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  Partner: UNT Libraries Government Documents Department
 Decade: 1940-1949
 Year: 1946
 Collection: Technical Report Archive and Image Library
10 M.C. Wide Band Amplefier and Scope

10 M.C. Wide Band Amplefier and Scope

Date: 1946
Creator: Elmore, W. C.
Description: Technical drawing of an amplifier for a nuclear reactor.
Contributing Partner: UNT Libraries Government Documents Department
300-400 V Regulated Supply

300-400 V Regulated Supply

Date: 1946?
Creator: U.S. Atomic Energy Commission
Description: 1 technical drawing of a regulated supply of 300-400 volts for nuclear reactors.
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics including scale effect of several wings and bodies alone and in combination at a Mach number of 1.53

Aerodynamic characteristics including scale effect of several wings and bodies alone and in combination at a Mach number of 1.53

Date: December 20, 1946
Creator: Van Dyke, Milton D
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics of four NACA airfoil sections designed for helicopter rotor blades

Aerodynamic characteristics of four NACA airfoil sections designed for helicopter rotor blades

Date: February 1946
Creator: Rice, Fred J , Jr
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics of several modifications of a 0.45-scale model of the vertical tail of the Curtiss XP-62 airplane

Aerodynamic characteristics of several modifications of a 0.45-scale model of the vertical tail of the Curtiss XP-62 airplane

Date: July 1946
Creator: Liddell, Robert B.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic data for a wing section of the Republic XF-12 airplane equipped with a double slotted flap

Aerodynamic data for a wing section of the Republic XF-12 airplane equipped with a double slotted flap

Date: January 1946
Creator: Cahill, Jones F.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamics of the carburetor air scoop and the engine cowling of a single-engine torpedo-bomber-type airplane

Aerodynamics of the carburetor air scoop and the engine cowling of a single-engine torpedo-bomber-type airplane

Date: June 1946
Creator: Palter, Herman
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Air-flow and performance characteristics of engine-stage supercharger of a double-row radial aircraft engine II : effect of design variables

Air-flow and performance characteristics of engine-stage supercharger of a double-row radial aircraft engine II : effect of design variables

Date: August 1946
Creator: Dugan, Paul D.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Airscrew Gyroscopic Moments

Airscrew Gyroscopic Moments

Date: September 1946
Creator: Bock, G.
Description: When flying in a turn or pulling out of a dive, the airscrew exerts a gyroscopic moment on the aircraft, In the case of airscrews with three or more blades, arranged symmetrically, the value of the gyroscopic moment is J(sub x) omega(sub x) omega(sub y), where J(sub x) denotes the axial moment of inertia about the axis of rotation of the airscrew, omega(sub x) the angular upeed of the airscrew about its axis, and omega (sub Y) the rotary speed of the whole aircraft about an axis parallel to the plane of the airscrew (e.g., when pulling up, the transverse axis of the aircraft). The gyroscopic moment then tends to rotate the aircraft about an axis perpendicular to those of the two angular speeds and, in the came of airscrews with three or more blades, is constant during a revolution of the airscrew. With two-bladed airscrews, on the contrary, although the calculate gyroscopic moment represents the mean value in time, it fluctuates about this value with a frequency equal to twice the revolutions per minute. In addition, pulsating moments likewise occur about the other two axes. This fact is known from the theory of the asymmetrical gyro; the calculations that ...
Contributing Partner: UNT Libraries Government Documents Department
Altitude cooling investigation of the R-2800-21 engine in the P-47G airplane II : investigation of the engine & airplane variables affecting the cylinder temperature distribution

Altitude cooling investigation of the R-2800-21 engine in the P-47G airplane II : investigation of the engine & airplane variables affecting the cylinder temperature distribution

Date: October 9, 1946
Creator: Pesman, Gerard J & Kaufman, Samuel J
Description: The data obtained from cooling tests of an R-2800-21 engine installed in a p-47G airplane were studied to determine which engine and airplane operation variables were mainly responsible for the extremely uneven temperature distribution among the 18 engine cylinders obtained at the medium and high engine-power conditions. The tests consisted of flights at altitudes from 5000 to 35,000 feet for the normal range of engine and airplane operation. The results of the study showed that a flow condition in the induction system associated with the wide-open throttle position, which affected either the fuel air or charge distribution, was primarily responsible for the uneven temperature distribution. For the range of fuel-air ratios tested (0.080 to 0.102), the temperature distribution remained essentially unchanged. The individual effects of thrust-axis inclination, cowl-flap opening, and quantity of auxiliary air were found to be secondary in importance. At low angles of throttle opening, engine speed was found to have little effect on the temperature pattern.
Contributing Partner: UNT Libraries Government Documents Department
Altitude cooling investigation of the R-2800-21 engine in the P-47g airplane III : individual-cylinder temperature reduction by means of intake-pipe throttle and by coolant injection

