Resource Type
Serial/Series Title
NACA Research Memorandums
353
NACA Technical Notes
222
Atomic Energy Commission Reports
120
Hanford Works Reports
63
HW (Series)
60
United States Geological Survey Reports
60
United States Bureau of Mines Reports
57
NACA Technical Reports
49
Trace elements investigations report
38
NACA Technical Memorandums
32
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Year
Month
Language
991 Matching Results
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991
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4-Channel Line Driver: Modified
Technical drawing of line drivers and amplifiers for use in nuclear reactors.
Date:
1950?
Creator:
Titterton, E. W.
Object Type:
Technical Drawing
System:
The UNT Digital Library
An 8-Foot Axisymmetrical Fixed Nozzle for Subsonic Mach Numbers Up to 0.99 and for a Supersonic Mach Number of 1.2
From Introduction: "This paper, which should be of interest to those concerned with transonic wind tunnels, covers the design and operating characteristics of the nozzle."
Date:
February 23, 1950
Creator:
Ritchie, Virgil S.; Wright, Ray H. & Tulin, Marshall P.
Object Type:
Report
System:
The UNT Digital Library
"25" Critically Consultation with J. W. Morfitt : April 3, 1950
Summary: "Criticality was considered impossible in any contingency encountered in practice under either of the following conditions which include no safety factor: (a) In any isolated cylinder not more than 5 in. in disruptor, if the total amount of U235 present does not exceed 7.5 Eg. (b) In an isolated vessel of any shape and size, if the total amount of U235 present does not exceed 880 g. An "isolated" vessel is one which does not "see" more than 0.1 [...] other vessels containing fissionable material."
Date:
April 3, 1950
Creator:
Merrill, E. T. & Sege, G.
Object Type:
Report
System:
The UNT Digital Library
30 Rv. Power Supply
Technical drawing of electronic circuits and power supplies to nuclear reactors.
Date:
1950?
Creator:
U.S. Atomic Energy Commission
Object Type:
Technical Drawing
System:
The UNT Digital Library
Ability of Pilots to Control Simulated Short-Period Yawing Oscillations
Report discussing an investigation into the ability of human pilots to control short-period yawing oscillations using a yaw simulating device. The ability to control the oscillations was determined to be a function of period, control effectiveness, and inherent damping. Pilot control effectiveness was found to improve with practice.
Date:
November 13, 1950
Creator:
Phillips, William H. & Cheatham, Donald C.
Object Type:
Report
System:
The UNT Digital Library
The Absorption and Translocation of Several Fission Elements by Russian Thistle
Abstract: An investigation was conducted to determine the absorption and translocation of fission products by Russian thistle from a localized spot of contaminated soil. The amount and identity of the radioactive elements absorbed and translocated by the Russian thistle is given along with the location of these elements in the plants. Beta radioactivity to the amounts of 10 microcuries per gram caused no visible effects on the growth habits of sectioned material are included.
Date:
June 8, 1950
Creator:
Selders, A. A.
Object Type:
Report
System:
The UNT Digital Library
Abstracts of the Literature Synthesis of Apatites and Some Related Phosphates: Part 1
Report presenting abstracts and major findings from physiological, biochemical, soil chemical, geological, and mineral studies of the apatite group of minerals.
Date:
December 1950
Creator:
Jaffe, Elizabeth B.
Object Type:
Report
System:
The UNT Digital Library
Advanced Seminar in Reactor Physics
The following report provides equations that result from a seminar in reactor physics.
Date:
July 26, 1950
Creator:
Smith, Nicholas M.
Object Type:
Report
System:
The UNT Digital Library
Aerodynamic and Lateral-Control Characteristics of a 1/28-Scale Model of the Bell X-1 Airplane Wing-Fuselage Combination: Transonic-Bump Method
Report discussing an investigation into the lateral-control characteristics and the pitching-moment characteristics of a scale model of the X-1 wing-fuselage configuration. Information about the estimated variation of rolling effectiveness and wing-fuselage pitching-moment coefficient is described in detail.
Date:
May 5, 1950
Creator:
Lockwood, Vernard E.
Object Type:
Report
System:
The UNT Digital Library
Aerodynamic Characteristics at a Mach Number of 1.25 of a 6-Percent-Thick Triangular Wing and 6- and 9-Percent-Thick Triangular Wings in Combination With a Fuselage: Wing Aspect Ratio 2.31, Biconvex Airfoil Sections
Report discussing testing to determine the aerodynamic characteristics of two semispan delta-wing configurations. Information about the lift characteristics, drag characteristics, pitching-moment characteristics, and comparison with other results is provided.
Date:
May 5, 1950
Creator:
Hall, Albert W. & Morris, Garland J.
