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Performance characteristics of cylindrical target-type thrust reversers

Description: From tests on cylindrical target-type thrust reversers, it was found that the reverser frontal area, lip angle, end-plate angle, and end-plate depth had important effects on reverse-thrust performance. Frontal area, reverser depth, lip angle, and end-plate angele had important effects on the spacing required for unrestricted nozzle flow. For reverse-thrust ratios greater than 64 percent, the reversed flow attached to the 7 degree cowl in quiescent air. Swept-type cylindrical reversers were generally unstable. The thrust-modulation characteristics of a cylindrical target-type thrust reverser were found to be satisfactory.
Date: January 11, 1956
Creator: Steffen, Fred W. & McArdle, Jack G.
Partner: UNT Libraries Government Documents Department

Experimental investigation of a two-dimensional split-wing ram-jet inlet at Mach number of 3.85

Description: Performance characteristics of a two-dimensional isentropic diffuser have been experimentally determined at a Mach number of 3.85. At zero angle of attack, a maximum total-pressure recovery of 0.41 was obtained with a supercritical mass-flow ratio of 0.95. As a consequence of the twin-duct arrangement of the diffuser, a large discontinuity in pressure recovery and mass flow with a characteristic hysteresis was encountered between critical and subcritical operation. An asymmetric shock pattern with large-scale separation and flow reversal in one of the passages occurred at reduced mass flows. Pressure and force data presented for an angle-of-attack range from zero to 4 degrees.
Date: August 11, 1952
Creator: Connors, James F. & Woollett, Richard R.
Partner: UNT Libraries Government Documents Department

Force characteristics in the submerged and planing condition of a 1/5.78-scale model of a hydro-ski-wheel combination for the Grumman JRF-5 airplane

Description: From Summary: "Force characteristics determined from tank tests of a 1/5.78-scale model of a hydro-ski-wheel combination for the Grumman JRF-5 airplane are presented. The model was tested in both the submerged and planing conditions over a range of trim, speed, and load sufficiently large to represent the most probable full-size conditions."
Date: July 11, 1952
Creator: Land, Norman S. & Pelz, Charles A.
Partner: UNT Libraries Government Documents Department

Comparison of two methods of modulating the throat area of convergent plug nozzles

Description: Report presenting an investigation to determine the effect on performance of two methods of throat-area modulation of two convergent plug nozzles. Data were obtained over a range of pressure ratios. Results regarding the performance of the translatable outer-shell-type plug nozzle, performance of the iris-outer-shell-type plug nozzles, sensitivity to throat-area variation, and air-flow parameter are provided.
Date: May 11, 1955
Creator: Krull, H. George & Beale, William T.
Partner: UNT Libraries Government Documents Department

Design and performance of a 1400-foot-per-second-tip-speed supersonic compressor rotor

Description: Report presenting performance testing of a supersonic compressor designed for a tip speed of 1400 feet per second, a pressure ratio of 2.0, and a corrected weight flow of 30.5 pounds per second. The overall performance results of the rotor alone at design speed gave a pressure ratio of 2.17, an adiabatic efficiency of 89 percent, and a weight flow of 28 pounds per second. A comparison with the predicted design results is provided.
Date: April 11, 1955
Creator: Klapproth, John F.; Jacklitch, John J., Jr. & Tysl, Edward R.
Partner: UNT Libraries Government Documents Department

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.
Partner: UNT Libraries Government Documents Department

Investigation at Mach number 1.91 of spreading characteristics of jet expanding from choked nozzles

Description: It is demonstrated that the temperature profiles of jets expanding into a supersonic stream are considerably smaller than the temperature profiles of jets expanding into quiescent air. The effect on the wake of varying afterbody geometry is shown to be small. The gross spreading characteristics of jets expanding from convergent and convergent-divergent nozzles in the base of a body of revolution with various boattail configurations at a Mach number of 1.91 are presented.
Date: January 11, 1952
Creator: Rousso, Morris D. & Baughman, L. Eugene
Partner: UNT Libraries Government Documents Department

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 and external performance characteristics were only slightly affected by a large change in jet temperature. The small differences in performance which did occur were predicted satisfactorily from theoretical considerations."
Date: March 11, 1954
Creator: Hearth, Donald P. & Wilcox, Fred A.
Partner: UNT Libraries Government Documents Department

Analysis of factors affecting selection and design of air-cooled single-stage turbines for turbojet engines 4: coolant-flow requirements and performance of engines using air-cooled corrugated-insert blades