Altitude cooling investigation of the R-2800-21 engine in the P-47g airplane III : individual-cylinder temperature reduction by means of intake-pipe throttle and by coolant injection

Date: October 9, 1946
Creator: Bell, E Barton; Valerino, Michael F & Manganiello, Eugene J
Description: Flight tests were conducted on a R-2800-21 engine in the P-47G airplane to determine the effect on the wall temperatures of cylinder 10 of throttling the charge in the intake pipe and of injecting a water-ethanol coolant into the intake pipe. Cylinder 10 was chosen for this investigation because it runs abnormally hot (head temperatures of the order of 45 F higher than those of the next hottest cylinder) at the medium and high-power conditions. Tests with interchanged cylinders showed that the excessive temperatures of cylinder 10 were inherent in the cylinder location and were not due to the mechanical condition of the cylinder assembly. Throttling the charge in the intake pipe is a simpler method than coolant injection into the intake pipe particularly when only one cylinder is considerably hotter than any other. Coolant injection into the individual cylinders is a more efficient method than throttling in the intake pipe and is warranted when several cylinders are to be cooled or when parts of the complex equipment required are already available.
Contributing Partner: UNT Libraries Government Documents Department
Altitude-Wind-Tunnel Investigation of Oil-System Performance of XR-4360-8 Engine in XTB2D-1 Airplane

Altitude-Wind-Tunnel Investigation of Oil-System Performance of XR-4360-8 Engine in XTB2D-1 Airplane

Date: September 4, 1946
Creator: Conrad, E. William
Description: An investigation was conducted in the Cleveland altitude wind tunnel to determine the aerodynamic characteristics and the oil delivery critical altitude of the oil-cooler installation of an XTB2D-1 airplane. The investigation was made with the propeller removed end with the engine operating at 1800 brake horsepower, an altitude of 15,000 feet (except for tests of oil-delivery critical altitude), oil-cooler flap deflections from -20 degrees to 20 degrees and inclinations of the thrust axis of 0 degrees, 1.5 degrees, and 6 degrees. At an inclination of the thrust axis of 0 degrees and with the propeller operating, the total-pressure recovery coefficient at the face of the oil cooler varied from 0.84 to 1.10 depending on the flap deflection. With the propeller removed, the best pressure recovery at the face of the oil cooler was obtained at an inclination of the thrust axis of 1.5 degrees. Air-flow separation occurred on the inner surface of the upper lip of the oil-cooler duct inlet at an inclination of the thrust axis of 0 degrees and on the inner surface of the lower lip at 6 degrees. Static pressure coefficients over the duct lips were sufficiently low that no trouble from compressibility would be encountered ...
Contributing Partner: UNT Libraries Government Documents Department
Altitude-Wind-Tunnel Investigation of Performance of Several Propellers on YP-47M Airplane at High Blade Loading, 1, Aeroproducts H20C-162-X11M2 Four-Blade Propeller

Altitude-Wind-Tunnel Investigation of Performance of Several Propellers on YP-47M Airplane at High Blade Loading, 1, Aeroproducts H20C-162-X11M2 Four-Blade Propeller

Date: October 11, 1946
Creator: Saari, Martin J. & Wallner, Lewis E.
Description: An investigation was made in the Cleveland Altitude wind tunnel to determine the performance of an Aeroproducts H20C-162-X11M2 four-blade propeller on a YP-47M airplane at high blade loadings and high engine powers. The propeller characteristics were obtained for a range of power coefficients from 0.30 to 1.00 at free-stream Mach numbers of 0.40 and 0.50. The results of the force measurements are indicative only of trends in propeller efficiency with changes in power coefficient and advance-diameter ratio because unknown interference effects existed during the investigation. At a free-stream Mach number of 0.40, the envelopes of the efficiency curves decreased about 11% between advance-diameter ratios of 2.40 and 4.40. An increase in power coefficient from 0.30 to 0.80 at an advance-diameter ratio of 2.40 had little effect on the propeller efficiency. A change in power coefficient from 0.40 to 1.00 at an advance-diameter ratio of 4.40 increased the propeller efficiency by about 40%. For conditions below the stall the thrust loading on the outboard blade sections increased more rapidly than on the inboard sections as the power coefficient was increased or as the advance-diameter ratio was decreased. For conditions beyond the stall, the thrust loading decreased on the outboard sections and ...
Contributing Partner: UNT Libraries Government Documents Department
Altitude-Wind-Tunnel Investigation of Performance of Several Propellers on YP-47M Airplane at High Blade Loading, 2, Curtiss 838-1C2-18R1 Four-Blade Propeller

