Resource Type
Serial/Series Title
NACA Research Memorandums
360
NACA Technical Notes
194
Atomic Energy Commission Reports
149
United States Geological Survey Reports
133
Trace elements investigations report
89
Hanford Works Reports
66
Oak Ridge National Laboratory Reports
58
HW (Series)
49
University of California Radiation Laboratory Reports
43
NACA Technical Reports
29
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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
The Absorption Spectra of Suspensions of Living Micro-Organism
The following document describes how to determine the measurements of the optical density or absorption spectra of suspensions of micro-organisms.
Date:
June 1954
Creator:
Shibata, Kazuo, 1918-; Benson, Andrew A. & Calvin, Melvin, 1911-1997
Object Type:
Report
System:
The UNT Digital Library
The Abundance of the Principle Crustacea of the Columbia River and the Radioactivity They Contain
The following document describes data collected from a 14-month period of analyzing crustaceans containing radioactivity. Provided is information based on the change of radioactivity through seasonal changes.
Date:
June 25, 1953
Creator:
Coopey, R. W.
Object Type:
Report
System:
The UNT Digital Library
Acoustical Treatment for the NACA 8- by 6-Foot Supersonic Propulsion Wind Tunnel
"This report presents results of a research and engineering program performed during the first half of 1950 that resulted in an acoustical treatment for the 8- by 6-foot supersonic wind tunnel at the Lewis Flight Propulsion Laboratory" (p. 1).
Date:
June 1955
Creator:
Beranek, Leo L.; Labate, Samuel & Ingard, Uno
Object Type:
Report
System:
The UNT Digital Library
The Action of Oxygen on Activated Charcoal
The following report provides information conducted with the purpose of ascertaining the effect of oxygen on activated charcoal at approximately one atmosphere by measuring the amount of CO2 formed over a known length of time.
Date:
June 29, 1951
Creator:
Bigelow, J. E.; Belaga, M. W. & Mulvihill, R. J.
Object Type:
Report
System:
The UNT Digital Library
Aerodynamic characteristics at high and low subsonic Mach numbers of four NACA 6-series airfoil sections at angles of attack from -2 to 31 degrees
From Introduction: "The airfoil sections tested, which differ only in thickness ratio, were the NACA 64-006, 64-008, 64-010, and 641-012. Lift, drag, and pitching-moment data were obtained for Mach numbers of 0.3 to that for tunnel choke at angles of attack of -2^o to 31^o. The results of this investigation are reported herein."
Date:
June 5, 1953
Creator:
Wilson, Homer B., Jr. & Horton, Elmer A.
Object Type:
Report
System:
The UNT Digital Library
Aerodynamic Characteristics of a 6-Percent-Thick Symmetrical Circular-Arc Airfoil Having a 30-Percent-Chord Trailing-Edge Flap at a Mach Number of 6.9
Memorandum presenting an investigation of the flow characteristics over a 6-percent-thick symmetrical circular-arc airfoil section with a 30-percent-chord trailing-edge flap at a Mach number of 6.90 and a Reynolds number of 1.65 x 10(sub 6). The model was tested over an angle-of-attack range of 0 to 16 degrees and a flap-deflection range of -16 degrees to 16 degrees. Results regarding pressure results and aerodynamic characteristics are provided.
Date:
June 5, 1956
Creator:
Ridyard, Herbert W. & Fetterman, David E., Jr.
Object Type:
Report
System:
The UNT Digital Library
Aerodynamic Characteristics of a 45 Degree Swept Wing Fighter Airplane Model and Aerodynamic Loads on Adjacent Stores and Missiles at Mach Numbers of 1.57, 1.87, 2.16, and 2.53
Report discussing tests to determine the aerodynamic characteristics of a model of a 45 degree swept-wing fighter airplane and to determine the loads on attached stores and detached missiles. An investigation into aileron-spoiler effectiveness, aileron hinge moments, and the effects of wing modifications of aerodynamic characteristics was also carried out at various Mach numbers. Results are presented, but caution is provided in regards to extrapolating results from the model onto a full-scale aircraft.
Date:
June 24, 1958
Creator:
Oehman, Waldo I. & Turner, Kenneth L.
