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Analysis of Landing-Gear Behavior

Description: From Summary: "This report presents a theoretical study of the behavior of the conventional type of oleo-pneumatic landing gear during the process of landing impact. The basic analysis is presented in a general form and treats the motions of the landing gear prior to and subsequent to the beginning of shock-strut deflection."
Date: 1953~
Creator: Milwitzky, Benjamin & Cook, Francis E.
Item Type: Refine your search to only Report
open access

An analysis of normal-acceleration and airspeed data from a four-engine type of transport airplane in commercial operation on an eastern united states route from November 1947 to February 1950

Description: Report presenting an analysis of 48,187 hours of normal-acceleration and airspeed data obtained on a four-engine type of transport airplane in commercial operation on an eastern United States route from November 1947 to February 1950 to determine gusts and gust loads for operations. Results regarding the presentation of data, effect of changes in operating conditions, effect of seasons, comparison with other results, reliability, acceleration, gusts, and airspeeds are provided.
Date: August 1953
Creator: Coleman, Thomas L. & Schumacher, Paul W. J.
Item Type: Refine your search to only Report
open access

Analysis of Off-Design Performance of a 16-Stage Axial-Flow Compressor With Various Blade Modifications

Description: "The over-all performance of a 16-stage axial-flow compressor was determined with various stator-blade resettings and a reduction in solidity of the rotor blades in the last three stages. It was shown that little control over the sudden change in slope of the surge-limit line at intermediate speeds was obtained with the blade modifications attempted, except that some change in speed at which the change in slope occurred could be effected by stator-blade resettings" (p. 1).
Date: March 5, 1953
Creator: Medeiros, Arthur A.; Benser, William A. & Hatch, James E.
Item Type: Refine your search to only Report
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Analysis of part-speed operation for high-pressure-ratio multistage axial-flow compressors

Description: From Introduction: "For the analysis reported herein, the same hypothetical 12-stage compressor discussed in reference 6 was chosen, and the effects of inlet-stage stall characteristics and stage interactions were estimated by arbitrary adjustment of the stall characteristics and stage interactions were estimated by arbitrary adjustment of the stalled characteristics of the individual stages."
Date: December 4, 1953
Creator: Benser, William A.
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 submarginal ore, Fawn Springs area, Bull Canyon District, San Miguel and Montrose Counties, Colorado

Description: During a compilation of ore reserves at Bull Canyon, it was apparent from the grade of submarginal mineralization that this material might be a low-grade reserve of importance. Mr. Lewis Hazen requested a memorandum of the results of the analysis; this memorandum is a response to that request.
Date: June 12, 1953
Creator: Garbrecht, Louis
Item Type: Refine your search to only Report
open access

The Analysis of TBP Process Streams for Calcium with the Flame Photometer

Description: Summary: A method was found for determining calcium concentrations in TBP process streams in spite of serious interferences bysodium, ferrous, uranyl, sulfate, phosphate, and sulfamate ions as well as by TBP. The precision attainable varied from sample to sample, depending upon its composition. In general, errors of 20% or greater occurred. The smallest determinable amount of calcium was about 10 mg/1.
Date: February 20, 1953
Creator: Brite, D. W.
Item Type: Refine your search to only Report
open access

An analysis of the factors affecting the loss in lift and shift in aerodynamic center produced by the distortion of a swept wing under aerodynamic load

Description: From Introduction: "The importance of this aeroelastic phenomenon has been recognized for some time, and several investigators have developed more or less refined methods for analysis of wing elastic distortions and their effects. (For examples, see refs. 1 to 4.) More specific evidence as to the influence of wing external geometry (in conjunction with flight condition) on this flexibility-longitudinial-stability problem would appear to be of interest to the aerodynamicist, however, so that he … more
Date: March 1953
Creator: Mathews, Charles W. & Kurbjun, Max C.
Item Type: Refine your search to only Report
open access

An analysis of the power-off landing maneuver in terms of the capabilities of the pilot and the aerodynamic characteristics of the airplane

Description: From Introduction: "In the present paper, an analysis of the power-off landing maneuver is presented in which an attempt is made to consider both the aerodynamic characteristics of the airplane and the human capabilities of the pilot. In this paper, the type of pilot judgment considered is that of a pilot with previous flight experience, although not necessarily flight experience in any particular airplane under discussion."
Date: August 1953
Creator: von Doenhoff, Albert E. & Jones, George W., Jr.
Item Type: Refine your search to only Report
open access

An analysis of the tracking performances of two straight-wing and two swept-wing fighter airplanes with fixed sights in a standardized test maneuver

Description: From Introduction: "This report presents the initial study, the tracking performance of typical fighter airplanes with fixed gunsights. The types of airplanes tested afford two comparisons of particular interest: that between typical World War II and currently operational fighters of greatly increased speed and altitude, and that between conventional and irreversabile power-boosted controls with artificial feel, both installed on the same airframe."
Date: October 22, 1953
Creator: Rathert, George A., Jr.; Gadeberg, Burnett L. & Ziff, Howard L.
Item Type: Refine your search to only Report
open access

