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  Partner: UNT Libraries Government Documents Department
 Decade: 1950-1959
 Year: 1957
 Collection: Technical Report Archive and Image Library
11,400 KW Nuclear Power Plant Employing an Organic Moderated Reactor: Preliminary Description

11,400 KW Nuclear Power Plant Employing an Organic Moderated Reactor: Preliminary Description

Date: 1957
Creator: Wheelock, C. W.
Description: Abstract: The preliminary design is described for a small electric-power-generating plant powered by an organic moderated reactor. System and component requirements are discussed and possible design configurations and equipment are described.
Contributing Partner: UNT Libraries Government Documents Department
15 MW Gas-Cooled Closed-Cycle Reactor Power System Study: Final Report, Volumes 1-2

15 MW Gas-Cooled Closed-Cycle Reactor Power System Study: Final Report, Volumes 1-2

Date: April 1, 1957
Creator: unknown
Description: This report covers a feasibility study for a 15 megawatt gas cooled reactor power system, conducted by the Ford Instrument Company Division of the Sperry Rand Corporation during the months of March to August 1956.
Contributing Partner: UNT Libraries Government Documents Department
20,000 KW Nuclear Power Plant Study for United States Atomic Energy Commission

20,000 KW Nuclear Power Plant Study for United States Atomic Energy Commission

Date: July 7, 1957
Creator: Gilbert Associates, Inc.
Description: Introduction: In September of 156, Gilbert Associates, Inc., entered into a contract with the United States of America, acting through the United States Atomic Energy Commission, for the study and preliminary design of a nuclear power plant being considered for integration into a central station power system at an overseas site.
Contributing Partner: UNT Libraries Government Documents Department
Abnormal grain growth in M-252 and S-816 alloys

Abnormal grain growth in M-252 and S-816 alloys

Date: November 1957
Creator: Decker, R F; Rush, A I; Dano, A G & Freeman, J W
Description: An experimental investigation was carried out on air- and vacuum-melted M-252 and S-816 alloys to find conditions of heating and hot-working which resulted in abnormal grain growth. The experiments were mainly limited to normal conditions of heating for hot-working and heat treatment and normal temperatures of solution treatment were used to allow grain growth after susceptibility to abnormal grain growth was developed by various experimental conditions. Results indicated that small reductions of essentially strain-free metal were the basic cause of such grain growth.
Contributing Partner: UNT Libraries Government Documents Department
Abnormal grain growth in nickel-base heat-resistant alloys

Abnormal grain growth in nickel-base heat-resistant alloys

Date: December 1957
Creator: Decker, R F; Rush, A I; Dano, A G & Freeman, A G
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Accelerations in fighter-airplane crashes

Accelerations in fighter-airplane crashes

Date: November 4, 1957
Creator: Acker, Loren W; Black, Duglad O & Moser, Jacob C
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Accidents from explosives at metal and nonmetallic mines

Accidents from explosives at metal and nonmetallic mines

Date: 1957
Creator: Cash, Frank E.
Description: Circular produced by the U.S. Bureau of Mines to promote safety through a series of reports on accident prevention in mines. According the the scope statement, "This is the fourth section of the revised series of circulars that cover various phases of accident prevention in metal and nonmetallic mines; it give information on accidents and injuries from storing, handling, and using explosive in metal and nonmetallic mines and discusses the precautions by which they can be prevented" (p. 2).
Contributing Partner: UNT Libraries Government Documents Department
Additional experiments with flat-top wing- body combinations at high supersonic speeds

Additional experiments with flat-top wing- body combinations at high supersonic speeds

Date: February 19, 1957
Creator: Gloria, H. R.; Syvertson, C. A. & Wong, T. J.
Description: Flat top wing body configuration effects on aerodynamic characteristics of supersonic aircraft.
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic and hydrodynamic characteristics of a proposed supersonic multijet water-based hydro-ski aircraft with a variable-incidence wing

Aerodynamic and hydrodynamic characteristics of a proposed supersonic multijet water-based hydro-ski aircraft with a variable-incidence wing

Date: October 23, 1957
Creator: Petynia, William W; Hasson, Dennis F & Spooner, Stanley H
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics at high speeds of related full-scale propellers having different blade-section cambers

Aerodynamic characteristics at high speeds of related full-scale propellers having different blade-section cambers

