Technical Report Archive & Image Library (TRAIL) - 59 Matching Results

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The solvent-extraction performance of small scale redox IA columns using Fenske helix packing, ammonium nitrate salting agent, and unirradiated uranium

Description: A report which deals with the Redox IA Column studies made in small-scale columns packed with 3/16-in. Fenske helices and using NH4NO3 salting agent.
Date: April 13, 1949
Creator: Woodfield, F. W.; Bradley, J. G.; Switzer, W. O. & Merrill, E. T.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Crystal Densities of Uranium Chlorides

Description: Abstract: "Using xylene as the densimetric solvent, the crystal densities have been determined by the pyknometric method for the following chlorides, UCl3, UCl4, UCl6(UCl4), UCl6 and U02Cl2."
Date: December 13, 1946
Creator: Sterett, C. C. & Calkins, V. P.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Effect of NACA Injection Impeller and Ducted Head Baffles on Flight Cooling Performance of Double-Row Radial Engine in Four-Engine Heavy Bomber

Description: "The NACA has conducted a flight investigation to improve the cooling characteristics of the installation of a double-row radial engine. The tests reported herein concern the use of the NACA injection impeller and ducted head baffles in various combinations on both the port inboard and the port outboard engines. The performance of the modified installation was evaluated by comparing it with that of the standard engines" (p. 1).
Date: April 13, 1945
Creator: Marble, Frank E.; Miller, Mahlon A. & Vensel, Joseph R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Experimental investigation of velocity distributions of downstream of single duct bends

Description: Report presenting measurements of the velocity distributions at the outlet of a large number of duct elbows of round and elliptical as well as square and rectangular cross section at a range of Reynolds numbers. Special investigations include measurements of the decay of velocity patterns produced by curved ducts and the effect of asymmetrical upstream velocity distributions. Results regarding typical distributions, tabulation of principal results, and special investigations are provided.
Date: January 13, 1947
Creator: Weske, John R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Investigation of shock diffusers at Mach number 1.85 3: multiple-shock and curved-contour projecting cones

Description: Report presenting total-pressure recoveries obtained with four-cone inlet combinations at Mach number 1.85. The configurations tested included a cone designed to produce three oblique shocks ahead of the diffuser inlet combined with two other inlets, a cone generated by a parabolic arc in combination with two other inlets, a cone-inlet combination designed to produce an isentropic entrance flow at 0 degrees angle of attack, and a 30 degree single-shock cone combined with a perforated inlet sect… more
Date: August 13, 1947
Creator: Moeckel, W. E. & Connors, J. F.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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An investigation of the effect of tip shape on the low-speed aerodynamic characteristics of large-scale swept wings

Description: Report presenting an investigation of the effect of tip shape on the aerodynamic characteristics of large-scale 45 degrees swept-forward and 45 degrees swept-back wings. The results show that none of the variations of tip shape investigated nor the addition of bodies of revolution at the tips produced major changes in the characteristics of the swept wings.
Date: November 13, 1947
Creator: Walling, Walter C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Free-Flight Investigation of Fullspan, 0.2 Chord Plain Ailerons at High Subsonic, Transonic, and Supersonic Speeds to Determine Some Effects of Wing Sweepback, Taper, Aspect Ratio, and Section-Thickness Ratio

Description: Report presenting an aerodynamic-control-effectiveness investigation using free-flight rocket-propelled RM-5 test vehicles at high subsonic, transonic, and supersonic speeds. Results regarding aileron control characteristics and drag measurements are provided.
Date: August 13, 1947
Creator: Sandahl, Carl A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Theoretical analysis of the performance of a supersonic ducted rocket

Description: Report presenting calculated performance characteristics of a ducted rocket with gasoline and liquid oxygen as the fuel mixture and with a mass flow of 1 slug per second. Evaluations of net thrust, frontal area, thrust per unit frontal area, and specific fuel consumption are given for all of the flight conditions under which it might operate.
Date: February 13, 1948
Creator: Hensley, Reece V.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Drag of a Wing-Body Configuration Consisting of a Swept-Forward Tapered Wing Mounted on a Body of Fineness Ratio 12 Measured During Free Fall at Transonic Speeds

Description: Report discussing an investigation to determine the drag of a configuration with a body of fitness ratio 12 with stabilizing tail surfaces and a 12-percent-thick 30-degree swept-forward wing using the free-fall method. The drag oft he wing and the total drag were measured separately and compared. The swept-forward wing was found to greatly increase the effect of drag on the body-tail combination.
Date: March 13, 1947
Creator: Thompson, Jim Rogers & Mathews, Charles W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Flight Characteristics at Low Speed of Delta-Wing Models

Description: Report presenting an investigation to obtain a survey of the flying characteristics at low speeds of models with low-aspect-ratio delta wings. Four models with triangular plan-form sweptback wings and five models with the tips cut off to give taper ratios were tested. Results regarding the stability and control characteristics of each of the models is provided.
Date: January 13, 1948
Creator: McKinney, Marion O., Jr. & Drake, Hubert M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Measurements of the wing and tail loads during the acceptance tests of Bell XS-1 research airplane

Description: Report presenting flight measurements obtained during acceptance tests conducted by the Bell Aircraft Corporation on the XS-1 research airplane. The primary focus was on the aerodynamic loads, handling qualities, maximum lift, and buffet boundaries of the airplane.
Date: April 13, 1948
Creator: Beeler, De E. & Mayer, John P.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Factors Affecting Lateral Stability and Controllability