Object Type:
Report
System:
The UNT Digital Library
Aerodynamic Characteristics of a 45 Degree Swept-Wing Fighter-Airplane Model and Aerodynamic Loads on Adjacent Stores and Missiles at Mach Numbers of 1.57, 1.87, 2.16, and 2.53
Memorandum presenting an investigation in the Unitary Plan wind tunnel to determine the aerodynamic characteristics of a model of a 45 degree swept-wing fighter airplane, and to determine the loads on attached stores and detached missiles in the presence of the model. Results also included a determination of aileron-spoiler effectiveness, aileron hinge moments, and the effects of wing modifications on model aerodynamic characteristics. The results are presented with minimum analysis.
Date:
June 24, 1958
Creator:
Oehman, Waldo I. & Turner, Kenneth L.
Object Type:
Report
System:
The UNT Digital Library
Aerodynamic Characteristics of a Refined Deep-Step Planing-Tail Flying-Boat Hull with Various Forebody and Afterbody Shapes
From Introduction: "The results of one phase of this investigation, presented in reference 1, have indicated that hull drag can be reduced without causing large changes in aerodynamic stability and hydrodynamic performance by the use of high length-beam ratios. Another phase of the investigation, reference 2, indicated that hulls of the deep-step planning-tail type have much lower air drag than the conventional type of hull and about the same aerodynamic stability; tank tests, reference 3, have indicated that this type of hull also has hydrodynamic performance equal to and in some respects superior to the conventional type of hull. Unpublished tank tests have indicated that the hull models presented in the present paper (with the possible exception of the forebody alone for which data are not available) will have acceptable hydrodynamic performance."
Date:
June 1952
Creator:
Riebe, John M. & Naeseth, Rodger L.
Object Type:
Report
System:
The UNT Digital Library
Aerodynamic Characteristics of Four Wings of Sweepback Angles 0 Degrees, 35 Degrees, 45 Degrees, and 60 Degrees, NACA 65A006 Airfoil Section, Aspect Ratio 4, and Taper Ratio 0.6 in Combination With a Fuselage at High Subsonic Mach Numbers and at a Mach Number of 1.2
Report discussing an investigation of the effect of sweepback angle on wing-fuselage characteristics at a subsonic and a supersonic Mach number. Lift, drag, and pitching-moment coefficients, downwash-angle, and total-pressure measurements are all provided.
Date:
June 6, 1951
Creator:
Luoma, Arvo A.
Object Type:
Report
System:
The UNT Digital Library
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
"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" (p. 1).
Date:
June 25, 1957
Creator:
Robinson, Ross B.
Object Type:
Report
System:
The UNT Digital Library
Aerodynamic characteristics of several flap-type trailing-edge controls on a trapezoidal wing at Mach numbers of 1.61 and 2.01
Report presenting an investigation at Mach numbers of 1.61 and 2.01 to determine the control effectiveness and hinge-moment characteristics for a series of 25.4-percent-chord trailing-edge controls on a trapezoidal wing with a 23 degree sweptback leading edge, aspect ratio of 3.1, and taper ratio of 0.4. Pressure distribution and hinge-moment measurements were made at a range of angles of attack and control deflections. Results regarding effect of control deflection, effect of wing angle of attack, effect of Reynolds number, effect of trailing-edge thickness, effect of hinge-line gap, effect of Mach number, and effect of control size and location are provided.
Date:
June 14, 1954
Creator:
Lord, Douglas R. & Czarnecki, K. R.
Object Type:
Report
System:
The UNT Digital Library
Aerodynamic characteristics of several jet-spoiler controls on a 45 degree sweptback wing at Mach numbers of 1.61 and 2.01
Report presenting an investigation in the supersonic pressure tunnel at two Mach numbers to determine the aerodynamic characteristics of several jet-spoiler controls on a wing having a 45 degree sweepback of the quarter-chord line, an aspect ratio of 3.5, a taper ratio of 0.3, and an NACA 65A005 airfoil section. Testing indicated that the jet-spoiler effectiveness increased with increasing angle of attack and correlated well with the momentum of jet flow.
Date:
June 24, 1958
Creator:
Lord, Douglas R.
Object Type:
Report
System:
The UNT Digital Library
Aerodynamic Characteristics of Tapered Wings Having Aspect Ratios of 4, 6, and 8, Quarter-Chord Lines Swept Back 45 Degrees, and NACA 63(Sub 1)a012 Airfoil Sections: Transonic-Bump Method
Report presenting testing of a series of three wings over a range of Mach numbers by the use of the transonic-bump technique. The lift, drag, pitching-moment, and root-bending-moment data of wings of a variety of aspect ratios but with the same quarter-chord lines and airfoil sections were obtained.