Description: Report presenting an investigation of the estimated minimum cooling requirements and related performance of turbojet engines equipped with high-performance single-stage turbines with air-cooled corrugated-insert blades over a range of turbine-inlet temperature, tip speed, and hub-tip radius ratio for Mach number 2 at 50,000 feet. The effects of stress-ratio factor, flight Mach number, altitude, turbine rotor impeller efficiency, and outside heat-transfer coefficient on cooling requirements were also investigated.
Date: May 11, 1955
Creator: Slone, Henry O. & Hubbartt, James E.
Partner: UNT Libraries Government Documents Department

Wind-tunnel investigation at low speed of effects of sideslip on static longitudinal trim and static lateral stability characteristics of three fighter-type airplane models

Description: Report presenting a wind-tunnel investigation at low speed to determine the effects of sideslip on the static longitudinal trim characteristics of three fighter-type airplane models. The three models consisted of a 45 degree swept-wing model with a horizontal tail geometrically similar to the wing and mounted slightly below the wing, a clipped-delta-wing model with a horizontal tail mounted in a moderately high position, and a 60 degree delta-wing with no horizontal tail. Results regarding static longitudinal stability, variation of pitching-moment coefficient with sideslip, effect of modifications to Model B on static longitudinal stability and variation of pitching-moment coefficient with sideslip, and static lateral stability are presented.
Date: September 11, 1956
Creator: Jaquet, Byron M. & Fletcher, H. S.
Partner: UNT Libraries Government Documents Department

Investigation at supersonic speeds of a translating-spike inlet employing a steep-lip cowl

Description: Report presenting an experimental investigation conducted in the supersonic wind tunnel at three Mach numbers on a translating-spike inlet analytically designed to keep the cone shoulder downstream of the cowl-lip station without a net internal contraction. The inlet in this investigation had an internal cowl-lip angle of 17.5 degrees and was constructed to have the same inlet capture area and maximum cross-sectional area as a previously tested inlet with an internal cowl-lip angle of only 7 degrees. Results regarding the total pressure recovery, effect of spike translation, external drag coefficients, and effective thrust parameter are provided.
Date: October 11, 1954
Creator: Gorton, Gerald C.
Partner: UNT Libraries Government Documents Department

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 recovery, combustion-chamber heat release, propulsive thrust, external drag, and specific impulse. From specific impulse considerations, it appears that for some air-launched missile applications the self-accelerating supersonic ram jet may have a lower gross weight than a rocket-boosted ram jet."
Date: February 11, 1954
Creator: North, Warren J.
Partner: UNT Libraries Government Documents Department

Transonic wind-tunnel investigation of the effects of indentation on the wing loads of a 45 degree sweptback wing-body combination

Description: Report presenting the effects of an angle of incidence of 4 degrees and body indentation on wing loads of a sweptback wing-body combination at a range of Mach numbers. The wing had an aspect ratio of 4, taper ratio of 0.3, 45 degrees of sweepback of the quarter-chord line, and NACA 65A006 airfoil sections parallel to the plane of symmetry. Results regarding the effect of incidence and effect of body indentation are provided.
Date: January 11, 1956
Creator: Platt, Robert J., Jr.
Partner: UNT Libraries Government Documents Department

Turbulent convective heat-transfer coefficients measured from flight tests of four research models (NACA RM-10) at Mach numbers from 1.0 to 3.6

Description: Report presenting an evaluation of convective heat-transfer coefficients from skin temperatures measured along the body of a research model designated NACA RM-10. Heat-transfer data is presented for a range of Mach and Reynolds numbers based on the axial distance from the nose to the point at which the temperature measurements were made. Results regarding the recovery factor, heat transfer, correlation with different aircraft models, and Reynolds analogy are provided.
Date: March 11, 1955
Creator: Chauvin, Leo T. & Maloney, Joseph P.
Partner: UNT Libraries Government Documents Department

Time histories of maneuvers performed with an F-86A airplane during squadron operations

Description: Report presenting some preliminary time-history results of maneuvers performed during US Air Force squadron operations with an F-86A jet-fighter airplane. The information covers a speed range from stall to 530 mph-indicated airspeed and pressure altitudes varying from sea level to approximately 25,000 feet.
Date: February 11, 1952
Creator: Hamer, Harold A. & Henderson, Campbell
Partner: UNT Libraries Government Documents Department

Motion of a ballistic missile angularly misaligned with the flight path upon entering the atmosphere and its effect upon aerodynamic heating, aerodynamic loads, and miss distance

Description: From Summary: "An analysis is given of the oscillating motion of a ballistic missile which upon entering the atmosphere is angularly misaligned with respect to the flight path. The history of the motion for some example missiles is discussed from the point of view of the effect of the motion on the aerodynamic heating and loading. The miss distance at the target due to misalignment and to small accidental trim angles is treated. The stability problem is also discussed for the case where the missile is tumbling prior to atmospheric entry."
Date: September 11, 1956
Creator: Allen, H. Julian
Partner: UNT Libraries Government Documents Department