Date: January 1, 1957
Creator: Maynard, Julian D & Salters, Leland B , Jr
Description: Wind-tunnel tests of a full-scale two-blade NACA 10-(10)(08)-03 (high camber) propeller have been made for a range of blade angles from 20 degrees to 55 degrees at airspeeds up to 500 miles per hour. The results of these tests have been compared with results from previous tests of the NACA 10-(3) (08)-03 (low camber) and NACA 10-(5)(08)-03 (medium camber) propellers to evaluate the effects of blade-section camber on propeller aerodynamic characteristics.
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics at Mach number of 4.06 of a typical supersonic airplane model using body and vertical-tail wedges to improve directional stability

Aerodynamic characteristics at Mach number of 4.06 of a typical supersonic airplane model using body and vertical-tail wedges to improve directional stability

Date: December 3, 1957
Creator: Dunning, Robert W
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic Characteristics of a 0.04956-Scale Model of the Convair TF-102A Airplane at Transonic Speeds, Coord. No. AF-120

Aerodynamic Characteristics of a 0.04956-Scale Model of the Convair TF-102A Airplane at Transonic Speeds, Coord. No. AF-120

Date: January 1, 1957
Creator: Osborne, Robert S.
Description: The basic aerodynamic characteristics of a 0.04956-scale model of the Convair TF-102A airplane with controls undeflected have been determined at Mach numbers from 0.60 to 1.135 for angles of attack up to approximately 22 deg in the Langley 8-foot transonic tunnel. In addition, comparisons have been made with data obtained from a previous investigation of a 0.04956-scale model of the Convair F-102A airplane. The results indicated the TF-102A airplane was longitudinally stable for all conditions tested. An increase in lift-curve slope from 0.045 to 0.059 and an 11-percent rearward shift in aerodynamic-center location occurred with increases in Mach number from 0.60 to approximately 1.05. The zero-lift drag coefficient for the TF-102A airplane increased 145 percent between the Mach numbers of 0.85 and 1.075; the maximum lift-drag ratio decreased from 9.5 at a Mach number of 0.60 to 5.0 at Mach numbers above 1.025. There was little difference in the lift and pitching-moment characteristics and drag due to life between the TF-102A and F-102A configurations. However, as compared with the F-102A airplane, the zero-lift drag-rise Mach number for the TF-102A was reduced by at least 0.06, the zero-lift peak wave drag was increased 50 percent, and the maximum lift-drag ratio was ...
Contributing Partner: UNT Libraries Government Documents Department
The aerodynamic characteristics of a body in the two-dimensional flow field of a circular-arc wing at a Mach number of 2.01

The aerodynamic characteristics of a body in the two-dimensional flow field of a circular-arc wing at a Mach number of 2.01

Date: July 2, 1957
Creator: Gapcynski, John P & Carlson, Harry W
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics of a circular cylinder at Mach number 6.86 and angles of attack up to 90 degrees

Aerodynamic characteristics of a circular cylinder at Mach number 6.86 and angles of attack up to 90 degrees

Date: January 1, 1957
Creator: Penland, Jim A
Description: Pressure-distribution and force tests of a circular cylinder have been made in the Langley 11-inch hypersonic tunnel at a Mach number of 6.88, a Reynolds number of 129,000, and angles of attack up to 90 degrees. The results are compared with the hypersonic approximation of Grimminger, Williams, and Young and a simple modification of the Newtonian flow theory. An evaluation of the crossflow theory is made through comparison of present results with available crossflow Mach number drag coefficients.
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics of a model of an escape capsule for a supersonic bomber-type airplane at a Mach number of 2.49

Aerodynamic characteristics of a model of an escape capsule for a supersonic bomber-type airplane at a Mach number of 2.49

Date: December 3, 1957
Creator: Presnell, John G , Jr
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics of missile configurations with wings of low aspect ratio for various combinations of forebodies, afterbodies, and nose shapes for combined angles of attack and sideslip at a Mach number of 2.01

Aerodynamic characteristics of missile configurations with wings of low aspect ratio for various combinations of forebodies, afterbodies, and nose shapes for combined angles of attack and sideslip at a Mach number of 2.01

Date: June 25, 1957
Creator: Robinson, Ross B
Description: An investigation has been made in the Langley 4-by-4-foot supersonic pressure tunnel to determine the aerodynamic characteristics of a series of missile configurations having low-aspect-ratio wings at a Mach number of 2.01. The effects of wing plan form and size, length-diameter ratio, forebody and afterbody length, boattailed and flared afterbodies, and component force and moment data are presented for combined angles of attack and sideslip to about 28 degrees. No analysis of the data was made in this report.
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic Forces and Moments on a Large Ogive-Cylinder Store at Various Locations Below the Fuselage Center Line of a Swept-Wing Bomber Configuration at a Mach Number of 1.61

