91 Matching Results

Search Results

Tabulated Pressure Coefficients and Aerodynamic Characteristics Measured in Flight on the Wing of the Douglas D-558-I Airplane for a 1 g Stall, a Speed Run to a Mach Number of 0.90, and a Wind-Up Turn at a Mach Number of 0.86

Description: "Tabulated pressure coefficients and aerodynamic characteristics are presented unanalyzed for six spanwise stations on the right wing of the Douglas D-558-I research airplane (BuAero No. 37972). The data were obtained in a 1 g stall at subcritical Mach numbers, in a speed run to a Mach number of 0.90 and in a wind-up turn at a Mach number of 0.86" (p. 1).
Date: December 15, 1950
Creator: Keener, Earl R. & Pierce, Mary
Partner: UNT Libraries Government Documents Department

Investigation of Perforated Convergent-Divergent Diffusers With Initial Boundary Layer

Description: An experimental investigation was made at Mach number 1.90 of the performance of a series of perforated convergent-divergent supersonic diffusers operating with initial boundary layer, which was induced and controlled by lengths of cylindrical inlets affixed to the diffusers. Supercritical mass-flow and peak total-pressure recoveries were decreased slightly by use of the longest inlets (4 inlet diameters in length). Combinations of cylindrical inlets, perforated diffusers, and subsonic diffuser were evaluated as simulated wind tunnels having second throats. Comparisons with noncontracted configurations of similar scale indicated conservatively computed power reductions of 25 percent.
Date: August 15, 1950
Creator: Weinstein, Maynard I.
Partner: UNT Libraries Government Documents Department

Altitude-Wind-Tunnel Investigation of Combustion-Chamber Performance on J47 Turbojet Engine

Description: From Introduction: "Results are presented to indicate the effect of altitude, flight Mach number, and exhaust-nozzle-outlet area on the combustion efficiency, the losses in total pressure occurring in the combustion chamber, and the fractional loss in engine cycle efficiency resulting from combustion-chamber pressure losses. The engine cycle efficiency is also presented.These results are shown graphically as a fraction of corrected engine speed and in tabular form."
Date: December 15, 1950
Creator: Campbell, Carl E.
Partner: UNT Libraries Government Documents Department

Formulas for the Supersonic Loading, Lift, and Drag of Flat Swept-Back Wings With Leading Edges Behind the Mach Line

Description: "The method of superposition of linearized conical flows has been applied to the calculation of the aerodynamic properties, in supersonic flight, of thin flat, swept-back wings at an angle of attack. The wings are assumed to have rectilinear plan forms, with tips parallel to the stream, and to taper in the conventional sense. The investigation covers the moderately supersonic speed range where the Mach lines from the leading-edge apex lie ahead of the wing" (p. 1147).
Date: March 15, 1950
Creator: Cohen, Doris
Partner: UNT Libraries Government Documents Department

Experimental investigation of a flat plate paddle jet vane operating on a rocket jet

Description: Report presenting the results of static tests conducted for the purpose of determining the lift forces and hinge moments associated with a flat-plate paddle vane, externally hinged near a rocket-nozzle exit and operating on the jet for vane deflection angles ranging from -4 degrees to 25 degrees. Results regarding vane aerodynamic characteristics, performance of rocket motor, and vane erosion
Date: November 15, 1950
Creator: Bond, Aleck C.
Partner: UNT Libraries Government Documents Department

Effect of blade-root fit and lubrication on vibration characteristics of ball-root-type axial-flow-compressor blades

Description: Report presenting the vibration characteristics of several symmetrical ball-root-type blades simulating the mass and natural frequency of axial-flow-compressor blades under various mounting conditions by subjecting them to controlled periodic excitation and centrifugal loading. Results regarding loose single ball-root mounting, loose-lubricated, single ball-root mounting, double ball-root mounting, and damping measurements are provided.
Date: June 15, 1950
Creator: Hanson, Morgan P.
Partner: UNT Libraries Government Documents Department

ESTIMATED MANUFACTURING COSTS FOR THE RECOVERY OF THORIUM AND URANIUM FROM MONAZITE SAND

Description: Costs are estimated for the production of uranium and pure thorium from monazite concentrates. The process involves; reaction of the monazite with caustic soda, dissolution of the hydrous oxides in hydrochloric acid, separation from the bulk of the rare earths by hydroxide precipitation of thorium and uranium, and purification by solvent extraction. (auth)
Date: September 15, 1950
Creator: Calkins, G.D. & Filbert, R.B. Jr.
Partner: UNT Libraries Government Documents Department