Analysis of the turbojet engine for propulsion of supersonic fighter airplanes

Description: An analytical investigation was made of two supersonic interceptor type airplanes to determine the most desirable turbojet engine characteristics for this application The airplanes were designed differently primarily because of the amount of subsonic flight incorporated in the flight plan--one flight having none and the other, a cruise radius of 400 nautical miles. Several power plant design variables were varied independently to determine the effect of changes in each parameter on airplane per… more
Date: October 26, 1953
Creator: Gabriel, David S.; Krebs, Richard P.; Wilcox, E. Clinton & Koutz, Stanley L.
Item Type: Refine your search to only Report
open access

Analysis of Turbine Stator Adjustment Required for Compressor Design-Point Operation in High Mach Number Supersonic Turbojet Engines

Description: From Introduction: "An investigation of the variation in turbine-entrance equivalent weight flow for a two-stage turbine equipped with an adjustable turbine stator is presented in reference 1. A general analytical investigation of turbine stator adjustment is presented in reference 2. In reference 2, the effect of stator adjustment on turbine off-design performance is also investigated by analytically computing the performance of a particular single-stage turbine."
Date: October 9, 1953
Creator: English, Robert E. & Cavicchi, Richard H.
Item Type: Refine your search to only Report
open access

An Analysis of Turbojet-Engine-Inlet Matching

Description: From Introduction: "This report presents a method of representing inlet air-flow capacities by the same parameter used to represent engine air-flow requirements so that the determination of the inlet operation condition at the match point can be simplified. Methods for analyzing the inlet geometric variations required to improve the power-plant performance at the match point are discussed and several examples are presented to illustrate the technique."
Date: September 1953
Creator: Wyatt, DeMarquis D.
Item Type: Refine your search to only Report
open access

Analytical comparison of turbine-blade cooling systems designed for a turbojet engine operating at supersonic speed and high altitude 1: liquid-cooling systems

Description: Report presenting an investigation of the influence of high-altitude supersonic flight on the operation and effectiveness of turbine-blade liquid-cooling systems for application in turbojet engines in guided missiles and in supersonic aircraft. The problems encountered in liquid-cooling systems were investigated with reference to several specific designs for alternate heat-rejection mediums.
Date: February 20, 1953
Creator: Schramm, Wilson B.; Nachtigall, Alfred J. & Arne, Vernon L.
Item Type: Refine your search to only Report
open access

Analytical comparison of turbine-blade cooling systems designed for a turbojet engine operating at supersonic speed and high altitude 2: air-cooling systems

Description: Report presenting an investigation of the influence of high-altitude supersonic flight on the operation and effectiveness of turbine-blade air- and liquid-cooling systems for turbojet application in guided missiles and supersonic interceptor aircraft. Results regarding the coolant passage heat-transfer-coefficients, nonrefrigerated air-cooling-system characteristics, and refrigerated-air-cooling-system characteristics are provided.
Date: February 19, 1953
Creator: Schramm, Wilson B.; Arne, Vernon L. & Nachtigall, Alfred J.
Item Type: Refine your search to only Report
open access

Analytical Derivation and Experimental Evaluation of Short-Bearing Approximation for Full Journal Bearing

Description: From Introduction: "This report extends the short-bearing pressure-distribution function of Michell and Cardullo to give equations for the various bearing characteristics. This short-bearing approximation makes available formulas relating eccentricity ratio to applied load, attitude angle, angular position of peak film pressure to unit pressure on projected area."
Date: June 12, 1953
Creator: DuBois, George B. & Ocvirk, Fred W.
Item Type: Refine your search to only Report
open access

Analytical evaluation of effect of equivalence ratio inlet-air temperature and combustion pressure on performance of several possible ram-jet fuels

Description: The results of an analytical investigation of the theoretical air specific impulse performance and adiabatic combustion temperatures of several possible ram-jet fuels over a range of equivalence ratios, inlet-air temperatures, and combustion pressures, is presented herein. The fuels include octane-1, 50-percent-magnesium slurry, boron, pentaborane, diborane, hydrogen, carbon, and aluminum. Thermal effects from high combustion temperatures were found to effect considerably the combustion perform… more
Date: September 14, 1953
Creator: Tower, Leonard K. & Gammon, Benson E.
Item Type: Refine your search to only Report
open access

Analytical investigation of icing limit for diamond-shaped airfoil in transonic and supersonic flow

Description: From Introduction: "The results presented herein were calculated for a symmetrical diamond airfoil at zero angle of attack for a range of airfoil-thickness ratios from 0.02 to 0.10, pressure altitude from sea level to 45,000 feet, and free-stream static temperatures to -.40^o F."
Date: January 1953
Creator: Callaghan, Edmund E. & Serafini, John S.
Item Type: Refine your search to only Report
open access

Analytical Investigation of Icing Limit for Diamond-Shaped Airfoil in Transonic and Supersonic Flow

Description: Calculations have been made for the icing limit of a diamond airfoil at zero angle of attack in terms of the stream Mach number, stream temperature, and pressure altitude. The icing limit is defined as a wetted-surface temperature of 320 F and is related to the stream conditions by the method of Hardy. The results show that the point most likely to ice on the airfoil lies immediately behind the shoulder and is subject to possible icing at Mach numbers as high as 1.4.
Date: January 1953
Creator: Callaghan, Edmund E. & Serafini, John S.
Item Type: Refine your search to only Report
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