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  Partner: UNT Libraries Government Documents Department
 Collection: Technical Report Archive and Image Library
Free-Spinning-Tunnel Tests of a 1/29-Scale Model of the Republic XP-91 Airplane with a Vee Tail Installed

Free-Spinning-Tunnel Tests of a 1/29-Scale Model of the Republic XP-91 Airplane with a Vee Tail Installed

Date: January 16, 1948
Creator: Snyder, Thomas L.
Description: A spin investigation has been conducted in the Langley 20 -foot free-spinning tunnel on a 1/29 - scale model of the Republic XP-91 airplane with vee tail installed. The effects cf control settings and movements upon the effect spin and recovery characteristics of the model were determined for the clean condition (wing tanks removed, landing gear and flaps retracted). The tests were made at a loading simulating that following cruise at altitude and at a time when nearly all fuel was expended. The results indicated that the airplane might not spin at normal spinning-control configuration, but if a spin were obtained, recovery therefrom by full rudder reversal would be satisfactory. It was also indicated that aileron-against settings would lead to violent oscillatory motions and should be avoided.
Contributing Partner: UNT Libraries Government Documents Department
Free-Spinning-Tunnel Tests of a 1/35-Scale Model of the Douglas XB-43 Airplane

Free-Spinning-Tunnel Tests of a 1/35-Scale Model of the Douglas XB-43 Airplane

Date: July 18, 1947
Creator: Snyder, Thomas L.
Description: Spin tests have been performed in the Langley 20-foot free-spinning tunnel on a 1/35-scale model of the Douglas XB-43 airplane. The spin and recovery characteristics were determined for several loading conditions of the airplane. The effects of installing a dorsal fin and of installing a ventral fin were investigated. Emergency escape of the crew was simulated and the stick and rudder pedal forces necessary to effect recoveries on the airplane were determined.
Contributing Partner: UNT Libraries Government Documents Department
Fission-Product Releases to the Primary System of EBR-II from April 1977 to May 1978

Fission-Product Releases to the Primary System of EBR-II from April 1977 to May 1978

Date: July 1979
Creator: So, B. Y. C.; Gross, K. C.; Lambert, J. D. B.; Kim, F. S.; Ebersole, E. R. & Lang, M. T.
Description: Suspected fission-product releases from 18 subassemblies between April 1977 and May 1978 are presented. Post-irradiation examinations pm 15 of the suspect subassemblies confirmed that all contained one or more breached elements. Except for two untagged subassemblies, xenon tagging was the primary method of identification, although other methods were used where appropriate. Methods to monitor and identify fission product sources are discussed. Problems encountered elements on plant availability were minimal during this reporting period. From all evidence, cladding breaching on elements in EBR-II continues to be a benign process.
Contributing Partner: UNT Libraries Government Documents Department
Fission-Product Releases to the Primary System of EBR-II, January 1974-March 1975

Fission-Product Releases to the Primary System of EBR-II, January 1974-March 1975

Date: October 1976
Creator: So, B. Y. C.; Lambert, J. D. B.; Johnson, D. L.; Ebersole, E. R. & Brunson, G. S.
Description: Seven releases of fission products occurred in EBR-II from January 1974 to March 1975 - - five from mixed-oxide elements and two from sodium-bonded driver-fuel elements. Four releases were from elements that contained a xenon tag, which aided considerably in locating three of the elements; data from the fourth element allowed estimation of changes of tag composition with reactor exposure. Rapid release of fission from two breached mixed-oxide elements caused the reactor to trip because of increased delayed-neutron activity, the first time such behavior has been observed. Identification of a subassembly of Mark-1A driver-fuel elements was complicated by multiple failure of its untagged elements during the diagnosis period. Several of these elements had some exposed fuel in the core, which was the likely cause of increasing delayed-neutron signals from the subassembly.
Contributing Partner: UNT Libraries Government Documents Department
Fission-Product Releases to the Primary System of EBR-II from April 1975 to March 1977

Fission-Product Releases to the Primary System of EBR-II from April 1975 to March 1977

Date: May 1979
Creator: So, B. Y. C.; Lambert, J. D. B.; Kim, F. S.; Armstrong, J. P.; Ebersole, E. R. & Lang, M. T.
Description: This report describes the 14 releases of fission products that occurred in EBR-II from April 1975 to March 1977. Each release was readily detected, and all but one (in a driver-fuel subassembly) was identified with a particular subassembly. Xenon tagging was the primary method of identification, although other methods were used where appropriate. Methods of monitoring and identifying fission-product sources are discussed, and each release and identification is described. Effects of breached elements on plant availability were minimal in this period. From all evidence, cladding breaching on elements in EBR-II continues to be a benign process.
Contributing Partner: UNT Libraries Government Documents Department
Steady-state engine windmilling and engine speed decay characteristics of an axial-flow turbojet engine

Steady-state engine windmilling and engine speed decay characteristics of an axial-flow turbojet engine