Smoke studies of secondary flows in bends, tandem cascades, and high-turning configurations

Description: Flow-visualization studies, using smoke, were made of the secondary flows in rectangular bends, tandem cascades, and high-turning configurations. The roll-up of the wall boundary layer of a rectangular bend forms a passage vortex near the suction surface similar to that previously observed for cascades. The vortex so formed then shifts out into the main stream. Because of leading-edge effects, the boundary-layer flows in bends were found to be sufficiently different from the flows in blade rows to make direct application of bend results to blade rows inadvisable.
Date: March 11, 1953
Creator: Hansen, Arthur G.; Herzig, Howard Z. & Costello, George R.
Partner: UNT Libraries Government Documents Department

Some control considerations for ram-jet engines

Description: Control requirements were determined from calculated engine performance maps for a fixed-geometry ram jet of a configuration suitable for strategic supersonic missile propulsion. Several control schemes for attaining desired engine performance and for stabilizing missile flight velocity during cruise are presented. The advantages and disadvantages of each system are discussed.
Date: August 11, 1952
Creator: Himmel, Seymour C.
Partner: UNT Libraries Government Documents Department

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.
Partner: UNT Libraries Government Documents Department

The influence of imperfect radar space stabilization on the final attack phase of an automatic interceptor system

Description: From Summary: "The manner in which imperfect space stabilization of the tracking radar influences the flight path stability of an automatic interceptor during the attack phase is illustrated by means of flight and analog-computer time histories. It is shown analytically that these effects may be interpreted in terms of a destabilizing airplane rate feedback which can be canceled by an additional compensatory feedback in the radar tracking loop."
Date: March 11, 1957
Creator: Triplett, William C.; McLean, John D. & White, John S.
Partner: UNT Libraries Government Documents Department

Experimental investigation of an axial-flow supersonic compressor having rounded leading-edge blades with an 8-percent mean thickness-chord ratio

Description: Report presenting testing of supersonic compressor blades with rounded leading edges with an 8-percent mean thickness-chord ratio and a solidity of about 2.5 were incorporated in a 16-inch-diameter rotor with and without guide vanes. Results regarding the overall performance, rotor-blade-element performance, and rotor without guide vanes are provided.
Date: December 11, 1953
Creator: Goldberg, Theodore J.; Boxer, Emanuel & Bernot, Peter T.
Partner: UNT Libraries Government Documents Department

Preliminary investigation of the combustion of a 50 percent pentaborane - 50 percent JP-4 fuel blend in a turbojet combustor at simulated altitude conditions

Description: A preliminary investigation was conducted to determine the combustion characteristics of a fuel composed of 50 percent pentaborane and 50 percent JP-4 (MIL-F-5624A) by weight in a turbojet combustor. A combustor designed to fit the housing of a J33-A-23 turbojet engine was selected for convenience. The fuel was evaluated at two engine conditions simulating altitudes of 40,000 and 57,000 feet, an engine speed of 85 percent of rated rpm, and a flight Mach number of 0.6. The pentaborane blend was initially evaluated in combustors developed for pure pentaborane and diborane reported in NACA RM E53B18 and RM E52L15. The performance of the blend was unsatisfactory in these combustors. A new combustor was then developed which provided combustor efficiencies measured from 91 to 101 percent as compared with efficiencies of 92 to 94 percent previously obtained for pentaborane at comparable conditions. Additional refinements of design details are needed to obtain lower oxide deposits and a more uniform outlet temperature profile; however, the combustor is believed to incorporate some of the design principles required to obtain satisfactory over-all performance with the fuel blend investigated.
Date: March 11, 1957
Creator: Branstetter, J. Robert; Kaufman, Warner B. & Gibbs, James B.
Partner: UNT Libraries Government Documents Department

Transonic flight tests to determine zero-lift drag and pressure recovery of nacelles located at the wing tips on a 45 degree sweptback wing and body combination

Description: Report presenting the zero-lift drag of a sweptback wing and body combination with nacelles with NACA 1-50-250 nose inlets locate in the wing tips as determined by flight tests of rocket-powered models at transonic speeds. Results regarding the pressure recovery and the effect of the nacelles on it are also provided.
Date: January 11, 1952
Creator: Hoffman, Sherwood & Pepper, William B., Jr.
Partner: UNT Libraries Government Documents Department

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.
Partner: UNT Libraries Government Documents Department