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The Ames 10- by 14-Inch Supersonic Wind Tunnel
Description:
"The purpose of the present report is to describe the 10- by 14-inch supersonic wind tunnel and its operational characteristics over the nominal Mach number range from 2.7 to 6.3. Rather complete calibration data on characteristics of flow in the test section are presented and briefly discussed" (p. 2).
Date:
January 1954
Creator:
Eggers, A. J., Jr. & Nothwang, George J.
Item Type:
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Report
Analysis and Construction of Design Charts for Turbines with Downstream Stators
Description:
From Introduction: "This paper describes the theoretical treatment that has been given the combustion process as it occurs in turbojet combustors. Various parts of this work have been previously published (refs. 1 to 3); this report presents a brief summary of this previous work together with new data which amplify the conclusions of references 1 to 3. Similar studies have been made of the ram-jet combustion process (ref. 4 and 5); however, the analysis for ram-jet combustion differs in some de…
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Date:
November 18, 1954
Creator:
Cavicchi, Richard H. & Constantine, Anita B.
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Report
Analysis of a nuclear-powered ram-jet missile
Description:
From Introduction: "The ram-jet missile studied in the present report is one type of shieldless which has the advantage of employing the simplest type of propulsion system."
Date:
October 5, 1954
Creator:
Rom, Frank E.
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Report
Analysis of Factors Affecting Selection and Design of Air-Cooled Single-Stage Turbine for Turbojet Engines 1: Turbine Performance and Engine Weight-Flow Capacity
Description:
Memorandum presenting an analysis to determine the compressor pressure ratios and specific weight flows obtainable with single-stage air-cooled turbines for both nonafterburning and afterburning turbojet engines operating at a flight Mach number of 2 in the stratosphere. Wide ranges in turbine-inlet temperature, tip speed, hub-tip radius ratio, and coolant-flow ratio were considered.
Date:
May 25, 1954
Creator:
Rossbach, Richard J.; Schramm, Wilson B. & Hubbartt, James E.
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Report
Analysis of Factors Affecting Selection and Design of Air-Cooled Single-Stage Turbines for Turbojet Engines 2: Analytical Techniques
Description:
Memorandum presenting computation methods for analyzing turbojet-engine performance for a series of air-cooled nonafterburning and afterburning engines where all the engine components are simultaneously aerodynamically limited. The coolant-flow ratio was arbitrarily assigned so that the results of the analysis can be applied to any specific air-cooled blade configurations.
Date:
June 21, 1954
Creator:
Rossbach, Richard J.
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Report
Analysis of Off-Design Operation of High Mach Number Supersonic Turbojet Engines
Description:
From Introduction: "Because of the lack of data on compressor characteristics at 130 or 145 percent of design equivalent rotational speed, several simplifying assumptions were made regarding the compressor characteristics during operation at equivalent rotational speeds above the design value (hereinafter called "compressor overspeeding"). In addition to results based on these assumptions, the effect of deviation from these assumptions is discussed."
Date:
February 4, 1954
Creator:
English, Robert E. & Cavicchi, Richard H.
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Report
Analysis of performance of four symmetrical-diagram-type subsonic inlet-stage axial-flow compressors
Description:
Report presenting an investigation of four axial-flow single-stage compressors with a hub-tip radius ratio of 0.5 with three objectives related to the ideal symmetrical-velocity-diagram design, the comparison of blade-element turning angle and loss data with cascade data, and the validity of the simplified radial-equilibrium equation. Results regarding the overall performance, blade-element performance, and radial equilibrium considerations are provided.
Date:
January 20, 1954
Creator:
Jackson, Robert J.
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Report
Analysis of Piezometer and Relief-Well Data: Report Number 1, Data from Sardis Dam, Mississippi
Description:
Summary: Data obtained from tests and observations of the extensive piezometer and relief-well systems at Sardis Dam, Mississippi, are analyzed in this report in furtherance of a Corps of Engineers program to study the performance of earth dams and foundations.
Date:
February 1954
Creator:
Waterways Experiment Station (U.S.)
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Report
An Analysis of Pressure Studies and Experimental and Theoretical Downwash and Sidewash Behind Five Pointed-Tip Wings at Supersonic Speeds
Description:
The following report covers an investigation that was done to supplement available experimental data on flow fields behind wings of an aircraft at supersonic speeds, as well as to furnish more quantitative information on the choice of the theoretical method for a given configuration and the accuracy to be expected when using such a method.
Date:
April 21, 1954
Creator:
Boatright, William B.
Item Type:
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Report
An Analysis of Pressure Studies and Experimental and Theoretical Downwash and Sidewash Behind Five Pointed-Tip Wings at Supersonic Speeds
Description:
"Flow-angle and pressure surveys behind five, thin, pointed-tip wings of varying plan form have been made at Mach numbers 1.62 and 2.41. Schlieren studies at a Mach number 1.93 for the same five plan-form wings were made to illustrate the behavior of the vortex sheet. The surveys were conducted at 1.5, 3, and 4 root chords behind three triangular wings of 50 degree, 63 degree, and 72 degree leading-edge sweep angle, and behind the 50 degree triangular wing reversed" (p. 1067).
Date:
January 22, 1954
Creator:
Boatright, William B.
