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Flight measurements of the transonic drag of models of several isolated external stores and nacelles

Description: Report presenting drag measurements on models of 20 isolated external stores and nacelles flown from the helium gun at a range of Mach numbers. Results regarding fineness-ratio and shape effects, drag correlation, and friction drag are provided. Generally, the shape variations among the various types of stores and nacelles had the expected effects on isolated body drag.
Date: March 11, 1955
Creator: Stevens, Joseph E. & Purser, Paul E.
Partner: UNT Libraries Government Documents Department

Effect of flight speed on dynamics of a turboprop engine

Description: Report presenting an investigation of transient operation of a turboprop engine in an altitude wind tunnel at 35,000 feet over a range of Mach numbers to determine the effect of flight speed upon the dynamic response of the engine. The generalized time constant of the engine-propeller combination varied with flight speed and power level.
Date: April 11, 1955
Creator: Nakanishi, S.; Craig, R. T. & Wile, D. B.
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

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

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

Stabilization techniques for ramp-type side inlets at supersonic speeds

Description: Report presenting an investigation of methods of increasing the stable subcritical range of a twin-duct double-ramp inlet mounted on the sides of a fuselage forebody in the supersonic wind tunnel. Results regarding the stabilization with high performance and low-mass-flow stabilization are also provided.
Date: April 11, 1955
Creator: Obery, L. J.; Cubbison, R. W. & Mercer, T. G.
Partner: UNT Libraries Government Documents Department

High-altitude performance of an experimental turbojet combustor having variable primary-air admission

Description: Report presenting an investigation of 47 experimental tubular designs embodying variable primary-air openings to control the fuel-air ratio in the combustion zone at simulated high-altitude operating conditions for a representative 5.2-pressure-ratio engine. The performance characteristics considered were combustion efficiency, operating range, and pressure loss. Results regarding the effect of fuel injector design, effect of primary-air baffles, and performance characteristics of the best models are provided.
Date: April 11, 1955
Creator: Straight, David M. & Gernon, J. Dean
Partner: UNT Libraries Government Documents Department

Preliminary Results From Free Jet Tests of a 48-Inch-Diameter Ram-Jet Combustor With an Annular-Piloted Baffle-Type Flameholder

Description: Report presenting an investigation in a free-jet facility of a ramjet engine with an experimental 48-inch-diameter combustor. Three combustor lengths, three lengths of the shroud which separated the bypass air from the burning stream, and four fuel-distribution systems were investigated over a range of fuel-air ratios and a range of engine air flows. Results regarding the engine performance and ignition data, effect of fuel profile on combustion efficiency, total-pressure ratio, and distribution of static pressure in the main air stream are provided.
Date: May 11, 1955
Creator: Rayle, Warren D.; Smith, Ivan D. & Wentworth, Carl B.
Partner: UNT Libraries Government Documents Department

Preliminary Results From Free-Jet Tests of a 48-Inch-Diameter Ram-Jet Combustor With an Annular Can-Type Flame Holder

Description: Report presenting an investigation in an NACA free-jet facility of a ramjet engine with an experimental 48-inch-diameter combustor. Three combustor lengths and three fuel-distribution systems were investigated over a range of fuel-air ratios and at two air flows. Results regarding the combustor performance and ignition data, velocity profile, and starting characteristics are provided.
Date: May 11, 1955
Creator: Wentworth, Carl B.; Dobson, Wilbur F. & Rayle, Warren D.
Partner: UNT Libraries Government Documents Department

Transonic Free-Flight Investigation of the Longitudinal Aerodynamic Characteristics of a 1/10-Scale Steel-Wing of the Northrop MX-775A Missile With Leading-Edge Extensions, Inboard Trailing-Edge Flaps, and a Speed Brake on the Vertical Tail

Description: Memorandum presenting results of a free-flight investigation over a range of Mach and Reynolds numbers to determine the longitudinal aerodynamic characteristics of the Northrop MX-775A missile. The missile has a wing, body, and vertical tail, but has no horizontal tail. Results regarding basic data, drag, trim, lift and static stability, damping, and static pressure are provided.
Date: February 11, 1955
Creator: Arbic, Richard G.
Partner: UNT Libraries Government Documents Department

Performance of Pure Fuels in Single J33 Combustors 2: Hydrocarbon and Nonhydrocarbon Fuels

Description: Memorandum presenting performance investigations of 13 fuels - five hydrocarbons, four oxygenated hydrocarbons, and four substituted hydrocarbon-type fuels - conducted in a single tubular turbojet combustor in order to determine a possible relation between combustor performance and fuel properties. Combustor temperature rise and combustion efficiency were determined at a variety of air-flow rates, inlet-air total temperatures, and a range of heat-input values.
Date: April 11, 1955
Creator: Smith, Arthur L. & Wear, Jerrold D.
Partner: UNT Libraries Government Documents Department

Aerodynamic Characteristics of a 0.04956-Scale Model of the Convair F-102A Airplane at Transonic Speeds

