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Analysis of Rocket, Ramjet, Turbojet Engines for Supersonic Propulsion of Long-Range Missiles 2: Rocket Missile Performance

Description: Memorandum presenting an investigation of the theoretical performance of a two-stage ballistic rocket missile with a centerbody and two parallel boosters for JP4-oxygen and ammonia-fluorine propellants. The missile using the ammonia-fluorine propellant weighs about one-half as much as a missile using JP4-oxygen. Results regarding the optimum missile and effect of variation of design parameters are provided.
Date: October 11, 1954
Creator: Huff, Vearl N. & Kerrebrock, Jack
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Effects of Secondary-Air Flow on Annular Base Force of a Supersonic Airplane

Description: Memorandum presenting an investigation of the effect of base bleed on the base force of a supersonic-interceptor model in the 8- by 6-foot supersonic wind tunnel. Generally, base pressures greater than ambient were obtained at the engine operating pressure ratios of the primary nozzle.
Date: October 11, 1954
Creator: Vargo, Donald J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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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

Description: 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 coe… more
Date: June 11, 1954
Creator: Hastings, Earl C., Jr. & Mitcham, Grady L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Longitudinal Stability and Control Characteristics at Transonic Speeds of a 1/30-Scale Model of the Republic XF-103 Airplane

Description: The longitudinal stability and control characteristics of a 1/30-scale model of the Republic XF-103 airplane were investigated in the Langley 8-foot transonic tunnel. The effect of speed brakes located at the end of the fuselage was also investigated. The main part of the investigation was made with internal flow in the model, but some data were obtained with no internal flow. The longitudinal stability and control at transonic-speeds appeared satisfactory. The transonic drag rise was small. Th… more
Date: August 11, 1954
Creator: Luoma, Arvo A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Aerodynamic Characteristics of a Circular Cylinder at Mach Number 6.86 and Angles of Attack Up to 90 Degrees

Description: "Pressure-distribution and force tests of a circular cylinder have been made in the Langley 11-inch hypersonic tunnel at a Mach number of 6.86, a Reynolds number of 129,000 based on diameter, and angles of attack up to 90 degrees. The results are compared with the hypersonic approximation of Grimminger, Williams, and Young and with a simple modification of the Newtonian flow theory. The comparison of experimental results shows that either theory gives adequate general aerodynamic characteristic… more
Date: March 11, 1954
Creator: Penland, Jim A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Effects of Secondary-Air Flow on Annular Base Force of a Supersonic Airplane

Description: Memorandum presenting an investigation of the effect of base bleed on the base force of a supersonic-interceptor model in the 8- by 6-foot supersonic wind tunnel. Two groups of fixed-geometry nozzles and shroud combinations simulating double-iris-type configurations were evaluated over a range of secondary to primary exit-diameter ratios.
Date: October 11, 1954
Creator: Vargo, Donald J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Analytical and experimental studies of a divided-flow ram-jet combustor

Description: From Introduction: "The investigation reported herein is a continuation of a ram-jet-combustor design program being conducted at the NACA Lewis laboratory. The purpose of this broad program is to establish basic design criteria for combustors operating over wide range of fuel-air ratio with low pressure losses and high combustion efficiency, and to utilize these design criteria in the development of practical ram-jet combustors."
Date: January 11, 1954
Creator: Dangle, E. E.; Friedman, Robert & Cervenka, Adolph J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Design and Test of Mixed-Flow Impellers 4: Experimental Results for Impeller Models MF-1 and MF-2 With Changes in Blade Height

Description: From Summary: "Modifications A and B of impeller model MFI-1 and A, B, and C of impeller model MFI-2 were investigated experimentally in an attempt to determine what allowance in blade height should be made for boundary layer and viscous losses in an impeller designed for isentropic compressible flow. A gradual increase in blade height was arbitrarily made from inlet to outlet in anticipation of a gradual build-up of boundary layer. Apparently there was a rapid build-up of boundary layer near t… more
Date: February 11, 1954
Creator: Hamrick, Joseph T.; Beede, William L. & Withee, Joseph R., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Summary of free-flight performance of a series of ram-jet engines at Mach numbers from 0.80 to 2.20