Object Type:
Report
System:
The UNT Digital Library
Aerodynamic Characteristics at a Mach Number of 1.38 of Four Wings of Aspect Ratio 4 Having Quarter-Chord Sweep Angles of 0 Degrees, 35 Degrees, 45 Degrees, and 60 Degrees
Report discussing testing to determine the supersonic aerodynamic characteristics of four sweptback wings and wing-body configurations at several angles. Information about basic wing data, modifications to the 60 degree wing, the effects of sweep, and effects of fuselage are included.
Date:
October 10, 1950
Creator:
Kemp, William B., Jr.; Goodson, Kenneth W. & Booth, Robert A.
Object Type:
Report
System:
The UNT Digital Library
Aerodynamic characteristics at Reynolds numbers of 3.0 x 10(exp 6) and 6.0 x 10(exp 6) of three airfoil sections formed by cutting off various amounts from the rear portion of the NACA 0012 airfoil section
Report presenting an investigation of the two-dimensional aerodynamic characteristics of three airfoil sections formed by removing various portions of the original chord from the trailing edge of the NACA 0012 airfoil section. Results regarding lift, drag, and pitching moment and aerodynamic center are provided.
Date:
April 1950
Creator:
Smith, Hamilton A. & Schaefer, Raymond F.
Object Type:
Report
System:
The UNT Digital Library
Aerodynamic characteristics of a wing with quarter-chord line swept back 60 degrees, aspect ratio 2, taper ratio 0.6, and NACA 65A006 airfoil section : transonic bump method
From Introduction: "This paper presents the results of the investigation of the wing-alone and wing-fuselage configurations employing a wing with the quarter-chord line swept back 60^o, aspect ratio 2, taper ratio 0.6, and an NACA 65A006 airfoil section parallel to the free stream."
Date:
February 24, 1950
Creator:
Myers, Boyd C., II & King, Thomas J., Jr.
Object Type:
Report
System:
The UNT Digital Library
Aerodynamic characteristics of a wing with unswept quarter-chord line, aspect ratio 2, taper ratio 0.78, and NACA 65A004 airfoil section: transonic-bump method
From Introduction: "This paper presents the results of an investigation of force and moment characteristics for a wing with an unswept quarter-chord line, aspect ratio 2, taper ratio 0.78, and an NACA 65A004 airfoil section parallel to the free stream."
Date:
March 8, 1950
Creator:
Polhamus, Edward C. & Campbell, George S.
Object Type:
Report
System:
The UNT Digital Library
Aerodynamic characteristics of a wing with unswept quarter-chord line, aspect ratio 4, taper ratio 0.6, and NACA 65A004 airfoil section: Transonic-bump method
From Introduction: "This paper presents the results of the investigation of the wing alone and of the wing-fuselage configurations employing a wing with an unswept quarter-chord line, aspect ratio 4, taper ratio 0.6, and an NACA 65A004 airfoil section parallel to the air stream. The experimental results of a wing of identical plan from having an NACA 65A006 airfoil section which was tested as part of the transonic program are presented in reference 1.
Date:
May 8, 1950
Creator:
Myers, Boyd C., II & Wiggins, James W.
Object Type:
Report
System:
The UNT Digital Library
Aerodynamic Characteristics of Damping Screens
From Summary: "The experimental investigation of damping screens described herein was undertaken primarily to test theories of the effects of damping screens and to obtain information on the performance of screens in oblique flow. The characteristics investigated include the damping of longitudinal and lateral components of turbulence, the effect of screens on scale, the conditions for the production of turbulence and eddies by screens, and the damping of spatial variations of mean speed."
Date:
January 1950
Creator:
Schubauer, G. B.; Spangenberg, W. G. & Klebanoff, P. S.
Object Type:
Report
System:
The UNT Digital Library
Aerodynamic characteristics of NACA RM-10 missile in 8- by 6-foot supersonic wind tunnel at Mach numbers from 1.49 to 1.98 1: presentation and analysis of pressure measurements (stabilizing fins removed)
Experimental investigation of flow about a slender body of revolution (NACA RM-10 missile) aligned and inclined to a supersonic stream was conducted at Mach numbers from 1.49 to 1.98 at a Reynolds number of approximately 30,000,000. Boundary-layer measurements at zero angle of attack are correlated with subsonic formulations for predicting boundary-layer thickness and profile. Comparison of pressure coefficients predicted by theory with experimental values showed close agreement at zero angle of attack and angle of attack except over the aft leeward side of body. At angle of attack, pitot pressure measurements in plane of model base indicated a pair of symmetrically disposed vortices on leeward side of body.
Date:
July 20, 1950
Creator:
Luidens, Roger W. & Simon, Paul C.
