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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 1, 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 1, 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 1, 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 1, 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 1, 1946
Creator: Dugan, Paul D.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Airscrew Gyroscopic Moments

Airscrew Gyroscopic Moments

Date: September 1, 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
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