Description: The effects on dynamic lateral stability and controllability of some of the important aerodynamic and mass characteristics are discussed and methods are presented for estimating the various stability parameters to be used in the calculation of the dynamic lateral stability of airplanes with swept and low-aspect-ratio wings.
Date: May 13, 1948
Creator: Campbell, John P. & Toll, Thomas A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Low-Speed Characteristics in Pitch of a 42 Degree Sweptback Wing With Aspect Ratio 3.9 and Circular-Arc Airfoil Sections

Description: Report presenting tests in a pressure tunnel to determine the low-speed pitch characteristics of a 42 degree sweptback wing with circular-arc airfoil sections. Information regarding the characteristics of basic wing, leading-edge flap investigation, and effects of fuselage are provided.
Date: November 13, 1947
Creator: Neely, Robert H. & Koven, William
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Experimental investigation of pressure fluctuations in 3.6 inch ram jet at Mach number 1.92

Description: Report presenting an experimental study of the pressure fluctuations at the combustion-chamber inlets of a ramjet operating a Mach number of 1.92 in the supersonic tunnel. Results are presented for two burner configurations of different operating characteristics to indicate trends in pressure magnitude, frequency, and wave form. Results regarding the perforated conical flame holder, regenerative-type burner, and diffuser total-pressure recovery are provided.
Date: October 13, 1949
Creator: Connors, James F. & Schroeder, Albert H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Flight Tests to Determine the Effect of Taper on the Zero-Lift Drag of Wings at Low Supersonic Speeds

Description: Report presenting the results of tests to determine the effect of taper on the zero-lift drag of wings of constant exposed aspect ratio at low supersonic speeds. Findings indicated that maximum thickness, leading-edge, and trailing-edge sweep are all important in determining the drag coefficient of a tapered wing.
Date: July 13, 1947
Creator: Alexander, Sidney R. & Nelson, Robert L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Preliminary Investigation of a Variable Mass-Flow Supersonic Nose Inlet

Description: Memorandum presenting a method for varying the mass flow of supersonic inlets with a circular cross section and a central body. The method consists of changing the size of the entering stream tube by means of an inflatable boot on the surface of the central body.
Date: December 13, 1949
Creator: Hayes, Clyde
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Preliminary Results of NACA Transonic Flights of the XS-1 Airplane With a 10-Percent-Thick Wing and 8-Percent-Thick Horizontal Tail

Description: Report presenting transonic speed testing utilizing a rocket-powered Bell XS-1 airplane with 10-percent-thick wing and 8-percent-thick horizontal tail. Information is provided for flights up to Mach number 1.06 and altitudes of about 40,000 feet. Results regarding the variation of control-surface positions and forces and sideslip angle with Mach number, time history, rudder effectiveness, and lateral oscillations are provided.
Date: October 13, 1948
Creator: Drake, Hubert M.; Goodman, Harold R. & Hoover, Herbert H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

An Investigation of the Characteristics of Three NACA 1-Series Nose Inlets at Subcritical and Supercritical Mach Numbers

Description: Report presenting an investigation of the characteristics of three representative NACA 1-series nose inlets over a Mach number range extending from 0.4 to 0.925 in the high-speed wind tunnel. Results regarding pressure distribution, drag, and some potential design considerations are provided.
Date: January 13, 1949
Creator: Pendley, Robert E. & Smith, Norman F.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Evaluation of Gust and Draft Velocities From Flights of P-61C Airplanes Within Thunderstorms July 31, 1947 to August 6, 1947 at Clinton County Army Air Field, Ohio

Description: Memorandum presenting the results of measurements of gust and draft velocities within thunderstorms at an air field over a 7-day period. The data are summarized in tables and compared to previous flights.
Date: February 13, 1948
Creator: Funk, Jack
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Study of compressor systems for a gas-generator engine

Description: Report presenting various methods of providing compressor-capacity and pressure-ratio control in the gas-generator type of compound engine over a range of altitudes. The analytical results indicated that the best method of control is that in which the first stage of compression is carried out in a variable-speed supercharger driven by a hydraulic slip coupling. Results regarding the constant-pressure-ratio compressor, constant-volume compressor, comparison of piston-type and rotary compressors,… more
Date: April 13, 1949
Creator: Sather, Bernard I. & Tauschek, Max J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Effect of temperature on performance of several ejector configurations

Description: Report presenting an investigation to determine the effect of the primary-jet temperature on the performance of several ejector configurations. The performance of ejectors expressed in terms of the ratio of weight of secondary air flow to primary air flow was found to be affected by temperature in two ways.
Date: June 13, 1949
Creator: Wilsted, H. D.; Huddleston, S. C. & Ellis, C. W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Restraint provided a flat rectangular plate by a sturdy stiffener along an edge of the plate

Description: From Summary: "A sturdy stiffener is defined as a stiffener of such proportions that it does not suffer cross-sectional distortion when moments are applied to some part of the cross section. When such a stiffener is attached to one edge of a plate, it will resist rotation of that edge of the plate by means of its torsional properties. A formula is given for the restraint coefficient provided the plate by such a stiffener. This coefficient is required for the calculation of the critical compress… more
Date: March 13, 1941
Creator: Lundquist, Eugene E. & Stowell, Elbridge Z.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Wind-Tunnel Tests of Four- and Six-Blade Single- and Dual-Rotating Tractor Propellers

Description: "Test of 10-foot diameter, four and six blade single-rotating and dual-rotating propellers were conducted in the NACA propeller-research tunnel. The propellers were mounted at the front end of a streamline body incorporating spinners to house the hub portions. The effect of a symmetrical wing mounted in the slipstream ranged from 20 degrees to 65 degrees setting corresponds to airplane speeds greater than 500 miles per hour. The results indicate that dual-rotating propellers were from 0 to 6 pe… more
Date: July 13, 1942
Creator: Biermann, David & Hartman, Edwin P.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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