UNT Libraries Government Documents Department - 41 Matching Results

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Altitude investigation of 16 flame-holder and fuel-system configurations in tail-pipe burner

Description: From Introduction: "The data obtained for each configuration are presented in a manner to show the effects of fuel distribution and flame-holder design on net thrust, specific fuel consumption, exhaust-gas temperature, combustion efficiency, operable range of tail-pipe-burner fuel-air ratios, and maximum altitude limit."
Date: December 12, 1951
Creator: Grey, Ralph E.; Krull, H. G. & Sargent, A. F.
Item Type: Refine your search to only Report
open access

Boiling Reactors: A Preliminary Investigation

Description: Technical report detailing kinetic equations that have been developed for a boiling-type reactor and inherent reactor stability studies that have been made on the basis of these equations. Presents features of the proposed reactor, comparisons of circulating types, investigations of bubble-rise velocities, effects of transient conditions of vapor mass in steam chest, and bubble time delay functions yield favorable results. [From Abstract]
Date: December 12, 1951
Creator: Stein, J. M. & Kasten, P. R.
Item Type: Refine your search to only Report
open access

Calculated and observed P-10 production in H-10

Description: Recently three H-10 tubes (2,772, 2,176, 3,673) have been removed and the tritium and other gases have been extracted from the Z slugs. It is of interest to compare the calculated volumes of gases with the amounts obtained in these extractions. The comparison is given in this paper. The reasons for the large disagreement are not known at present. As pointed out below, the weakest part of the calculation is the knowledge of the exposure which these Z slugs have received. It is possible that some… more
Date: January 12, 1951
Creator: Ozeroff, W. J.
Item Type: Refine your search to only Report
open access

Characteristics throughout the subsonic speed range of a plane wing and of a cambered and twisted wing, both having 45 degrees of sweepback

Description: Report presenting a wind-tunnel investigation of two semispan wing models with 45 degrees of sweepback, an aspect ratio of 5, and a taper ratio of 0.565. One wing had no camber or twist while the other was cambered for a design lift coefficient of 0.4 and twisted to relieve loading at the tip. Results regarding the plane wing, cambered and twisted wing, wing-body combinations, effect of camber and twist, effect of fences, effect of surface roughness, and lift-drag ratio are provided.
Date: July 12, 1951
Creator: Johnson, Ben H., Jr. & Shibata, Harry H.
Item Type: Refine your search to only Report
open access

Considerations on a Large Hydraulic Jet Catapult

Description: Report presenting a survey of various types of catapults in connection with the problem of accelerating a large car along a track to a speed of 150 miles per hour. A hydraulic jet catapult seems to be the best-suited for the purpose, and various types of design problems are examined.
Date: April 12, 1951
Creator: Joyner, Upshur T. & Horne, Walter B.
Item Type: Refine your search to only Report
open access

The Corrosion of Various Stainless Steels in Synthetic Waste Solutions

Description: Technical report describing the tests on types 309, 316, and 347 stainless steel. These steels were tested for a total of 779 to 828 hours in three different synthetic waste solutions. Results shoe that the best all-around corrosion resistance to the test conditions was exhibited by 316 stainless steel, but in one solution 347 stainless steel was more resistant. [From Abstract]
Date: February 12, 1951
Creator: English, James L.
Item Type: Refine your search to only Report
open access

Effect of Angle of Incidence of Second-Stage Vane Assembly on Third-Stage Compressor-Blade Vibration and Engine Performance

Description: "Strain-gages were used to measure blade vibrations causing failures in the third stage of a production 11-stage axial-flow compressor. After the serious third-stage vibration was detected, a series of investigations were conducted with second-stage vane assemblies of varying angles of incidence. Curves presented herein show the effect of varying the angle of incidence of second-stage vane assembly on third-stage rotor-blade vibration amplitude and engine performance" (p. 1).
Date: June 12, 1951
Creator: Meyer, André J., Jr. & Calvert, Howard F.
Item Type: Refine your search to only Report
open access

The Effect of End Plates, End Struts, and Depth of Submergence on the Characteristics of a Hydrofoil