Description: "Tests have been conducted in the Langley 8-foot transonic tunnel on a 0.04956-scale model of the Convair F-102A airplane which employed an indented and extended fuselage, cambered wing leading edges, and deflected wing tips. Force and moment characteristics were obtained for Mach numbers from 0.60 to 1.135 at angles of attack up to 20 degrees. In addition, tests were made over a limited angle-of-attack range to determine the effects of the cambered leading edges, deflected tips, and a nose section with a smooth area distribution" (p. 1).
Date: April 11, 1955
Creator: Tempelmeyer, Kenneth E. & Osborne, Robert S.
Partner: UNT Libraries Government Documents Department

Aerodynamic Design of Axial-flow Compressors 6 - Experimental Flow in Two-Dimensional Cascades

Description: "Available experimental two-dimensional cascade data for conventional compressor blade sections are correlated at a reference incidence angle in the region of minimum loss. Variations of reference incidence angle, total-pressure loss, and deviation angle with cascade geometry, inlet Mach number, and Reynolds number are investigated. From the analysis and the correlations of the available data, rules and relations are evolved for the prediction of blade-profile performance" (p. 1).
Date: November 11, 1955
Creator: Lieblein, Seymour
Partner: UNT Libraries Government Documents Department

The Origin and Distribution of Supersonic Store Interference From Measurement of Individual Forces on Several Wing-fuselagestore Configurations. 1.-swept-wing Heavy-bomber Configuration With Large Store Nacelle . Lift and Drag, Mach Number, 1.61

Description: Supersonic store interference - 1, swept-wing heavy bomber with large stores - lift & drag at mach 1.61.
Date: March 11, 1955
Creator: Carlson, H. W. & Smith, N. F.
Partner: UNT Libraries Government Documents Department

Preliminary Results from Free-Jet Tests of a 48-Inch-Diameter Ram-Jet Combustor with an Annular-Piloted Baffle-Type Flameholder

Description: A ram-jet engine with an experimental 48-inch-diameter combustor was investigated in a free-jet facility. The combustor design comprised a large-volume annular pilot region and an array of sloping baffle- or gutter-type flameholders. The combustor was intended to operate at a fuel-air ratio of about 0.037. To promote combustion efficiency at such low fuel-air ratios, a divided-flow system was employed which bypassed a portion of the engine air around the combustion region. Three combustor lengths, three lengths of the shroud which separated the bypass air from the burning stream, and four fuel-distribution systems were investigated over a range of fuel-air ratios from 0.025 to 0.055 and a range of engine air flows from 40 to 110 pounds per second (combustor-outlet total pressures from 500 t o 1800 lb/sq ft abs). The highest efficiencies were obtained with a combustor length of 78 inches and a shroud length of 6 inches. At the lowest air flow, with combustor pressures of about 700 pounds per square foot absolute, a maximum efficiency of about 93 percent was obtained. The efficiency increased with combustor length, a typical increase being from 88 to 95 percent as the length increased from 60 to 96 inches. The length of the shroud separating the bypass air from the burning stream affected not only the efficiency level, but also the fuel-air ratio at which the maximum efficiency occurred. In general, a longer shroud caused the maximum efficiency to occur at lower f'uel-air ratios. Highest efficiencies usually resulted from the use of a fuel-injection system giving a uniform fuel profile. The efficiency at low fuel-air ratios could be considerably improved by the use of a radially nonuniform fuel profile which concentrated the fuel towards the outermost portion of the burning stream The total-pressure ratio across the combustor was about 0.86 at the ...
Date: May 11, 1955
Creator: Rayle, W. D.; Smith, I. D. & Wentworth, C. B.
Partner: UNT Libraries Government Documents Department

Transonic Free-Flight Investigation of the Longitudinal Aerodynamic Characteristics of a 1/10-Scale Steel-Wing Model of the Northrop MX-775A Missile with Leading-Edge Extensions, Inboard Trailing-Edge Flaps, and a Speed Brake on the Vertical Tail

Description: Results are presented of a free-flight investigation between Mach numbers of 0.7 to 1.3 and Reynolds numbers of 3.1 x 10(exp 6) to 7.0 x 10(exp 6) to determine the longitudinal aerodynamic characteristics of the Northrop MX-775A missile. This missile has a weng, body, and vertical tail, but has no horizontal tail. The basic wing plan form has an aspect ratio of 5.5, 45 deg of sweepback of the 0.406 streamwise chord line, and a taper ratio of 0.4. A 1/10-scale steel-wing model of the missile was flown with modifications to the basic wing plan form consisting of leading-edge chord-extensions deflected 7 deg downward together with the forward 15 percent of the wing chord, and inboard trailing-edge flaps deflected 5 deg downward. In addition, the model had a static-pressure tube mounted at the tip of the vertical tail for position-error measurements and had a speed brake also mounted on the vertical tail to trim the model to positive lift coefficients and to permit determination of the trim and drag effectiveness of the brake. The data are uncorrected for the effects of wing elasticity, but experimental wing influence coefficients are presented.
Date: February 11, 1955
Creator: Arbic, R. G.
Partner: UNT Libraries Government Documents Department