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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 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

An Approximate Method for Estimating the Incompressible Laminar Boundary-Layer Characteristics on a Flat Plate in Slipping Flow

Description: Memorandum presenting an approximate method for the estimation of the properties of the incompressible laminar boundary layer on a flat plate in the slip-flow region using Karman's momentum method. At equivalent stations, the total thickness and the skin friction of a slipping boundary layer are less than that of the normal boundary layer at the same Reynolds number.
Date: May 2, 1949
Creator: Donaldson, Coleman duP.
Item Type: Refine your search to only Report
open access

Characteristics of a 15-Percent-Chord and a 35-Percent-Chord Plain Flap on the NACA 0006 Airfoil Section at High Subsonic Speeds

Description: Memorandum presenting wind-tunnel tests to determine the aerodynamic characteristics of a 15-percent- and a 35-percent-chord plain trailing-edge flap on the NACA 0006 airfoil section. Simultaneous measurements of section lift, drag, and pitching moment were made over a range of Mach numbers, angles of attack, and flap deflections.
Date: October 2, 1947
Creator: Ilk, Richard J.
Item Type: Refine your search to only Report
open access

Columbia Scaling Circuits

Description: Abstract: "The advantages of high scaling ratios in counting random pulses are discussed. The mechanism of the basic circuit used in the Columbia University scaling circuits is described. The difficulties experienced in the performance of the earlier circuits are indicated and modified circuits to eliminate these difficulties are given. Precautions that must be observed in carrying out the constructional details are suggested. The complete circuit and specifications are given in detail for a Sc… more
Date: May 2, 1944
Creator: Glassford, H. A. & Dunning, J. R.
Item Type: Refine your search to only Report
open access

Comparison of performance of AN-F-58 and AN-F-32 fuels in J33-A-23 turbojet engine

Description: Report presenting an investigation using a 4600 pound-thrust turbojet engine as part of a program to determine the comparative performance of fuels conforming to specifications AN-F-58 and AN-F-32. Results regarding the altitude performance, altitude low-speed blow-out limits, idling limits of fuel-metering control, altitude windmilling starts, carbon-deposition rates, and iron oxide contamination are provided.
Date: June 2, 1949
Creator: Wilsted, H. D. & Armstrong, J. C.
Item Type: Refine your search to only Report
open access

Correlation of the drag characteristics of a typical pursuit airplane obtained from high-speed wind-tunnel and flight tests

Description: In order to obtain a correlation of drag data from wind-tunnel and flight tests at high Mach numbers, a typical pursuit airplane, with the propeller removed, was tested in flight at Mach numbers up to 0.755, and the results were compared with wind-tunnel tests of a 1/3-scale model of the airplane. The tests results show that the drag characteristics of the test airplane can be predicted with satisfactory accuracy from tests in the Ames 16-foot high-speed wind tunnel of the Ames Aeronautical Lab… more
Date: November 2, 1944
Creator: Nissen, James M.; Gadeberg, Burnett L. & Hamilton, William T.
Item Type: Refine your search to only Report
open access

Correlation of wind-tunnel and flight determinations of the buffet speed of an airplane equipped with external stores

Description: Tests were made in the Langley 7 by 10 foot tunnel on a model of a fighter-type airplane with external stores. The data obtained is presented and compared to flight-test results to determine the feasibility of estimating flight buffet Mach number from tunnel data.
Date: March 2, 1948
Creator: Silvers, H. Norman & Spreemann, Kenneth P.
Item Type: Refine your search to only Report
open access

The Determination of Uranium by Potentiometric Titration with Ferric Sulfate

Description: Abstract: "A method for the potentiometric titration of uranium with ferric sulfate is described. This method provides a rapid and accurate way of determining the element in solutions free from interfering ions. Application of the method to analysis of pure uranium compounds and to uranium recovered from contaminated solutions by suitable procedures is briefly discussed."
Date: November 2, 1949
Creator: Grimes, W. R.
Item Type: Refine your search to only Report
open access

The Dissolution of Thorium Metal and Thorium Dioxide in HNO3 - HF and HNO3- ( NH4 ) 2 SiF6 Mixtures

