspect ratio of 8.0 in the 19-foot pressure tunnel. Testing included the effects of leading- and trailing-edge flaps, flow control fences, and a fuselage. Report presenting longitudinal stability characteristics, lift characteristics, drag characteristics, fuselage effects, Reynolds number effects, effect of wing roughness are provided.
Date:
June 11, 1952
Creator:
Salmi, Reino J.
System:
The UNT Digital Library
A Transonic Investigation by the Free-Fall Method of an Airplane Configuration Having 45 Degrees Sweptback Wing and Tail Surfaces
Report presenting a free-fall investigation of airplanes in the transonic range using a configuration with 45 degree sweptback wing and tail surfaces. The lift, drag, and longitudinal static and dynamic stability and control characteristics were obtained at a range of operating lift coefficients and Mach numbers.
Date:
June 11, 1953
Creator:
Faber, Stanley & Eggleston, John M.
System:
The UNT Digital Library
Experimental investigation of the zero-lift drag of a fin-stabilized body of fineness ratio 10 at Mach numbers between 0.6 and 10
Report presenting free-flight measurements of the zero-lift drag of a cruciform-finned body at a range of Mach and Reynolds numbers. Results regarding experimental total drag, comparison of theory with experiment, comparison of experiment with NOL results, boundary-layer transition, Reynolds number effects, and fin leading-edge shape are provided.
Date:
June 11, 1953
Creator:
James, Carlton S. & Carros, Robert J.
System:
The UNT Digital Library
Effect of pressure level on afterburner-wall temperatures
Report presenting an investigation conducted on a full-scale afterburner and turbojet engine to determine the effect of pressure level on afterburner-wall temperature. The purpose behind the investigation was to investigate the idea that luminous radiation from nongaseous substances in the afterburner gas stream might be present and vary significantly with pressure.
Date:
June 11, 1958
Creator:
Shillito, Thomas B. & Smolak, George R.
System:
The UNT Digital Library
Effect of Dissociation on Exhaust-Nozzle Performance
Memorandum presenting net jet thrusts for stoichiometric hydrocarbon-air, hydrogen-air and pentaborane-air mixtures for equilibrium and frozen expansion in the exhaust nozzle at flight Mach numbers up to 10. Examinations of the dissociation products involved and the energies associated with them, for the hydrocarbon- and hydrogen-air mixtures indicated that a major portion of the dissociation energy for the hydrocarbon mixture is involved in the carbon monoxide molecule.
Date:
June 11, 1958
Creator:
Reynolds, T. W.
System:
The UNT Digital Library
Performance of JP-4 fuel with fluorine-oxygen mixtures in 1000-pound-thrust rocket engines
Report presenting seven injectors of four different types tested for use with JP-4-oxygen-fluorine propellant combinations. High characteristics velocities were obtained over the complete range of 0- to 70-percent fluorine in the oxidant. Results regarding the injector performance, heat rejection, injector with triplet-jet elements in skewed array, and fluorine addition are provided.
Date:
June 11, 1958
Creator:
Nored, Donald L. & Douglass, Howard W.
System:
The UNT Digital Library
Longitudinal Stability Characteristics of the Consolidated Vultee XFY-1 Airplane with Windmilling Propellers as Obtained from Flight of 0.133-Scale Rocket-Propelled Model at Mach Numbers from 0.70 to 1.13
From Summary: "A flight test has been conducted to determine the longitudinal stability and control characteristics of a 0.133-scale model of the Consolidated Vultee XFY-1 airplane with windmilling propellers for the Mach number range between 0.70 and 1.13. The variation of lift-curve slope C(sub L(sub alpha) with Mach number was gradual with a maximum value of 0.074 occurring at a Mach number of 0.97. Propellers had little effect upon the values of lift-curve slope or the linearity of lift coefficient with angle of attack."
Date:
June 11, 1954
Creator:
Hastings, Earl C., Jr. & Mitcham, Grady L.
System:
The UNT Digital Library