Description: From Summary: "Data obtained from the NACA air-launched ram-jet program are summarized with emphasis placed upon the transonic propulsive thrust potential of the engines. Data are presented for boosted and non-boosted engine configurations which incorporate a single-oblique-shock or double-oblique-shock diffuser designed for critical inlet operation at flight Mach numbers of 1.8 and 2.4, respectively. The engines are evaluated in terms of flight Mach number, mass-flow ratio, diffuser pressure r… more
Date: February 11, 1954
Creator: North, Warren J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Measured and Estimated Lateral Static and Rotary Derivatives of a 1/12-Scale Model of a High-Speed Fighter Airplane With Unswept Wings

Description: Report presenting a low-speed investigation to determine the lateral static and rotary derivatives of a model of a high-speed fighter airplane. The purpose was to compare experimental stability derivatives with derivatives estimated for a wing-fuselage combination, a vertical- and horizontal-tail combination, and a complete model.
Date: January 11, 1954
Creator: Williams, James L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Thrust and drag characteristics of a convergent-divergent nozzle with various exhaust jet temperatures

Description: From Summary: "An investigation was conducted in the 8-by-6 foot supersonic wind tunnel on the effect of exhaust-gas temperatures on the external and internal characteristics of a convergent-divergent nozzle having an area expansion ratio of 1.83. Data were obtained over a pressure-ratio range from 1 to 20 at free-stream Mach numbers of 1.6 and 2.0 for exhaust temperatures of 860 degrees, 1650 degrees, and 2000 degrees R. Results of this investigation indicated that generally both the internal … more
Date: March 11, 1954
Creator: Hearth, Donald P. & Wilcox, Fred A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

An experimental investigation of hollow turbine blades for expandable jet engines

Description: From Summary: "An experimental investigation was made to determine the feasibility of using hollow turbine blades in engines designed for short service life. Airfoils were fabricated from sheet material and techniques of welding and brazing attachment were investigated. The airfoils were not intended to be cooled. A principal objective was the reduction of strategic material requirements primarily as a function of direct weight reduction."
Date: March 11, 1954
Creator: Morgan, W. C. & Morse, C. R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Investigation of a translating-cone inlet at Mach numbers from 1.5 to 2.0

Description: Report presenting an investigation in the 8- by 6-foot supersonic wind tunnel to evaluate the performance of a translating-cone inlet operated over a range of Mach numbers and angles of attack. The effects of spike projection and internal flow area variation on pressure recovery, external drag, and corrected air-flow variation were determined.
Date: May 11, 1954
Creator: Sterbentz, William H. & Leissler, L. Abbott
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Experimental Sea-Level Static Investigation of a Short Afterburner

Description: Report presenting a sea-level static investigation to determine the performance and some design principles for a short afterburner. The power section of a 12-stage axial-flow turbojet engine was used and the afterburner was designed to fit within the length required for the tail pipe used on the standard nonafterburning model.
Date: May 11, 1954
Creator: Harp, James L., Jr.; Mallett, William E. & Shillito, Thomas B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Investigation of transient combustion characteristics in a single tubular combustor

Description: An investigation was conducted to determine the combustion response to rapid fuel-flow changes in a single tubular combustor at two simulated altitude-rotor speed conditions of 25,000 feet-70 percent rated engine speed and 50,000 feet-70 percent rated engine speed. Limiting rates of change of fuel flow (acceleration limits) were determined and the effects of certain combustion air flow variables on the transient combustion characteristics were studied with the aid of rapid-response instrumentat… more
Date: February 11, 1954
Creator: Donlon, Richard H.; McCafferty, Richard J. & Straight, David M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Pressures and Associated Aerodynamic and Load Characteristics for Two Bodies of Revolution at Transonic Speeds

Description: Report presenting an analysis of results obtained from a transonic wind-tunnel investigation of two bodies of revolution with the same nose shape but two different shapes of afterbody. Results regarding pressure distribution, normal-force characteristics, pitching-moment and center-of-pressure characteristics, and detailed load characteristics are provided.
Date: March 11, 1954
Creator: Robinson, Harold L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Low-velocity turning as a means of minimizing boundary-layer accumulations resulting from secondary flows within turbine stators