Description: Report presenting an investigation into the effect of end plates and end-mounted struts on the lift-drag ratios of a hydrofoil at several speeds and Reynolds numbers that were all above the limiting speed of wave propagation. Information about the lift-drag ratio, effective aspect ratio, and comparison of the results versus theoretical calculations is included.
Date: April 12, 1951
Creator: Wadlin, Kenneth L.; Fontana, Rudolph E. & Shuford, Charles L., Jr.
Item Type: Refine your search to only Report
open access

Experimental Evaluation by Thermodynamic Methods of Work Input to a Centrifugal Compressor Operating With Water Injection

Description: Memorandum presenting a thermodynamic method of determining the work input to a centrifugal compressor operating with water injection. The method was used to compute the work input to a double-entry centrifugal compressor, which was operated at a design equivalent impeller speed over a range of inlet-water ratios and varying weight flow.
Date: January 12, 1951
Creator: Kovach, Karl; Beede, William L. & Hamrick, Joseph T.
Item Type: Refine your search to only Report
open access

Experimental Investigation of Air-Cooled Turbine Blades in Turbojet Engine. 7: Rotor-Blade Fabrication Procedures

Description: "An experimental investigation was conducted to determine the cooling effectiveness of a wide variety of air-cooled turbine-blade configurations. The blades, which were tested in the turbine of a - commercial turbojet engine that was modified for this investigation by replacing two of the original blades with air-cooled blades located diametrically opposite each other, are untwisted, have no aerodynamic taper, and have essentially the same external profile. The cooling-passage configuration is … more
Date: September 12, 1951
Creator: Long, Roger A. & Esgar, Jack B.
Item Type: Refine your search to only Report
open access

Experimental Investigation of an 0.8 Hub-Tip Radius-Ratio, Nontwisted-Rotor-Blade Turbine

Description: "An experimental investigation of a 0.8 hub-tip radius ratio, nontwisted-rotor-blade turbine designed for a stagnation-pressure ratio of 2.5 and an equivalent mean blade speed of 643 feet per second was made in a cold-air turbine with (a) nontwisted stator blades, and (b) twisted stator blades designed to maintain zero rotor-inlet incidence angles. Turbine efficiencies of the order of 0.85 at the design point were obtained with a nontwisted-rotor-blade turbine with a hub-tip radius ratio of 0.8… more
Date: December 12, 1951
Creator: Silvern, David H. & Slivka, William R.
Item Type: Refine your search to only Report
open access

A flight evaluation of the longitudinal stability characteristics associated with the pitch-up of a swept-wing airplane in maneuvering flight at transonic speeds

Description: This report presents the results of flight measurements of longitudinal stability and control characteristics made on a swept-wing jet aircraft to determine the origin of the pitch-up encountered in maneuvering flight at transonic speeds. For this purpose measurements were made of elevator angle, tail angle of attack, and wing-fuselage pitching moments (obtained from measurements of the balancing tail loads).
Date: September 12, 1951
Creator: Anderson, Seth B. & Bray, Richard S.
Item Type: Refine your search to only Report
open access

Flow Separation Ahead of a Blunt Axially Symmetric Body at Mach Numbers 1.76 to 2.10

Description: "The pressure distribution and drag were determined for a spherical-nosed axially symmetric body with thin projecting rods at Mach numbers of 1.76, 1.93, and 2.10. The upstream projection distance of the rods was varied over a wide range to study changes in the character of the flow separation and to determine the variation of drag and pressure distribution with tip projection. Drag coefficients between 0.18 and 0.30 were obtained for most tip projections at each Mach number" (p. 1).
Date: December 12, 1951
Creator: Moeckel, W. E.
Item Type: Refine your search to only Report
open access

Generalization of Turbojet and Turbine-Propeller Engine Performance in Windmilling Condition

Description: Windmilling characteristics of several turbojet and turbine-propeller engines were investigated individually over a wide range of flight conditions in the NACA Lewis altitude wind tunnel. A study was made of all these data and windmilling performance of gas turbine engines was generalized. Although internal-drag, air-flow, and total-pressure-drop parameters were generalized to a single curve for both the axial-flow type engines and another for the centrifugal-flow engine.
Date: December 12, 1951
Creator: Wallner, Lewis E. & Welna, Henry J.
Item Type: Refine your search to only Report
open access

Horizontal-Tail Effectiveness and Downwash Surveys for Two 47.7 Degree Sweptback Wing-Fuselage Combinations With Aspect Ratios of 5.1 and 6.0 at a Reynolds Number of 6.0 X 10(Exp 6)

