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Strain-Gage Measurements of Buffeting Loads on a Jet-Powered Bomber Airplane

Description: Buffet boundaries, buffeting-load increments for the stabilizers and elevators, and buffeting bending-moment increments for the stabilizers and wings as measured in gradual maneuvers for a jet-powered bomber airplane are presented. The buffeting-load increments were determined from strain-gage measurements at the roots or hinge supports of the various surfaces considered. The Mach numbers of the tests ranged from 0.19 to 0.78 at altitudes close to 30,000 feet. The predominant buffet frequencies… more
Date: March 19, 1951
Creator: Aiken, William S., Jr. & See, John A.
Item Type: Refine your search to only Report
open access

An Investigation of ThF4 - Fused Salt Solutions for Homogeneous Breeder Reactors

Description: Technical report presenting a consideration of the characteristics of fused salt-ThF4 solutions suitable for use in homogeneous reactors. Presented in tandem with a brief survey of the literature pertaining to such solutions and a summary of the experimental work accomplished. [From Abstract]
Date: June 19, 1951
Creator: Blomeke, J. O. & Johnston, C. P.
Item Type: Refine your search to only Report
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Geology and Ore Deposits of Yazzie Mesa, Apache County, Arizona with Recommendations for Exploration Drilling

Description: Abstract: Yazzie Mesa was examined in May 1951, by the writer, assisted by R. C. Cutter. The mesa shows one main channel deposit and three minor channels. The main channel appears to be a northern extension of a channel deposit being worked by the Vanadium Corporation of America at their Monument No. 2 mine. Two samples taken on the south outcrop of the main channel assayed 0.16% U308 over 4.5 feet and 0.80% U308 over 1 foot. The area is recommended for 10,000 feet of exploration drilling. It i… more
Date: June 19, 1951
Creator: Chester, John W.
Item Type: Refine your search to only Report
open access

Expressions for Conversion Ratio in a Th-U²³⁵ Converter

Description: "This memo shall be an attempt to write down in a consistent manner some expressions for conversion ratio so that a comparison can be made with regard to a uniformly loaded core versus a flattered zone surrounded by an unloaded region. The discussion will be limited to the type of loading that is at present being considered for the reactor - a checkerboard array of MTR fuel elements and feed elements; the unloaded reactor will consist of fuel elements only."
Date: December 19, 1951
Creator: Cohen, E. Richard, 1922- & Benton, A.
Item Type: Refine your search to only Report
open access

Schlieren investigation of the wing shock-wave boundary-layer interaction in flight

Description: Report presenting data obtained in flight using a schileren apparatus that photographed the shock-wave interaction with a thick turbulent boundary layer on a wing. Local Mach number and boundary-layer characteristics obtained from pressure measurements in the vicinity of the shock wave are also presented.
Date: September 19, 1951
Creator: Cooper, George E. & Bray, Richard S.
Item Type: Refine your search to only Report
open access

Effect of Hanford Pile Effluent Upon Aquatic Invertebrates in the Columbia River

Description: Abstract: "This is the preliminary report of a radiological-ecological survey of the invertebrate fauna that inhabit the Columbia River within the confines of Hanford Works and downstream to the site of McNary Dam. The survey was carried out during the period of October, 1948 through February, 1950. Materials and methods are discussed and the results of extensive radioassays, qualitative and quantitative biological determinations, and hydrographic studies are given and analyzed. Twelve figures … more
Date: January 19, 1951
Creator: Davis, Jared J. & Cooper, Calvin L.
Item Type: Refine your search to only Report
open access

Flight Performance of a Twin-Engine Supersonic Ram Jet From 2,300 to 67,200 Feet Altitude

Description: Report presenting a flight investigation of a ground-launched supersonic twin ram-jet test vehicle using short flame-length burners. Results were obtained for a range of Mach numbers, altitudes, and fuel-air-ratios. Engine performance, gross thrust, fuel rate, total impulse, values of combustion efficiency and impulse, and overall combustion efficiency are also included.
Date: February 19, 1951
Creator: Dettwyler, H. Rudolph & Bond, Aleck C.
Item Type: Refine your search to only Report
open access

Force and pressure characteristics for a series of nose inlets at Mach numbers from 1.59 to 1.99 1: conical spike all-external compression inlet with subsonic cowl lip

Description: Report presenting an experimental investigation to determine the force and pressure characteristics of a typical nose inlet ramjet configuration. It consisted of a conical spike all-external compression inlet attached to an annular subsonic diffuser. Results regarding external-flow characteristics and internal-flow characteristics are provided.
Date: January 19, 1951
Creator: Esenwein, Fred T. & Valerino, Alfred S.
Item Type: Refine your search to only Report
open access

Low-speed longitudinal and wake air-flow characteristics at a Reynolds number of 5.5 x 10(exp 6) of a circular-arc 52 degrees sweptback wing with a fuselage and a horizontal tail at various vertical positions