Date: December 5, 1951
Creator: Sobolewski, A E & Farley, J M
Description: A wind tunnel investigation has been conducted to determine the steady-state windmilling and engine speed decay characteristics of the J34-WE-32 turbo-jet over a range of altitudes from 5000 to 50,000 feet and simulated flight Mach numbers from 0.19 to 1.06. The effect of an engine accessory load on the speed decay characteristics was also determined. The accessory load was about 7.8 horsepower for engine speeds above 4000 rpm and decreased with decreasing engine speed. An analysis of the speed decay data was made and engine speed decay rates were determined for hypothetical accessory loads up to 40 horsepower.
Contributing Partner: UNT Libraries Government Documents Department
Altitude operational characteristics of prototype J40-WE-8 turbojet engine

Altitude operational characteristics of prototype J40-WE-8 turbojet engine

Date: August 14, 1953
Creator: Sobolewski, Adam E & Lubick, Robert J
Description: The altitude operational characteristics of the prototype J40-WE-8 turbojet engine were determined in the NACA Lewis altitude wind tunnel. The operational characteristics that were obtained include (1) compressor surge characteristics, (2) acceleration and deceleration rates, (3) steady-state windmilling-engine characteristics, (4) altitude ignition characteristics, and (5) the effect of two grades of fuel on steady-state engine performance at an altitude of 45,000 feet and a flight Mach number of 0.20. The altitude ignition characteristics determined include the effects of (1) ignition fuel flow, (2) two ignition procedures, (3) fuel temperatures, and (4) two grades of fuel on ignition characteristics. The compressor surge line, when presented as a function of compressor pressure ratio and corrected engine speed, was not affected by changes in flight condition and was independent of engine-inlet installation and of the manner in which surge was approached, rapidly or slowly. Also there was no effect of altitude or engine-inlet installation on the compressor surge recovery line when presented as a function of compressor pressure ratio and corrected engine speed.
Contributing Partner: UNT Libraries Government Documents Department
Altitude performance investigation of two single-annular type combustors and the prototype J40-WE-8 turbojet engine combustor with various combustor-inlet air pressure profiles

Altitude performance investigation of two single-annular type combustors and the prototype J40-WE-8 turbojet engine combustor with various combustor-inlet air pressure profiles

Date: May 29, 1953
Creator: Sobolewski, Adam E; Miller, Robert R & Mcaulay, John E
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Directional Stability of Towed Airplanes

Directional Stability of Towed Airplanes

Date: January 1, 1956
Creator: Soehne, W.
Description: So far, very careful investigations have been made regarding the flight properties, in particular the static and dynamic stability, of engine-propelled aircraft and of untowed gliders. In contrast, almost no investigations exist regarding the stability of airplanes towed by a towline. Thus, the following report will aim at investigating the directional stability of the towed airplane and, particularly, at determining what parameters of the flight attitude and what configuration properties affect the stability. The most important parameters of the flight attitude are the dynamic pressure, the aerodynamic coefficients of the flight attitude, and the climbing angle. Among the configuration properties, the following exert the greatest influence on the stability: the tow-cable length, the tow-cable attachment point, the ratio of the wing loadings of the towing and the towed airplanes, the moments of inertia, and the wing dihedral of the towed airplane. In addition, the size and shape of the towed airplane vertical tail, the vertical tail length, and the fuselage configuration are decisive factors in determining the yawing moment and side force due to sideslip, respectively.
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
Conceptual Design and Economic Evaluation of a Steam-Cooled Fast Breeder Reactor

Conceptual Design and Economic Evaluation of a Steam-Cooled Fast Breeder Reactor

Date: November 15, 1961
Creator: Sofer, G.; Hankel, R.; Goldstein, L. & Birman, G.
Description: From abstract: This report describes a conceptual design and economic evaluation of 300 and 40 MWe steam-cooled fast breeder reactor power plants performed by NDA under contract with the AEC.
Contributing Partner: UNT Libraries Government Documents Department
Three papers from conference on "Wing and tail-surface oscillations : March 6-8, 1941, Munich

Three papers from conference on "Wing and tail-surface oscillations : March 6-8, 1941, Munich

Date: August 1, 1951
Creator: Sohngen, Heinz; Schwarz, L & Dietze, F
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Knocking in an internal-combustion engine

Knocking in an internal-combustion engine

Date: January 1, 1940
Creator: Sokolik, A & Voinov, A
Description: The question remains open of the relation between the phenomena of knocking in the engine and the explosion wave. The solution of this problem is the object of this paper. The tests were conducted on an aircraft engine with a pyrex glass window in the cylinder head. Photographs were then taken of various combinations of fuels and conditions.
Contributing Partner: UNT Libraries Government Documents Department
Self-Ignition and Combustion of Gases

Self-Ignition and Combustion of Gases

Date: August 1, 1942
Creator: Sokolik, A. S.
Description: This paper attempts to state laws for the self-ignition and combustion of gases in a comprehensive manner.
Contributing Partner: UNT Libraries Government Documents Department
Hydrodynamic Properties of Planing Surfaces and Flying Boats