Date:
June 13, 1951
Creator:
Polhamus, Edward C. & King, Thomas J., Jr.
Object Type:
Report
System:
The UNT Digital Library
The Aerodynamic Design of High Mach Number Nozzles Utilizing Axisymmetric Flow with Application to a Nozzle of Square Test Section
From Introduction: "A method for the design of three-dimensional nozzles based on axi-symmetric flow is presented in this paper. The design method presented in this paper is general; however, as an illustrative example of the design of a Mach number 10 nozzle with square test section is included."
Date:
June 1952
Creator:
Beckwith, Ivan E.; Ridyard, Herbert W. & Cromer, Nancy
Object Type:
Report
System:
The UNT Digital Library
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 To 16 x 10(Exp 6)
Report presenting testing of a modified 1/10-power nose shape in free flight at Mach numbers up to 6.7. Measured heating rates were presented and compared with calculated values. Results regarding transition and comparison with previous investigations are provided.
Date:
June 17, 1957
Creator:
Garland, Benjamine J.; Swanson, Andrew G. & Speegle, Katherine C.
Object Type:
Report
System:
The UNT Digital Library
Aerodynamic investigation of a four-blade propeller operating through an angle-of-attack range from 0 to 180 degrees
Report presenting an investigation of the aerodynamic characteristics of a four-blade rigid model propeller in the full-scale tunnel for a range of angles of attack, blade angles, and advance ratio. It included a preliminary explanation of vertical descent and a comparison with theory. Results regarding the static thrust and forward flight are provided.
Date:
June 1954
Creator:
McLemore, H. Clyde & Cannon, Michael D.
Object Type:
Report
System:
The UNT Digital Library
Aerodynamic loads on a leading-edge flap and a leading-edge slat on the NACA 64A010 airfoil section
From Summary: "The present report presents the chordwise distributions of pressure measured concurrently with the force and moment data of NACA TN 3007."
Date:
June 1954
Creator:
Kelly, John A. & McCullough, George B.
Object Type:
Report
System:
The UNT Digital Library
Aerodynamics of Oscillating Control Surfaces at Transonic Speeds
Memorandum presenting a discussion of oscillating flap-type and all-movable controls with particular emphasis on the aerodynamic forces and moments at transonic speeds. Hinge-moment results from recent wind-tunnel and rocket-powered-model tests are summarized for trailing-edge flap-type controls to illustrate the effects of control hinge-line position and profile shape on one-degree-of-freedom flutter of this type of control.
Date:
June 17, 1957
Creator:
Thompson, Robert F. & Clevenson, Sherman A.
Object Type:
Report
System:
The UNT Digital Library
Age Calculations for Lattices with Aluminum-Matrix Slugs
The process of age calculation for Hanford exponential lattices containing aluminum-matrix slugs, where the sums run over the materials of the lattice cell.
Date:
June 8, 1954
Creator:
Neumann, Herschel
Object Type:
Report
System:
The UNT Digital Library
Aileron and Elevator Hinge Moments of the Bell X-1 Airplane Measured in Transonic Flight
"During the flight investigation of the X-1 airplane the hinge moments of the elevator and aileron control surfaces have been measured over a Mach number range extending to above 1.0. The results of these measurements are presented in this paper" (p. 2).
Date:
June 22, 1953
Creator:
Drake, Hubert M. & McKay, John B.
Object Type:
Report
System:
The UNT Digital Library
Air forces and moments on triangular and related wings with subsonic leading edges oscillating in supersonic potential flow
From Introduction: "This report is concerned with the derivation of expressions for the velocity potential and associated forces and moments for oscillating triangular wings in supersonic flow. The purpose of the present report is to make use of the expanded form of the velocity potential to obtain the forces and moments, based on the first terms of this potential, for a rigid triangular wing performing vertical and pitching sinusoidal oscillations in mixed supersonic flow."
Date:
June 19, 1951
Creator:
Watkins, Charles E. & Berman, Julian H.
Object Type:
Report
System:
The UNT Digital Library
Airborne radioactivity survey of portions of the Defiance Uplift and Carrizo Mountains, Apache County, Arizona
Aerial image shows the result of an airborne radioactive survey over an area of 940 square miles in Apache County, Arizona with the approximate location of radioactivity anomalies found. Text describes methods used and discusses the anomalies.
Date:
June 21, 1953
Creator:
Moxham, Robert Morgan & Johnson, R. W.
Object Type:
Map
System:
The UNT Digital Library