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  Partner: UNT Libraries Government Documents Department
 Collection: Technical Report Archive and Image Library
Standard X-ray Diffraction Powder Patterns: Section 18. Data for 58 Substances

Standard X-ray Diffraction Powder Patterns: Section 18. Data for 58 Substances

Date: October 1981
Creator: Morris, Marlene C.; McMurdie, Howard F.; Evans, Eloise H.; Paretzkin, Boris; Parker, Harry S.; Panagiotopoulos, Nicolas C. et al.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aeroradioactivity Survey and Areal Geology of the Hanford Plant Area, Washington and Oregon (ARMS-I)

Aeroradioactivity Survey and Areal Geology of the Hanford Plant Area, Washington and Oregon (ARMS-I)

Date: March 1961
Creator: Schmidt, Robert George
Description: Report regarding an airborne gamma-radioactivity survey that took place over a 9,000 square mile area in south-central Washington and north-central Oregon. Topics include the types of bedrock noted in the area as well as their levels of radioactivity.
Contributing Partner: UNT Libraries Government Documents Department
An investigation of the experimental aerodynamic loading on a model helicopter rotor blade

An investigation of the experimental aerodynamic loading on a model helicopter rotor blade

Date: May 1, 1953
Creator: Meyer, John R , Jr; Falabella, Gaetano, Jr & NACA
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Avia pursuit airplane B.H. 21

Avia pursuit airplane B.H. 21

Date: November 1, 1926
Creator: Serryer, J
Description: Built by the 'Czecho-Slovakian' aircraft factory, AVIA, the B.H. 21, has a top speed of 250 MPH, and carries 120 kg of gasoline and 20 kg of oil, giving it a radius of action of 600-650 km. It is equipped with a Hispano-Suiza engine capable of 300 HP.
Contributing Partner: UNT Libraries Government Documents Department
Lockheed "Vega" airplane : a commercial cabin monoplane

Lockheed "Vega" airplane : a commercial cabin monoplane

Date: November 1, 1927
Creator: unknown
Description: The Vega is a high wing monoplane suitable for commercial purposes. It can seat 6 passengers or 100 cubic feet of cargo.
Contributing Partner: UNT Libraries Government Documents Department
The Westland "Widgeon III" "Cirrus II: or "Genet II" engine

The Westland "Widgeon III" "Cirrus II: or "Genet II" engine

Date: August 1, 1927
Creator: unknown
Description: The Widgeon III is a parasol type monoplane. One of it's strongest features was the high degree of visibility available to the pilot.
Contributing Partner: UNT Libraries Government Documents Department
The Mureaux "Brunet 3C2" pursuit airplane

The Mureaux "Brunet 3C2" pursuit airplane

Date: May 1, 1927
Creator: Serryer, J
Description: Designed by Engineer Brunet, the 3C2 is an all metal monoplane with two engines and provision for six machine guns and 12 10 Kg. bombs.
Contributing Partner: UNT Libraries Government Documents Department
The Armstrong Whitworth "Starling" (British) : (single seat fighter)

The Armstrong Whitworth "Starling" (British) : (single seat fighter)

Date: September 1, 1928
Creator: unknown
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Effect of ice formations on section drag of swept NACA 63A-009 airfoil with partical-span leading-edge slat for various modes of thermal ice protection

Effect of ice formations on section drag of swept NACA 63A-009 airfoil with partical-span leading-edge slat for various modes of thermal ice protection

Date: March 15, 1954
Creator: Von Glahn, Uwe H & Gray, Vernon H
Description: Studies were made to determine the effect of ice formations on the section drag of a 6.9-foot-chord 36 degree swept NACA 63A-009 airfoil with partial-span leading-edge slat. In general, the icing of a thin swept airfoil will result in greater aerodynamic penalties than for a thick unswept airfoil. Glaze-ice formations at the leading edge of the airfoil caused large increases in section drag even at liquid-water content of 0.39 gram per cubic meter. The use of an ice-free parting strip in the stagnation region caused a negligible change in drag compared with a completely unheated airfoil. Cyclic de-icing when properly applied caused the drag to decrease almost to the bare-airfoil drag value.
Contributing Partner: UNT Libraries Government Documents Department
Investigation of turbines for driving supersonic compressors II : performance of first configuration with 2.2 percent reduction in nozzle flow area / Warner L. Stewart, Harold J. Schum, Robert Y. Wong

Investigation of turbines for driving supersonic compressors II : performance of first configuration with 2.2 percent reduction in nozzle flow area / Warner L. Stewart, Harold J. Schum, Robert Y. Wong

Date: July 22, 1952
Creator: Stewart, Warner L; Schum, Harold J & Wong, Robert Y
Description: The experimental performance of a modified turbine for driving a supersonic compressor is presented and compared with the performance of the original configuration to illustrate the effect of small changes in the ratio of nozzle-throat area to rotor-throat area. Performance is based on the performance of turbines designed to operate with both blade rows close to choking. On the basis of the results of this investigation, the ratio of areas is concluded to become especially critical in the design of turbines such as those designed to drive high-speed, high-specific weight-flow compressors where the turbine nozzles and rotor are both very close to choking.
Contributing Partner: UNT Libraries Government Documents Department