Description: Abstract. A satisfactory method has been found for dissolving thorium metal and thorium oxide in heat-treated 25-12 stainless steel vessels without excessive corrosion of the vessels. The dissolution medium consists of strong HNO3 containing a small amount of fluoride or fluo-silicate. the fluoride required has no harmful effects on a subsequent solvent-extraction step for a separation of uranium isotopes from the dissolved thorium.
Date: August 2, 1946
Creator: Schuler, Frederick W.; Steahly, Frank L. & Stoughton, Raymond W.
Item Type: Refine your search to only Report
open access

Effect of Inlet Air Distortion on the Steady-State and Surge Characteristics of an Axial-Flow Turbojet Compressor

Description: "An investigation was conducted in an altitude test chamber to determine the effects of inlet airflow distortion on the compressor steady-state and surge characteristics of a high-pressure ratio, axial-flow turbojet engine. Circumferential-type inlet flow distortions were investigated, which covered a range of distortion sector angles from 20 deg to 168 deg and distortion levels up to 22 percent. The presence of inlet airflow distortions at the compressor face resulted in a substantial increase… more
Date: January 2, 1948
Creator: Ciepluch, Carl C.
Item Type: Refine your search to only Report
open access

Effect of Radiation on Chromate in Water. III. Inhibition Experiments in the CP-3 Pile

Description: Abstract. The effect of various inhibitors on the production of CrIII in W waters containing chromatic has been studies at a variety of pH's in the CP-3 pile. The addition of 2 ppm NaClO3 appears to have little effect a a pH of 5.3, but 2 ppm NaClO3 cr 0.15 ppm of Cl2 (in the form of NaOCl) somewhat decreases the amount of chromatic reduced at a pH of 7.1. The inhibition is not great enough, however, to reduce the amount of CrIII formed to the maximum concentration permissible at W (0.02 ppm)… more
Date: November 2, 1944
Creator: Bowman, M. G.; Burton, Milton, 1902-; Davis, S. G., 1907-; Ghormley, J. A. & Gordon, S.
Item Type: Refine your search to only Report
open access

The Effect of Thermal Cycling on the Thermal Transfer from a Sand Blasted Slug to an Unbonded Jacket

Description: Abstract. Measurements were made to determine the effect of thermal cycling on heat transfer from slug to jack using a slug with a sand blasted surface. The value of the transfer coefficient h decreased from initial values ranging from 10 to [formula], to values and [formula] after 1700 cycles, and to a range of 0.15 to 0.45 [formula] after 3200 cycles. Comparisons are made with the results found for slugs with different surfaces.
Date: April 2, 1945
Creator: Bentley, Robert R.
Item Type: Refine your search to only Report
open access

The Effects of Neutron Bombardment on the Electrical Resistance of Aluminum, Beryllium and Tuballoy (Uranium)

Description: Abstract. Wigner effects on aluminum, beryllium, and tuballoy have been studied by the electrical resistance method. Samples were exposed during an interval which would have produced an increase of approximately 22% in resistance of AGOT-K graphite. The resistance of tuballoy increased approximately 1%. It is shown that the increase can be accounted for by the amount of fission product impurity formed during the exposure. Neither aluminum nor beryllium showed any change. In the case of Be,… more
Date: November 2, 1944
Creator: Royal, J.
Item Type: Refine your search to only Report
open access

Evaluation of Gust and Draft Velocities from Flights of P-61C Airplanes within Thunderstorms August 13, 1947 to August 15, 1947 at Clinton County Army Air Field, Ohio

Description: The gust and draft velocities from records of NACA instruments installed in P-61C airplanes participating in thunderstorm flights at Clinton County Army Air Field, Ohio, from August 13, 1947 to August 15, 1947 are presented.
Date: February 2, 1948
Creator: Funk, Jack
Item Type: Refine your search to only Report
open access

Evaluation of Gust and Draft Velocities from Flights of P-61C Airplanes within Thunderstorms May 13, 1947 to May 29, 1947 at Clinton County Army Air Field, Ohio

Description: The gust and draft velocities evaluated from records of NACA instruments installed in P-61C airplanes participating in thunderstorm flights at Clinton County Army Air Field, Ohio, from May 13 to May 29, 1947 are presented.
Date: January 2, 1948
Creator: Tolefson, Harold B.
Item Type: Refine your search to only Report
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