Initial flight investigation of a twin engine supersonic ram jet

Description: From Summary: "A flight investigation was made of a supersonic twin-ram-jet test vehicle using short-flame-length burners. The test demonstrated a maximum acceleration of 3.6g and a maximum flight Mach number of 3.02. Data were obtained over a Mach number range from about 1.9 to 3.0, an altitude range from 1,800 to 40,900 feet, and a fuel-air-ratio range from 0.012 to 0.065."
Date: September 15, 1950
Creator: Faget, Maxime A. & Dettwyler, H. Rudolph
Partner: UNT Libraries Government Documents Department

Matrix method of determining the longitudinal-stability coefficients and frequency response of an aircraft from transient flight data

Description: From Summary: "A matrix method is presented for determining the longitudinal-stability coefficients and frequency response of an aircraft from arbitrary maneuvers. The method is devised so that it can be applied to time-history measurements of combinations of such simple quantities as angle of attack, pitching velocity, load factor, elevator angle, and hinge moment to obtain the over-all coefficients. Although the method has been devised primarily for the evaluation of stability coefficients which are of primary interest in most aircraft loads and stability studies, it can be used also, with a simple additional computation, to determine the frequency-response characteristics. The entire procedure can be applied or extended to other problems which can be expressed by linear differential equations."
Date: December 15, 1950
Creator: Donegan, James J. & Pearson, Henry A.
Partner: UNT Libraries Government Documents Department

PATHFINDER ATOMIC POWER PLANT CONCEPTUAL DESIGN STUDY OF CRBR QUICK- OPERATING PRESSURE VESSEL CLOSURE AND SELF-ENERGIZING SEAL TESTS. Final Report

Description: The work to determine the feasibility of using a quickoperating closure for the pressure vessel of the controlled Recirculation Boiling Reactor is described. An outline of the worb performed and the conclusions made is given. Datailed results of the self-energizing seal-evaluation tests are given. (W.D.M.)
Date: October 15, 1950
Creator: Michel, R.G.
Partner: UNT Libraries Government Documents Department

Low-Powered Induction Heater for Testing Use.

Description: Certain laboratory processes require low-powered radio-frequency heating with fine continuous control. A lightweight low-powered induction heater which is capable of delivering about 20 watts of power into a load 12 feet from the heater with fair efficiency was developed to meet this need.
Date: September 15, 1950
Creator: Shipp, R. L.
Partner: UNT Libraries Government Documents Department

DEVELOPMENT OF TECHNIQUES FOR ROLLING URANIUM METAL

Description: Uranium can be rolled from cast metal or forged ingot to sheet satisfactory for cupping, deep drawing, and similar fabrication procedures by a combination of hot breakdown in the neighborhood of 600 deg C and warm finishing at 225 to 325 deg C. Sheet may also be obtained by hot rolling alone and by warm rolling alone, but the combination of hot and warm rolling afforded the best and most practical method to secure good quality sheet in the quantity required. The percent reduction by hot working does not appear to be critical, but at least 60% warm reduction is desirable to obtain complete and controlled grain size by recrystallization with high ductility and strength properties. Except for research investigation, rolling of uranium below 225 deg C is not recommended. Hot rolling of unplated uranium from the as-cast or as-forged surface is recommended, using a bath of 35% Li/sub 2/CO/sub 3/ plus 65% K/sub 2/CO/sub 3/ for a heating medium. No further preparation other than washing the salt from the hot rolled surface is required before warm rolling, and a bath of Meltemp No. 7 oil is recommended for warm rolling. Starting with an as-cast tensile strength averaging 60,000 psi, as-rolled sheet up to 230,000 psi was produced, with elongation averaging 5--8% and tensile to yield strength ratios averaging 75%. Uniform, equi-axed grains are produced upon annealing, and grain sizes can be controlled by choice of annealing temperature and time. (P.C.H.)
Date: November 15, 1950
Creator: Deutsch, D.E.; Hanks, G.S.; Taub, J.M. & Doll, D.T.
Partner: UNT Libraries Government Documents Department

Experimental Investigation of Various Wing-Mounted External Stores on a Wing-Fuselage Combination Having a Sweptback Wing of Inverse Taper Ratio

Description: Report presenting an investigation in the high speed tunnel to determine the effects of several wing-mounted external-store configurations on the aerodynamic characteristics of a model of a swept wing-fuselage combination for a range of Mach numbers. Some of the configurations explored included inboard underwing installations and wing-tip installations. Results regarding lift-drag ratios, drag characteristics, lift-curve slope, and pitching-moment characteristics are provided.
Date: September 15, 1950
Creator: Spreemann, Kenneth P. & Silvers, H. Norman
Partner: UNT Libraries Government Documents Department