Object Type:
Report
System:
The UNT Digital Library
Aerodynamic characteristics of NACA RM-10 missile in 8- by 6-foot supersonic wind tunnel at Mach numbers from 1.49 to 1.98 2: presentation and analysis of force measurements
Experimental investigation of aerodynamic forces acting on body of revolution (NACA RM-10 missile) with and without stabilizing fins was conducted at Mach numbers from 1.49 to 1.98 at angles of attack from 0 to 9 degrees and at Reynolds number of approximately 30,000,000. Comparison of experimental lift, drag, and pitching-moment coefficients and center of pressure location for body alone is made with linearized potential theory and a semiempirical method. Results indicate that aerodynamic characteristics were predicted more accurately by semiempirical method than by potential theory. Breakdown of measured drag coefficients into components of friction, pressure, and base-pressure drag is presented for body alone at zero angle of attack.
Date:
July 21, 1950
Creator:
Esenwein, Fred T.; Obery, Leonard J. & Schueller, Carl F.
Object Type:
Report
System:
The UNT Digital Library
Aerodynamic characteristics of NACA RM 10 missile in 8 by 6 foot supersonic wind tunnel at Mach numbers from 1.49 to 1.98. 3: analysis of force distribution at angle of attack (stabilizing fins removed)
Report presenting an analysis of the force distribution on a slender pointed body of revolution at angle of attack utilizing pressure-distribution data and balance measurements. The data were obtained in the supersonic tunnel at a variety of Mach numbers and angles of attack. Results regarding normal forces and axial force are provided.
Date:
December 12, 1950
Creator:
Luidens, Roger W. & Simon, Paul C.
Object Type:
Report
System:
The UNT Digital Library
Aerodynamic characteristics with fixed and free transition of a modified delta wing in combination with fuselage at high subsonic speeds
From Introduction: "An investigation of the high-speed aerodynamic characteristics of a modified delta wing in combination with a fuselage was conducted in the Langley high-speed 7- by 10-foot tunnel. The model was tested on the sting support system through a Mach number range of 0.40 to 0.90 with both free and fixed transition. Because of the nature of the transition effect, the results seemed to be of the general interest and are presented in the present paper."
Date:
May 2, 1950
Creator:
Polhamus, Edward C. & King, Thomas J., Jr.
Object Type:
Report
System:
The UNT Digital Library
Aerodynamic coefficients for an oscillating airfoil with hinged flap, with tables for a Mach number of 0.7
From Introduction: "The fundamental integral equation for the pressure distribution on an oscillating thin airfoil moving at subsonic speed has been derived by Possio in reference 1. Collocation procedures have been used by Possio, Frazer, and Skan, and others to obtain lift and moment on an oscillating first plate. An important contribution has been made by Dietze (see reference 2 and 3), who has developed an iterative procedure for numerical solution of Possio's integral equation."
Date:
October 1950
Creator:
Turner, M. J. & Rabinowitz, S.
Object Type:
Report
System:
The UNT Digital Library
The aerodynamic forces and moments on a 1/10-scale model of a fighter airplane in spinning attitudes as measured on a rotary balance in the Langley 20-foot free-spinning tunnel
From Introduction: "This investigation provides general information on the magnitudes and directions of the aerodynamic forces and moments acting on a fighter airplane in fully developed spins. The investigation includes the determination of the effects on the aerodynamic forces and moments of varied rudder setting with and against the spin, of tail modifications, and of deflected flaps and lowered landing gear."
Date:
September 1950
Creator:
Stone, Ralph W., Jr.; Burk, Sanger M., Jr. & Bihrle, William, Jr.
Object Type:
Report
System:
The UNT Digital Library
The Aerodynamic Forces on Slender Plane- and Cruciform-Wing and Body Combinations
From Introduction: "Since these results were not applicable to the present problem, a theoretical analysis of the aerodynamic properties of slender wing-body combinations was undertaken. The results of this investigation were first reported in reference 5 and were later extended in reference 6 to include cruciform-wing and body combinations. The present report summarizes and extends the theory and results previously presented in these references."
Date:
1950%
Creator:
Spreiter, John R.
Object Type:
Report
System:
The UNT Digital Library
Aerodynamic Investigation of a Parabolic Body of Revolution at Mach Number of 1.92 and Some Effects of an Annular Jet Exhausting From the Base
Report discussing an investigation of a parabolic body of revolution with and without the effects of an annular jet exhausting from the base. The aerodynamic characteristics, pressures, lift-curve slope, and other characteristics with the jet in operation and inoperative were compared.
Date:
February 8, 1950
Creator:
Love, Eugene S.
Object Type:
Report
System:
The UNT Digital Library