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THE HEAT CAPACITY OF BERYLLIUM CARBIDE POWDER IN STAINLESS STEEL CAPSULES AS A FUNCTION OF TEMPERATURE (400-1800 F)

Description: The mean heat capacity of a sample of powdered beryllium carbide, a possible moderator material for a nuclear reactor, was determined as a function of temperature. A thin-walled stainless steel capsule containing the material was heated in an electric furnace and dropped into a water calorimeter. The following linear equation for mean heat capacity over the temperature range 50 f C-T f C as a function of temperature, T, was derived from the data by the method of least squares: C/sub p/ = 0.299 … more
Date: April 20, 1949
Creator: Powers, H.; Kostigen, T. & Trice, J.B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Icing-protection requirements for reciprocating-engine induction system

Description: From Summary: "Despite the development of relatively ice-free fuel-metering systems, the widespread use of alternate and heated-air intakes, and the use of alcohol for emergency de-icing, icing of aircraft-engine induction systems is a serious problem. Investigations have been made to study and to combat all phases of this icing problem. From these investigations, criterions for safe operation and for design of new induction systems have been established. The results were obtained from laborato… more
Date: June 20, 1949
Creator: Coles, Willard D.; Rollin, Vern G. & Mulholland, Donald R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Measurements of Aileron Effectiveness of Bell X-1 Airplane Up to a Mach Number of 0.82

Description: "Abrupt, rudder-fixed aileron rolls have been made with the Bell X-1 airplane having a 10-percent-thick wing in glides to a Mach number of 0.82 at about 30,000 feet pressure altitude. Aileron movements were between one-fourth and one-half of full deflection. These aileron rolls indicate that Mach number has little effect on the aileron effectiveness up to a Mach number of 0.82" (p. 1).
Date: June 20, 1949
Creator: Drake, Hubert M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Flight Investigation of the Effect of Boundary-Layer Suction on Profile-Drag Coefficient at Supercritical Mach Numbers

Description: Memorandum presenting flight tests with a fighter airplane to study the effect of boundary-layer suction aft of the shock wave on airfoil drag at supercritical Mach numbers and high Reynolds numbers. Airfoil chord force was determined from pressure-distribution measurements obtained at a range of Mach numbers at steady dives. Results of the tests showed no measurable effect of suction for the suction coefficient available.
Date: September 20, 1949
Creator: Skoog, Richard B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

A Free-Flight Technique for Measuring Damping in Roll by Use of Rocket-Powered Models and Some Initial Results for Rectangular Wings

Description: Report presenting a simplified method for obtaining free-flight measurements of damping in roll through the use of rocket-powered models. Initial configurations have been tested for a range of Mach numbers. Results regarding the rolling velocity with two different airfoil sections and damping-in-roll coefficient are provided.
Date: December 20, 1949
Creator: Edmondson, James L. & Sanders, E. Claude, Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Investigation of Extensible Wing-Tip Ailerons on an Untapered Semispan Wing at 0 Degree and 45 Degrees Sweepback

Description: Report presenting a low-speed wind-tunnel investigation to determine the lateral control characteristics of extensible wing-tip ailerons on an untapered semispan wing with two configurations; one was unswept and had an aspect ratio of 3.13 and the other was swept back 45 degrees and had an aspect ratio of 1.59. Results regarding the plain-wing aerodynamic characteristics and lateral control characteristics are provided.
Date: September 20, 1949
Creator: Hagerman, John R. & O'Hare, William M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Investigation of a thin wing of aspect ratio 4 in the Ames 12-foot pressure wind tunnel 4 : the effect of a constant-chord leading-edge flap at high subsonic speeds

Description: Report presenting wind-tunnel tests of a semispan model of a thin sharp-edged unswept wing of aspect ratio 4 and taper ratio 0.5 equipped with a full-span, constant-chord, leading-edge flap. The effectiveness of the leading-edge flap in improving the lift-drag ratio of the wing was investigated over a range of Mach and Reynolds numbers. Results regarding the lift characteristics, drag characteristics, pitching-moment characteristics, and lift-drag ratio are provided.
Date: January 20, 1949
Creator: Johnson, Ben H., Jr. & Reed, Verlin D.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Pressure Distributions on Thin Conical Body of Elliptic Cross Section at Mach Number 1.89

Description: Memorandum presenting an investigation conducted to determine the pressure distribution on a conical body of elliptic cross section at a Mach number of 1.89. Experimental data are presented for a range of angles of yaw from -16 to 16 degrees and angles of attack from -10 to 10 degrees. As the angle of flow deflection was increased, the deviation from experiment of the theoretical pressure distribution slightly increased, although agreement was satisfactory over the entire range of calculations.
Date: January 20, 1949
Creator: Maslen, Stephen H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

The effect of rate of change of angle of attack on the maximum lift coefficient of a pursuit airplane

Description: Report presenting an investigation of the effect of the rate of change of angle of attack on the maximum lift coefficient of a pursuit airplane equipped with a low-drag-type wing in stalls of varying abruptness over a range of Mach and Reynolds numbers. Maximum lift coefficients were found to increase linearly with increasing rate of change of angle of attack per chord length of travel up to the maximum rate attained in the tests.
Date: January 20, 1949
Creator: Gadeberg, Burnett L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Effects of high-lift and stall-control devices, fuselage, and horizontal tail on a wing swept back 42 degrees at the leading edge and having symmetrical circular-arc airfoils sections at a Reynolds number of 6.9 x 10(exp 6)

Description: Report presenting an investigation of the low-speed characteristics of a wing swept back 42 degrees at the leading edge and having various high-lift and stall-control devices and fuselage and horizontal tail vertical positions. Results regarding the characteristics of the basic wing, leading-edge flap investigation, wing fuselage investigation, and horizontal tail investigation are provided.
Date: April 20, 1949
Creator: Woods, Robert L. & Spooner, Stanley H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Aerodynamic characteristics of a wing with quarter-chord line swept back 45 degrees, aspect ratio 6, taper ratio 0.6, and NACA 65A009 airfoil section

Description: 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 45^o, aspect ratio 4, taper ratio 0.3, and an NACA 65A006 airfoil section parallel to the stream."
Date: July 20, 1949
Creator: Spreemann, Kenneth P.; Morrison, William D., Jr. & Pasteur, Thomas B., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Correlation of Physical Properties With Molecular Structure for Some Dicyclic Hydrocarbons Having High Thermal-Energy Release Per Unit Volume

Description: "As part of a program to study the correlation between molecular structure and physical properties of high-density hydrocarbons, the net heats of combustion, melting points, boiling points, densities, and kinematic viscosities of some hydrocarbons in the 2-n-alkylbiphenyl, 1,1-diphenylalkane, diphenylalkane, 1,1-dicyclohexylalkane, and dicyclohexylalkane series are presented" (p. 55).
Date: June 20, 1949
Creator: Wise, P. H.; Serijan, K. T. & Goodman, I. A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Redox Committee: Conference notes and recommendations, meeting of June 16, 1949

Description: Topics discussed included scope of work by the Kellex Corporation; Redox Production Plant procurement; bearing capacity of soils and other site characterization for the Redox Production Plant site; purchase of Moyno pumps; scope drawing schedules; 68% nitric acid requirements for the process; pump development for the Redox Production Plant; vessel specifications; Design basis letters on electrical distribution, steam distribution, raw and filtered water distribution, and railroads. The report i… more
Date: June 20, 1949
Creator: Greager, O. H.; MacCready, W. K. & Seckendorff, E. W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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