Description: A study of a series of three single-passage nozzles, designed to turn the flow at different velocity levels but to identical outlet conditions, in order to determine whether secondary-flow accumulations of boundary-layer fluids within nozzles could be minimized by use of low-velocity turning. Results indicated that the type of turning with subsequent acceleration is highly effective in minimizing secondary-flow accumulations at the corner where the suction surface joins the end walls.
Date: May 11, 1954
Creator: Stewart, Warner L. & Wong, Robert Y.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Theoretical Maximum Performance of Liquid Fluorine - Liquid Oxygen Mixtures With JP-4 Fuel as Rocket Propellants

Description: Memorandum presenting a calculation of theoretical values of rocket performance parameters for JP-4 fuel and various mixtures of liquid fluorine and liquid oxygen, assuming equilibrium and frozen composition during the expansion process. Data were calculated at several equivalence ratios for each assigned fluorine-oxygen mixture. Some of the parameters explored include specific impulse, combustion-chamber temperature, nozzle-exit temperature, equilibrium composition, mean molecular weight, char… more
Date: October 11, 1954
Creator: Gordon, Sanford & Wilkins, Roger L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Preliminary investigation of an asymmetric swept nose inlet of circular projection at Mach number 3.85

Description: Report presenting an experimental investigation of the performance capabilities of an asymmetric swept nose inlet of circular projection in the supersonic wind tunnel at a Mach number of 3.85. The aysmmetric inlet was evaluated in terms of its pressure recovery and mass-flow characteristics for angles of attack up to 9 degrees. Results regarding diffuser performance, supercritical flow patterns, oblique shocks, subcritical stability ranges, and Mach number profiles are provided.
Date: October 11, 1954
Creator: Connors, James F. & Woollett, Richard R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Investigation at Transonic Speeds of the Lateral-Control and Hinge-Moment Characteristics of a Flap-Type Spoiler Aileron on a 60 Degree Delta Wing

Description: This paper present results of an investigation of the lateral-control and hinge-moment characteristics of a 0.67 semispan flap-type spoiler aileron on a semispan thin 60 degree delta wing at transonic speeds by the reflection-plane technique. The spoiler-aileron had a constant chord of 10.29 percent mean aerodynamic chord and was hinged at the 81.9-percent-wing-root-chord station. Results indicated reasonably linear variations of rolling-moment and hinge-moment coefficients with spoiler project… more
Date: January 11, 1954
Creator: Wiley, Harleth G. & Taylor, Robert T.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Preliminary investigation of an asymmetric swept nose inlet of circular projection at Mach number 3.85

Description: Report presenting a preliminary experimental investigation of the performance capabilities of an asymmetric swept nose inlet of circular projection in the supersonic wind tunnel at a Mach number of 3.85. The performance of the inlet was compared with previously reported performance for more conventional, axially symmetric, annular nose inlets.
Date: October 11, 1954
Creator: Connors, James F. & Woollett, Richard R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Investigation of a Transonic Turbine Designed for a Maximum Rotor-Blade Suction-Surface Relative Mach Number of 1.57

Description: "A transonic turbine designed for a maximum blade-surface relative Mach number of 1.57 was investigated experimentally. The performance of the turbine is compared with that of three other transonic turbines that were previously investigated" (p. 1).
Date: October 11, 1954
Creator: Whitney, Warren J.; Wong, Robert Y. & Monroe, Daniel E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Investigation of Turbojet Engine Performance at Speeds and Gas Temperatures Above Rated Using Turbine-Blade External Water-Spray Cooling from Stationary Injection Orifices

Description: Memorandum presenting a turbojet engine with a centrifugal-flow compressor which permitted overspeed, overtemperature operation and was modified for spray cooling. The effectiveness of spray cooling as a method which permits operation at overspeed, overtemperature conditions with this engine was investigated and the overspeed, overtemperature performance was obtained. Results regarding the cooling system performance, turbine performance, and engine performance are provided.
Date: October 11, 1954
Creator: Freche, John & McKinnon, Roy A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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