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Acceleration of high-pressure-ratio single-spool turbojet engine as determined from component performance characteristics 3: effect of turbine stator adjustment

Description: From Summary: "An analytical investigation was made to determine from component performance the effect of turbine stator adjustment on the acceleration characteristics of a typical high-pressure-ratio single-spool turbojet engine. Turbine stator adjustment was adequate to permit engine operation in the intermediate-speed range, but was less satisfactory than the relatively simple schemes of compressor-interstage and -outlet bleed."
Date: August 2, 1954
Creator: Rohlik, Harold E. & Rebeske, John J.
Item Type: Refine your search to only Report
open access

Accelerator Development Department Internal Report

Description: In this report we present solutions of the design problem in which a system of quadruple lenses is required to carry a particle beam from given focal lines in the x and y planes to other given focal lines. Particular attention will be given to the case of the anastigmatic lens system which takes a beam from one focal point to another focal point. Since the general problem is almost impossibly complicated a simplification is introduced by breaking the lens system into two parts. The first part o… more
Date: October 2, 1958
Creator: Blewett, J. P.
Item Type: Refine your search to only Report
open access

Adaptation of Combustion Principles to Aircraft Propulsion Volume 2: Combustion in Air-Breathing Jet Engines

Description: This volume continues the NACA study of combustion principles for aircraft propulsion. The various aspects of combustion pertinent to jet engines are organized and interpreted with quite extensive information, particularly for basic or fundamental. subject matter. The report concerns only air-breathing engines and hydrocarbon fuels, and not rocket engines and high-energy fuels.
Date: May 2, 1956
Creator: Fuels and Combustion Research Division
Item Type: Refine your search to only Report
open access

Aerodynamic characteristics at Mach numbers from 0.7 to 1.75 of a four-engine swept-wing airplane configuration as obtained from a rocket-propelled model test

Description: Report presenting flight testing of a rocket-propelled model of a typical multiengine airplane configuration to obtain data on drag, stability, and nacelle performance. Data were obtained at a variety of Mach numbers, lift coefficients, and subsonic and supersonic speeds. Results regarding airplane performance, nacelle performance, longitudinal characteristics, and lateral characteristics are provided.
Date: September 2, 1955
Creator: Chapman, Rowe, Jr.
Item Type: Refine your search to only Report
open access

Aerodynamic characteristics of a 68.4 degree delta wing at Mach numbers of 1.6 and 1.9 over a wide Reynolds number range

Description: From Introduction: "The purpose of this paper is to provide further information on the effects of Reynolds number on the aerodynamic characteristics of the wing of reference 1 as well as to provide load distributions for the wing at Mach numbers of 1.6 and 1.9."
Date: November 2, 1953
Creator: Hatch, John E., Jr. & Gallagher, James J.
Item Type: Refine your search to only Report
open access

Aerodynamic Characteristics of Low-aspect-ratio Wings at High Supersonic Mach Numbers

Description: Memorandum presenting some recently obtained data on the aerodynamic characteristics of low-aspect-ratio wings at supersonic Mach number of 4.04 and 6.9 and discusses some new methods of predicting the lift and drag of such wings. The plan forms, airfoil sections, and thickness ratios of the wings tested are provided.
Date: November 2, 1953
Creator: Ulmann, Edward F. & Bertram, Mitchel H.
Item Type: Refine your search to only Report
open access

Aerodynamic characteristics of low-aspect-ratio wings at high supersonic Mach numbers

Description: From Introduction: "This paper presents some recently obtained data on the aerodynamic characteristics of low-aspect-ratio wings at supersonic Mach numbers of 4.04 and 6.9 and discusses some new methods of predicting the lift and drag of such wings. Data on lifting wings in the Mach number range above 2.5 are not plentiful and most of the available data may be found in NACA RM L51D17, NACA RM L51D30, NACA RM L52D15a, NACA RM L52K19, NACA RM L53D03, and NACA RM L53D30a."
Date: November 2, 1953
Creator: Ulmann, Edward F. & Bertram, Mitchel H.
Item Type: Refine your search to only Report
open access

Aerodynamic characteristics of two-plane, unswept tapered wings of aspect ratio 3 and 3-percent thickness from tests on a transonic bump

Description: From Introduction: "The Ames Aeronautical Laboratory has in progress an experimental investigation of the aerodynamic characteristics of wings of interest in the design of high-speed fighter aircraft. This program included an investigation in the Ames 6-by 6-foot supersonic wind tunnel at both subsonic and supersonic Mach numbers of a wing-body combination having a 3-percent-thick, unswept, tapered wing with circular-arc sections and an aspect ratio of 3.1 (reference 1).
Date: May 2, 1952
Creator: Emerson, Horace F. & Gale, Bernard M.
Item Type: Refine your search to only Report
open access

Aerodynamic characteristics with fixed and free transition of a modified delta wing in combination with fuselage at high subsonic speeds