Altitude-Wind-Tunnel Investigation of Performance of Several Propellers on YP-47M Airplane at High Blade Loading, 2, Curtiss 838-1C2-18R1 Four-Blade Propeller

Date: November 26, 1946
Creator: Wallner, Lewis E. & Sorin, Solomon M.
Description: An investigation was conducted in the Cleveland altitude wind tunnel to determine the performance of a Curtiss propeller with four 838-lC2-lSRl blades on a YP-47M airplane at high blade loadings and engine powers. The study was made for a range of power coefficients between 0.30 and 1.00 at free-stream Mach numbers of 0.40 and 0.50. The results of the force measurements indicate primarily the trend of propeller efficiency for changes in power coefficient or advance-diameter ratio, inasmuch as corrections for the effects of tunnel-wall constriction on the installation have not been applied. Slip-stream pressure surveys across the propeller disk are presented to illustrate blade thrust load distribution for several operating conditions. At a free-stream Mach number of 0.40, nearly constant peak efficiencies were obtained at power coefficients from 0.30 to 0.70. A change in power coefficient from 0.70 to 0.90 reduced the peak efficiency about 5 percent. Blade stall at the tip sections became evident for a power coefficient of 0.91 when the advance-diameter ratio was reduced to 1.87. At a free-stream Mach number of 0.50, the highest propeller efficiencies were obtained for power coefficients from 0.80 to 1.00 at advance-diameter ratios above 2.90. At advance-diameter ratios below 2.90, the ...
Contributing Partner: UNT Libraries Government Documents Department
Altitude-Wind-Tunnel Investigation of Performance of Several Propellers on YP-47M Airplane at High Blade Loadings, 4, Curtiss 732-1C2-0 Four-Blade Propeller

Altitude-Wind-Tunnel Investigation of Performance of Several Propellers on YP-47M Airplane at High Blade Loadings, 4, Curtiss 732-1C2-0 Four-Blade Propeller

Date: November 26, 1946
Creator: Saari, Martin J. & Sorin, Solomon M.
Description: An altitude-wind-tunnel investigation has been made to determine the performance of a Curtiss 732-1C2-0 four-blade propeller on a YP-47M airplane at high blade loadings and engine power. Propeller characteristics were obtained for a range of power coefficients from 0.30 to 1.00 at free-stream Mach numbers of 0.40 and .50.
Contributing Partner: UNT Libraries Government Documents Department
Altitude-Wind-Tunnel Investigation of Performance of Several Propellers on YP-47M Airplane at High Blade Loadings, 6, Hamilton Standard 6507A-2 Four- and Three-Blade Propellers

Altitude-Wind-Tunnel Investigation of Performance of Several Propellers on YP-47M Airplane at High Blade Loadings, 6, Hamilton Standard 6507A-2 Four- and Three-Blade Propellers

Date: December 19, 1946
Creator: Saari, Martin J. & Sorin, Solomon M.
Description: An altitude-wind-tunnel investigation has been made to determine the performance of Hamilton Standard 6507A-2 four-blade and three-blade propellers on a YP-47M airplane at high blade loadings and high engine powers. Characteristics of the four-blase propeller were obtained for a range of power coefficients from 0.10 to 1.00 at free-stream Mach numbers of 0.20, 0.30, 0.40. Characteristics of the three-blade propeller were obtained for a range of power coefficients from 0.30 to 1.00 at a free-stream Mach number of 0.40. Results of the force measurements indicate primarily the trend of propeller efficiency for changes in power coefficient or advance-diameter ratio because no corrections for the effects of tunnel-wall constriction on the installation were applied. Slipstream surveys are presented to illustrate blade thrust load distribution for certain operating conditions. Within the range of advance-diameter ratios investigated at each free-stream Mach number, the efficiency of the four-blade propeller decreased as the power coefficient was increased from 0.10 to 1.00. For the three-blade propeller, nearly constant maximum efficiencies were obtained for power coefficients from 0.32 to 0.63 at advance-diameter ratios between 1.90 and 3.00. In general, for conditions below the stall and critical tip Mach number, the maximum thrust load shifted from the inboard ...
Contributing Partner: UNT Libraries Government Documents Department
Altitude-Wind-Tunnel Investigation of Performance of Several Propellers on YP-47M Airplane at High Blade Loadings V - Curtiss 836-14C2-18R1 Four-Blade Propeller