Description: Report presenting an investigation in the 19-foot pressure tunnel to determine the effects of a fuselage and a horizontal tail located at various vertical positions on the low-speed longitudinal characteristics of a circular-arc 52 degree sweptback wing. Results regarding the effect of fuselage on longitudinal characteristics of the wing, effect of tail position on stability and tail effectiveness, and air-flow characteristics are provided.
Date: June 19, 1951
Creator: Foster, Gerald V. & Griner, Roland F.
Item Type: Refine your search to only Report
open access

Investigation at Mach Number 1.88 of Half of a Conical-Spike Diffuser Mounted as a Side Inlet With Boundary-Layer Control

Description: Experimental investigation was conducted at Mach number 1.88 to determine performance characteristics of half a 50 degree-conical-spike inlet mounted on a flat plate. Initial boundary layer was removed up-stream of inlet by a ram-type scoop of variable height. Initial boundary-layer thickness was also varied. With complete removal of initial boundary layer, total-pressure recovery of approximately 70 percent. Several alternative boundary-layer-removal systems were investigated which decreased t… more
Date: September 19, 1951
Creator: Goelzer, H. Fred & Cortright, Edgar M., Jr.
Item Type: Refine your search to only Report
open access

Notes from Talk on Dimensional Changes in Uranium given on September 19, 1951

Description: It was the purpose of this talk to present up-to-date information with regards to dimensional stabilityof metallic uranium. A brief discusssion concerning the history, present status, proposed theories, and recent results are given. The factors affecting and methods of minimizing dimension changes are outlined.
Date: September 19, 1951
Creator: Hayward, B.R.
Item Type: Refine your search to only Report
open access

An Experimental Investigation at Subsonic Speeds of a Scoop-Type Air-Induction System for a Supersonic Airplane

Description: Report presenting an investigation at subsonic speeds of a scoop-type air-induction system designed for use at subsonic and supersonic speeds. Measurements of the ram-recovery ratio and static pressures in a scoop-type intake on the upper surface of the fuselage were taken for a large range of mass-flow ratios, angles of attack, and angles of sideslip.
Date: July 19, 1951
Creator: Holzhauser, Curt A.
Item Type: Refine your search to only Report
open access

Flight Measurements With the Douglas D-558-II (BuAero No. 37974) Research Airplane: Measurements of the Distribution of the Aerodynamic Load Among the Wing, Fuselage, and Horizontal Tail at Mach Numbers Up to 0.87

Description: "Flight measurements of the aerodynamic wing and tail loads have been made on the Douglas D-558-II airplane from which the distribution of the aerodynamic load among the wing, fuselage, and horizontal tail has been determined at Mach numbers up to 0.87. These measurements indicate that, for normal-force coefficients less than 0.7, the distribution of air load among the airplane components does not change appreciably with Mach number at Mach number up to 0.87. The measurements also indicate that… more
Date: January 19, 1951
Creator: Mayer, John P. & Valentine, George M.
Item Type: Refine your search to only Report
open access

Mound Laboratory participation in the Kelley-Koett Instrument Company radium accident

Description: At 11:20 A.M. Tuesday, July 24, 1951, a radium capsule containing 49.6 milligrams of radium became open to the atmosphere t the Kelley-Koett instrument Company, 930 York Street, Cincinnati, Ohio. This radium was contained in a platinum tube and was used for the purpose of calibrating radiation detection instruments. At the time of the accident, the actual chemical composition of the radium salt was not known. On Tuesday morning, July 31, 1951, Mr. W.A. Bigler and Mr. R.A. Miller of the Monsanto… more
Date: September 19, 1951
Creator: Miller, R. A.; Bigler, W. A.; Jolley, W. P. & Garner, J. M.
Item Type: Refine your search to only Report
open access

Thorium and Thorium Alloys Preliminary Corrosion Tests

Description: Technical report investigating the corrosion resistance of thorium and thorium alloys containing from 2 to 6% chromium, columbinium (niobium), titanium, zirconium and titanium-zirconium in distilled water at 95ºC. The true effects of the various alloy additions could not be determined because of the more marked effect of cold working. [From Abstract]
Date: December 19, 1951
Creator: Olsen, Arnold R.
Item Type: Refine your search to only Report
open access

Aerodynamic characteristics of the NACA RM-10 research missile in the Ames 1- by 3-foot supersonic wind tunnel no. 2: Pressure and force measurements at Mach numbers of 1.52 and 1.98

Description: Report presenting an experimental investigation of the aerodynamic characteristics of a fin-stabilized body of revolution, designated as RM-10, in a supersonic wind tunnel. Pressure distributions and force characteristics were determined at two different Mach numbers. Results regarding pressure distributions, body-alone force tests, and body-tail combination force tests are provided.
Date: September 19, 1951
Creator: Perkins, Edward W.; Gowen, Forrest E. & Jorgensen, Leland H.
Item Type: Refine your search to only Report
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