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Report
Analysis of rocket, ram-jet, and turbojet engines for supersonic propulsion of long-range missiles 1: rocket-engine performance
Description:
Report presenting theoretical performance characteristics and estimates of effective specific impulse and weight for rocket engines serving a main and booster power plants for missiles. The fuels used included ammonia-fluorine and JP4-oxygen propellants. At extremely high altitudes, the specific impulse depends primarily on the expansion ratio.
Date:
July 9, 1954
Creator:
Huff, Vearl N. & Kerrebrock, Jack
Item Type:
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Report
Analysis of Rocket, Ram-Jet, and Turbojet Engines for Supersonic Propulsion of Long-Range Missiles 2 - Rocket Missile Performance
Description:
From Summary: "The theoretical performance of a two-stage ballistic rocket missile having a centerbody and two parallel boosters was investigated for J oxygen and ammonia-fluorine propellants. Both power-plant and missile parameters were optimized to give minimum cost on-the basis of the analysis for a range of 5500 nautical miles. After optimum values were found, each parameter was varied independently to determine its effect on performance of the missile."
Date:
September 29, 1954
Creator:
Huff, Vearl N. & Kerrebrock, Jack
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Report
Analysis of rocket, ramjet, and turbojet engines for supersonic propulsion of long-range missiles. 3: Ramjet engine performance
Description:
Report presenting ramjet engine performance data over a range of engine design variables to permit selection and evaluation of a ramjet engine configuration for a long-range supersonic missile. Results include engine thrust, drag, fuel consumption, area ratios, and weight, and are suitable for use in design studies of missiles incorporating either internally or externally mounted ramjet engines.
Date:
August 5, 1954
Creator:
Weber, Richard J. & Luidens, Roger W.
Item Type:
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Report
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:
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Report
An analysis of shock-wave cancellation and reflection for porous walls which obey an exponential mass-flow pressure-difference relation
Description:
From Introduction: "In the present report a generalized exponential relation between pressure difference and normal flow is assumed which adequately describes porous-wall calibrations obtained experimentally at the Ames Laboratory and those presented in references 1 and 3."
Date:
August 1954
Creator:
Spiegel, Joseph M. & Tunnell, Phillips J.
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Report
Analysis of Straight Multicell Wings on Cal-Tech Analog Computer
Description:
Note presenting structural analyses made for four straight multicell wings. Wings with aspect ratios of 2 and 4 with rectangular and biconvex cross sections have been considered. The results indicated that under bending loads, all of the wings show fairly good agreement with beam theory.
Date:
January 1954
Creator:
Benscoter, Stanley U. & MacNeal, Richard H.
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Report
Analysis of Sweptback Wings on Cal-Tech Analog Computer
Description:
Note presenting structural analyses made of two 45 degree swept wings of aspect ratio 3. One has a constant depth and the other had a constant biconvex cross section in planes parallel to the air stream. Deflections, all internal forces, and vibration modes have been calculated for concentrated static loads.
Date:
January 1954
Creator:
MacNeal, Richard H. & Benscoter, Stanley U.
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Report
An analysis of the stability and ultimate bending strength of multiweb beams with formed-channel webs
Description:
From Introduction: "The purpose of the present paper is to develop a simple method of calculating both the stress at which initial wrinkling occurs in muti-web beams and the ultimate bending strength of beams which are susceptible to this mode of instability."
Date:
August 1954
Creator:
Semonian, Joseph W. & Anderson, Roger A.
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Report
Analysis of the turbojet for propulsion of supersonic bombers
Description:
From Introduction: "The investigation is discussed in the present report is an analysis of the turbojet engine as the power plant for bombers capable of supersonic flight speeds. A similar analysis, in which the turbojet engine is considered for the propulsion of supersonic fighter aircraft, is presented in reference 1. Two plans are considered in this report."
Date:
April 5, 1954
Creator:
Krebs, Richard P. & Wilcox, E. Clinton
Item Type:
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Report
Analysis of Turbulent Heat Transfer, Mass Transfer, and Friction in Smooth Tubes at High Prandtl and Schmidt Numbers
Description:
From Introduction: "In the analysis given herein, which was made at the NACA Lewis laboratory, the expression for eddy diffusivity given in reference 1 is modified in order to account for the effect of kinematic viscosity in reducing the turbulence in the region close to the wall. The effects of variable viscosity and of length-to-diameter ratio are also investigated."
Date:
February 17, 1954
Creator:
Deissler, Robert G.
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Report
Analysis of Wind-Tunnel Tests at Low Speeds of a Four-Engine Propeller-Driven Airplane Configuration Having a Wing With 40 Degrees of Sweepback
Description:
Report presenting an investigation to determine the effects of operating propellers on the longitudinal characteristics of a four-engine tractor airplane with a 40 degree swept wing with an aspect ratio of 10. Results regarding components of the lift changes due to operating propellers, components of the pitching-moment changes due to operating propellers, effect of configuration changes on the pitching-moment characteristics of the model, stick-fixed longitudinal stability of the model, reduct…
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Date:
October 8, 1954
Creator:
Edwards, George G. & Buell, Donald A.
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Report
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:
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Report
An analytical and experimental study of the transient response of a pressure-regulating relief valve in a hydraulic circuit
Description:
From Introduction: "This report presents an analysis of the response of the relief valve to sudden flow-demand changes. The analysis can be applied to the design of relief valves to satisfy given response specifications and to predict the stability of the valve in a specific hydraulic circuit. For this reason, derivatives of all the constants employed are included in the report."
Date:
March 1954
Creator:
Gold, Harold & Otto, Edward W.
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Report
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