Altitude-Wind-Tunnel Investigation of Performance of Several Propellers on YP-47M Airplane at High Blade Loadings V - Curtiss 836-14C2-18R1 Four-Blade Propeller

Date: December 2, 1946
Creator: Saari, Martin J. & Wallner, Lewis E.
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 powers from 150 to 2500 brake horsepower, and for engine speeds from 1000 to 2900 rpm. The propeller efficiencies were obtained from force measurements and the blade thrust load distribution was obtained by two diametrically opposed slipstream survey rakes shown in this paper.
Contributing Partner: UNT Libraries Government Documents Department
Altitude-wind-tunnel investigations of thrust augmentation of a turbojet engine performance with tail-pipe burning

Altitude-wind-tunnel investigations of thrust augmentation of a turbojet engine performance with tail-pipe burning

Date: September 25, 1946
Creator: Fleming, W A & Dietz, R O
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Altitude-wind-tunnel tests of power-plant installation in jet-propelled fighter

Altitude-wind-tunnel tests of power-plant installation in jet-propelled fighter

Date: February 1946
Creator: Jagger, James M.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Analyses of Alaska Coals

Analyses of Alaska Coals

Date: 1946
Creator: Gates, George O. & Fieldner, Arno Carl
Description: Report issued by the Bureau of Mines discussing the coal fields of Alaska. Analyses of the Alaskan coal fields are presented in detail. This report includes tables, and a map.
Contributing Partner: UNT Libraries Government Documents Department
Analysis of available data on the effects of tabs on control-surface hinge moments

Analysis of available data on the effects of tabs on control-surface hinge moments

Date: May 1946
Creator: Crandall, Stewart M & Murray, Harry E
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Analysis of cooling limitations and effect of engine-cooling improvements on level-flight cruising performance of four-engine heavy bomber

Analysis of cooling limitations and effect of engine-cooling improvements on level-flight cruising performance of four-engine heavy bomber

Date: March 14, 1946
Creator: Marble, Frank E; Miller, Marlon A & Bell, E Barton
Description: The NACA has developed means, including an injection impeller and ducted head baffles, to improve the cooling characteristics of the 3350-cubic-inch-displacement radial engines installed in a four-engine heavy bomber. The improvements afforded proper cooling of the rear-row exhaust-valve seats for a wide range of cowl-flap angles, mixture strengths, and airplane speeds. The results of flight tests with this airplane are used as a basis for a study to determine the manner and the extent to which the airplane performance was limited by engine cooling. By means of this analysis for both the standard airplane and the airplane with engine-cooling modifications, comparison of the specific range at particular conditions and comparison of the cruising-performance limitations was made.
Contributing Partner: UNT Libraries Government Documents Department
Analysis of deep rectangular shear web above buckling load

Analysis of deep rectangular shear web above buckling load

Date: March 1946
Creator: Levy, Samuel; Woolley, Ruth M & Corrick, Josephine N
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Analysis of Effect of Rolling Pull-Outs on Wing and Aileron Loads of a Fighter Airplane

Analysis of Effect of Rolling Pull-Outs on Wing and Aileron Loads of a Fighter Airplane

Date: March 1946
Creator: Pearson, Henry A. & Aiken, William S.
Description: An analysis was made to determine the effect of rolling pull-out maneuvers on the wing and aileron loads of a typical fighter airplane, the P-47B. The results obtained indicate that higher loads are imposed upon wings and ailerons because of the rolling pull-out maneuver, than would be obtained by application of the loading requirements to which the airplane was designed. An increase of 102 lb or 15 percent of wing weight would be required if the wing were designed for rolling pull-out maneuver. It was also determined that the requirements by which the aileron was originally designed were inadequate.
Contributing Partner: UNT Libraries Government Documents Department
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