Description: Report presenting an experimental investigation of the effectiveness of a horizontal tail on two 47.7 degree sweptback wing-fuselage combinations of aspect ratios 5.1 and 6.0. Various combinations of components were tested, including leading-edge flaps, drooped-nose, split flaps, and double slotted flaps, in addition to the flaps-neutral configuration. The primary purpose of the study was to determine the longitudinal stability characteristics of these wings in combination with the fuselage and… more
Date: January 12, 1951
Creator: Salmi, Reino J.
Item Type: Refine your search to only Report
open access

Investigation at Mach number 1.91 of side and base pressure distributions over conical boattails without and with jet flow issuing from base

Description: Experimental side and blade pressure distributions over a series of conical boattails without and with jet flow from the base are presented at a Mach number of 1.91. For the case of no jet flow the methods of characteristics and linearized theory are shown to overpredict the side pressure drag. A semi-empirical theory is presented to predict the effect of boattail angle on base pressure. With the boattail extending to a sharp edge at the nozzle exit, the over-pressure jet is shown to decrease t… more
Date: September 12, 1951
Creator: Cortright, Edgar M., Jr. & Schroeder, Albert H.
Item Type: Refine your search to only Report
open access

Investigation of a 24-inch shock-in-rotor type supersonic compressor designed for simple radial equilibrium behind normal shock

Description: A 24-inch-diameter shock-in-rotor supersonic compressor rotor designed to obtain simple radial equilibrium behind the normal shock obtained a maximum total-pressure ratio of 2.02 at an adiabatic efficiency of 0.74 and a weight flow of 61.5 pounds per second at design speed. Although this design method considerably reduced the radial forces, there was no apparent reduction in the radial forces, there was no apparent reduction in the radial redistribution of mass flow over the radial redistributi… more
Date: December 12, 1951
Creator: Lown, Harold & Hartmann, Melvin J.
Item Type: Refine your search to only Report
open access

Investigations of Slot Configurations for Film-Cooled Turbine Blades by Flow Visualization Methods

Description: Memorandum presenting an investigation on the effectiveness of different slot configurations, which uses the method of making the flow of the cooling air visible. Two methods were used for this purpose: one utilized the traces caused by a reaction between pain spread over the blade surface and a gas mixed with the cooling air, while the second utilized smoke mixed with the cooling air to make it visible. A continuous slot was found to give the best coverage of the cooling-air film.
Date: January 12, 1951
Creator: Eckert, E. R. G.; Jackson, Thomas W. & Francisco, Allen C.
Item Type: Refine your search to only Report
open access

Large-Scale Flight Measurements of Zero-Lift Drag at Mach Numbers from 0.90 to 1.95 of an Arrow Wing in Combination with a Small Body

Description: Report presenting a flight investigation at high subsonic, transonic, and supersonic speeds and at high Reynolds numbers to determine the zero-lift drag of an arrow wing-body combination and of the body without the wing. Results regarding the drag coefficient, Reynolds number, and normal-force coefficient against Mach number are provided.
Date: January 12, 1951
Creator: Gillespie, Warren, Jr. & Arbic, Richard G.
Item Type: Refine your search to only Report
open access

Lift, drag, and pitching moment of low-aspect-ratio wings at subsonic and supersonic speeds: twisted and cambered triangular wing of aspect ratio 2 with NACA 0003-63 thickness distribution

Description: This report presents the results of an investigation to ascertain the lift, drag, and pitching moment of a wing-body combination having a triangular wing of aspect ratio 2 with NACA 0003-63 thickness distribution in streamwise planes and twisted and cambered for a nearly elliptical span load distribution. Results are shown for Mach numbers from 0.60 to 0.90 and from 1.30 to 1.70 at Reynolds numbers of 3.0 million and 7.5 million.
Date: June 12, 1951
Creator: Hall, Charles F. & Heitmeyer, John C.
Item Type: Refine your search to only Report
open access

A Low Voltage Ion Source

Description: Describes the investigation of a particular method of extracting ions from an arc. Experimental results of a low extraction voltage ion source are given in some detail.
Date: July 12, 1951
Creator: Foster, J. S., (John Stuart), 1890-1964 & Martina, Eugene F.
Item Type: Refine your search to only Report
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