Aerodynamic Forces and Moments on a Large Ogive-Cylinder Store at Various Locations Below the Fuselage Center Line of a Swept-Wing Bomber Configuration at a Mach Number of 1.61

Date: January 14, 1957
Creator: Morris, O. A.
Description: A supersonic wind-tunnel investigation on store interference has been conducted in the Langley 4- by 4-foot supersonic pressure tunnel at a Mach number of 1.61. Forces and moments were measured on a large ogive-cylinder store in the presence of a 45 deg swept-wing-fuselage bomber configuration for a number of store locations below the fuselage center line. Results of the investigation show that large variations of store lift, drag, and pitch occur with changes in store or airplane angle of attack, store vertical location, and store horizontal location. The variation of the store forces and moments with respect to the chordwise location of the wing plan form indicates that the wing is a large factor in producing the interference loads on the store. Comparison of data for underfuselage and underwing store locations at an angle of attack of 0 deg showed maximum store drag interferences of similar magnitudes, but showed considerably smaller maximum interference on store lift an pitching moments for underfuselage store locations.
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic Forces on a Vibrating Unstaggered Cascade

Aerodynamic Forces on a Vibrating Unstaggered Cascade

Date: August 1, 1957
Creator: Soehngen, H.
Description: The unsteady aerodynamic forces, [based on two-dimensional incompressible flow considerations], are determined for an unstaggered cascade, the blades of which are vibrating in phase in an approach flow parallel to the blades.
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic Heating and Boundary-layer Transition on a 1/10-power nose shape in free flight at Mach numbers up to 6.7 and Free-stream Reynolds numbers up tp 16 x 10(exp 6)

Aerodynamic Heating and Boundary-layer Transition on a 1/10-power nose shape in free flight at Mach numbers up to 6.7 and Free-stream Reynolds numbers up tp 16 x 10(exp 6)

Date: June 17, 1957
Creator: Garland, Benjamine J; Swanson, Andrew G & Speegle, Katherine C
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic heating of a thin, unswept, untapered, multiweb, aluminum-alloy wing at Mach numbers up to 2.67 as determined from a free-flight investigation of a rocket-propelled model

Aerodynamic heating of a thin, unswept, untapered, multiweb, aluminum-alloy wing at Mach numbers up to 2.67 as determined from a free-flight investigation of a rocket-propelled model

Date: August 6, 1957
Creator: Strass, H Kurt & Stephens, Emily W
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic interference of slender wing-tail combinations

Aerodynamic interference of slender wing-tail combinations

Date: January 1, 1957
Creator: Sacks, Alvin H
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic load distribution over a 45 degree swept wing having a spoiler-slot-deflector aileron and other spoiler ailerons for Mach numbers from 0.60 to 1.03

Aerodynamic load distribution over a 45 degree swept wing having a spoiler-slot-deflector aileron and other spoiler ailerons for Mach numbers from 0.60 to 1.03

Date: December 5, 1957
Creator: West, F E , Jr; Whitcomb, Charles F & Schmeer, James W
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic Loads on Tails at High Angles of Attack and Sideslip

Aerodynamic Loads on Tails at High Angles of Attack and Sideslip

Date: July 23, 1957
Creator: Polhamus, E. C. & Spahr, J. R.
Description: Results are presented for the loads and moments acting on the individual tail surfaces of a body-tail combination over a wide range of angles of attack and sideslip. The effects of forebody length and panel-panel interference on the characteristics are included. It is shown that large nonlinear variations in these loads and moments, which occur at some combinations of angle of attack and sideslip, cannot be predicted by low-angle theory. A relatively simple, but general, theoretical method for calculating these load and moment characteristics is described, and the results from this method are found to be in good agreement with experiment provided the initial positions of the forebody vortices are known. It is shown that a simple application of slender-body theory can be used to predict the side loads due to sideslip that are contributed by a vertical tail on a wide variety of wing-body-tail combinations at low angles of attack. For several configurations, changes are indicated which reduced the vertical-tail loads per unit yawing moment of each complete configuration at large angles of attack. Some results are presented on the effect of high angle of attack on the induced-flow field and tail loads due to a wing at supersonic ...
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic performance of several techniques for spike-position control of  a blunt-lip nose inlet having internal contraction; Mach numbers of 0.63 and 1.5 to 2.0

Aerodynamic performance of several techniques for spike-position control of a blunt-lip nose inlet having internal contraction; Mach numbers of 0.63 and 1.5 to 2.0

Date: September 17, 1957
Creator: Anderson, Arthur A & Weinstein, Maynard I
Description: None
Contributing Partner: UNT Libraries Government Documents Department
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