Hydrodynamic Properties of Planing Surfaces and Flying Boats

Date: October 1, 1950
Creator: Sokolov, N. A.
Description: The study of the hydrodynamic properties of planing bottom of flying boats and seaplane floats is at the present time based exclusively on the curves of towing tests conducted in tanks. In order to provide a rational basis for the test procedure in tanks and practical design data, a theoretical study must be made of the flow at the step and relations derived that show not only qualitatively but quantitatively the inter-relations of the various factors involved. The general solution of the problem of the development of hydrodynamic forces during the motion of the seaplane float or flying boat is very difficult for it is necessary to give a three-dimensional solution, which does not always permit reducing the analysis to the form of workable computation formulas. On the other had, the problem is complicated by the fact that the object of the analysis is concerned with two fluid mediums, namely, air and water, which have a surface of density discontinuity between them. The theoretical and experimental investigations on the hydrodynamics of a ship cannot be completely carried over to the design of floats and flying-boat hulls, because of the difference in the shape of the contour lines of the bodies, ...
Contributing Partner: UNT Libraries Government Documents Department
Critical velocities of ultracentrifuges

Critical velocities of ultracentrifuges

Date: March 1, 1951
Creator: Sokolov, V I
Description: The Euler equations for the rotation of a solid body are applied to the problem of the motion of ultracentrifuges. Particular attention is paid to the problem of the passage of an ultracentrifuge rotor through the critical velocity. The factors that affect the passage of rotors through the critical point are stressed.
Contributing Partner: UNT Libraries Government Documents Department
Transonic flow past cone cylinders

Transonic flow past cone cylinders

Date: January 1, 1955
Creator: Solomon, George E
Description: Experimental results are presented for transonic flow post cone-cylinder, axially symmetric bodies. The drag coefficient and surface Mach number are studied as the free-stream Mach number is varied and, wherever possible, the experimental results are compared with theoretical predictions. Interferometric results for several typical flow configurations are shown and an example of shock-free supersonic-to-subsonic compression is experimentally demonstrated. The theoretical problem of transonic flow past finite cones is discussed briefly and an approximate solution of the axially symmetric transonic equations, valid for a semi-infinite cone, is presented.
Contributing Partner: UNT Libraries Government Documents Department
Transonic flow past cone cylinders

Transonic flow past cone cylinders

Date: September 1, 1954
Creator: Solomon, George E
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The subsonic aerodynamic characteristics of two double-wedge airfoil sections suitable for supersonic flight

The subsonic aerodynamic characteristics of two double-wedge airfoil sections suitable for supersonic flight

Date: May 12, 1947
Creator: Solomon, Joseph & Henney, Floyd W
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Speed-brake investigation at low speed of a 1/10-scale model of the mx-1554a airplane with a circular jet nozzle

Speed-brake investigation at low speed of a 1/10-scale model of the mx-1554a airplane with a circular jet nozzle

Date: January 1, 1953
Creator: Solomon, M.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Speed-brake investigation at low speed of a 1/10-scale model of the MX-1554A airplane with a circular jet nozzle

Speed-brake investigation at low speed of a 1/10-scale model of the MX-1554A airplane with a circular jet nozzle

Date: January 7, 1954
Creator: Solomon, Martin
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics at high speeds of a two-blade NACA 10-(3)(062)-045 propeller and of a two-blade NACA 10-(3)(08)-045 propeller

Aerodynamic characteristics at high speeds of a two-blade NACA 10-(3)(062)-045 propeller and of a two-blade NACA 10-(3)(08)-045 propeller

Date: October 1, 1948
Creator: Solomon, William
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics of a two-blade NACA 10-(3)(062)-045 propeller and of a two-blade NACA 10-(3)(08)-045 propeller

Aerodynamic characteristics of a two-blade NACA 10-(3)(062)-045 propeller and of a two-blade NACA 10-(3)(08)-045 propeller

Date: January 1, 1953
Creator: Solomon, William
Description: Characteristics are given for the two-blade NACA 10-(3)(062)-045 propeller and for the two-blade NACA 10-(3)(08)-045 propeller over a range of advance ratio from 0.5 to 3.8, through a blade-angle range from 20 degrees to 55 degrees measured at the 0.75 radius. Maximum efficiencies of the order of 91.5 to 92 percent were obtained for the propellers. The propeller with the thinner airfoil sections over the outboard portion of the blades, the NACA 10-(3)(062)-045 propeller, had lower losses at high tip speeds, the difference amounting to about 5 percent at a helical tip Mach number of 1.10.
Contributing Partner: UNT Libraries Government Documents Department
Investigation of Spoiler Ailerons with and Without a Gap Behind the Spoiler on a 45 Degree Sweptback Wing-Fuselage Combination at Mach Numbers from 0.60 to 1.03

Investigation of Spoiler Ailerons with and Without a Gap Behind the Spoiler on a 45 Degree Sweptback Wing-Fuselage Combination at Mach Numbers from 0.60 to 1.03

Date: September 14, 1953
Creator: Solomon, William; West, F E , Jr & Brummal, Edward M
Description: None
Contributing Partner: UNT Libraries Government Documents Department