Description: From Introduction: "An investigation of the high-speed aerodynamic characteristics of a modified delta wing in combination with a fuselage was conducted in the Langley high-speed 7- by 10-foot tunnel. The model was tested on the sting support system through a Mach number range of 0.40 to 0.90 with both free and fixed transition. Because of the nature of the transition effect, the results seemed to be of the general interest and are presented in the present paper."
Date: May 2, 1950
Creator: Polhamus, Edward C. & King, Thomas J., Jr.
Item Type: Refine your search to only Report
open access

Altitude-Test-Chamber Investigation of McDonnell Afterburner on J34 Engine

Description: "An altitude-test-chamber investigation was conducted to determine the operational and performance characteristics of a McDonnell afterburner with a fixed-area exhaust nozzle on a J34 engine. At rated engine speed, the altitude limit, as determined by combustion blow-out, occurred as a band of unstable operation of about 6000-foot altitude in width with minimum altitude limits from 31,000 feet at a simulated flight Mach number of 0.40 to about 45,500 feet at a simulated flight Mach number of 1.… more
Date: June 2, 1949
Creator: Reller, John O. & Dowman, Harry W.
Item Type: Refine your search to only Report
open access

Altitude-wind-tunnel investigation of AN-F-58 fuel in experimental version of J47 turbojet engine

Description: An altitude-wind-tunnel investigation of the performance of AN-F-58 and AN-F-32 fuels in an experimental turbojet engine was conducted over a range of simulated altitudes and flight Mach numbers. Combustion efficiencies obtained with AN-F-58 and AN-F-32 fuels were approximately equal. The minimum-speed altitude operational limit was essentially the same with either AN-F-58 or AN-F-32 fuel. Starting characteristics of the two fuels were approximately the same at low wind milling speeds. Visual o… more
Date: May 2, 1949
Creator: Meyer, Carl L.
Item Type: Refine your search to only Report
open access

Altitude-Wind-Tunnel Investigation of Performance of Several Propellers on YP-47M Airplane at High Blade Loadings 5 - Curtiss 836-14C2-18R1 Four-Blade Propeller

Description: An investigation of the performance of several propellers on the YP-47M airplane at high blade loadings has been conducted in the Cleveland altitude wind tunnel at the request of the Air Materiel Command, Army Air Forces. As part of the program, a study was made of a Curtiss 836-14C2-18R1 four-blade propeller. The investigation was made for a range of power coefficients from 0.10 to 1.00 at free-stream Mach numbers of 0.30, 0.40, and 0.50 for density altitudes from 10,000 to 45,000 feet, engine… more
Date: December 2, 1946
Creator: Saari, Martin J. & Wallner, Lewis E.
Item Type: Refine your search to only Report
open access

Analysis of effects of airplane characteristics and autopilot parameters on a roll-command system with aileron rate and deflection limiting

Description: From Summary: "The dynamic characteristics of an airplane with a proportional-gain roll-control autopilot are discussed. A comparison of three different high-speed fighter airplanes is presented. The dynamic effects of time lags and various gains in the system are described."
Date: September 2, 1955
Creator: Schy, Albert A. & Gates, Ordway B., Jr.
Item Type: Refine your search to only Report
open access

Analysis of Performance of Jet Engine From Characteristics of Components 2: Interaction of Components as Determined From Engine Operation

Description: "In order to understand the operation and the interaction of jet-engine components during engine operation and to determine how component characteristics may be used to compute engine performance, a method to analyze and to estimate performance of such engines was devised and applied to the study of the characteristics of a research turbojet engine built for this investigation. An attempt was made to correlate turbine performance obtained from engine experiments with that obtained by the simple… more
Date: June 2, 1948
Creator: Goldstein, Arthur W.; Alpert, Sumner; Beede, William & Kovach, Karl
Item Type: Refine your search to only Report
open access

Analysis of several methods of pumping cooling air for turbojet engine afterburners

Description: From Introduction: "Afterburning is well established as an effective means of increasing the thrust of a turbojet engine. In order to obtain the maximum thrust from an afterburner, it is necessary to burn to the highest temperatures possible (reference 1). At these high temperatures, material limitations (reference 2) necessitate the installation of cooling systems to permit safe and reliable operation."
Date: February 2, 1953
Creator: Samuels, John C. & Yanowitz, Herbert
Item Type: Refine your search to only Report
open access

Analysis of turbomachine viscous losses affected by changes in blade geometry

Description: From Introduction: "This report also presents a method of optimizing the blade number and solidity for a given application if the blade loss variation with solidity can be estimated or experimentally determined. Also discussed are the penalties in performance that accompany deviations from optimum values of blade number and solidity."
Date: October 2, 1956
Creator: Miser, James W.; Stewart, Warner L. & Whitney, Warren J.
Item Type: Refine your search to only Report
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