UNT Libraries Government Documents Department - 31 Matching Results

Search Results

Results: 1 - 24 next
open access

Air Sample Activity vs Flow Rate

Description: A bibliography on the subject of air sample activity vs flow rate has been prepared. The findings in two documents reviewed have been applied directly to this problem. It is concluded that air sample activity is not dependent on flow rate when sampling particles whose average diameter in 0.06 micron or greater.
Date: December 27, 1954
Creator: Clark, R. G.
Item Type: Refine your search to only Report
open access

Altitude investigation of 20-inch-diameter ram-jet engine with annular-piloted combustor

Description: From Introduction: "The combustor efficiency, combustor-inlet Mach number, and combustor total-pressure ratio of the annular-piloted combustor are presented herein. The effect of combustor-exit total pressure on combustor efficiency, and a comparison of configurations on the basis of specific fuel consumption are also presented."
Date: August 27, 1954
Creator: Henzel, James G. & Trout, Arthur M.
Item Type: Refine your search to only Report
open access

Comparison of low-speed rotor and cascade performance for medium-camber NACA 65-(C(sub lo)A(sub 10) 10 compressor-blade sections over a wide range of rotor blade-setting angles at solidities. of 1.0 and 0.5

Description: Report presenting testing of a medium-camber compressor rotor with particular NACA blades in a low-speed 28-inch test blower. Testing was made at solidities of 1.0 and 0.5 without guide vanes or stators over a wide range of blade-setting angles and quantity flow rates. Results regarding overall rotor performance, comparison between measured and estimated section efficiencies near design angle of attack, comparison between low-speed rotor and cascade turning angles, and detailed blade section pe… more
Date: December 27, 1954
Creator: Ashby, George C., Jr.
Item Type: Refine your search to only Report
open access

Drag Measurements on a 1/6-Scale, Finless, Sting-Mounted NACA RM-10 Missile in Flight at Mach Numbers From 1.1 to 4.04 Showing Some Reynolds Number and Heating Effects

Description: Report discussing a finless NACA RM-10 missile string-mounted on a parent body to determine the total drag, base drag, and wall temperature at peak Mach number 4.04. The total- and base-drag measurements were well-correlated with wind tunnel results and calculations made by using Love's method. The existence of considerable regions of laminar flow on the body during the flight were observed.
Date: October 27, 1954
Creator: Piland, Robert O.
Item Type: Refine your search to only Report
open access

Effect of rotation of a NACA 1-series E-type cowling on the internal flow and force characteristics of the cowling at Mach numbers up to 0.84 and at an angle of attack of 0 degrees

Description: Report presenting an investigation to determine the effect of rotation on the internal flow and force characteristics of an NACA 1-series E-type cowl, designed to operate with a four-blade single-rotation propeller. Results regarding internal-flow characteristics, force characteristics, and velocity distributions are provided.
Date: October 27, 1954
Creator: Sammonds, Robert I. & Reynolds, Robert M.
Item Type: Refine your search to only Report
open access

The Effect of Wing Profile on the Transonic Characteristics of Rectangular and Triangular Wings Having Aspect Ratios of 3: Transonic Bump Technique

Description: Report presenting an investigation to determine the effect of wing profile on the transonic aerodynamic characteristics of rectangular and triangular wings with aspect ratios of 3. Five wings were compared over a range of Mach and Reynolds number. Results regarding the rectangular and triangular wings and use of transonic area rule are provided.
Date: October 27, 1954
Creator: Nelson, Warren H. & Frank, Joseph L.
Item Type: Refine your search to only Report
open access

An error Analysis of R-C Timers

Description: The results of this paper show that a variation is sensing voltage produces an error in timing which increases logarithmically with time interval. Also, variation in supply voltage produces the same type of errors, but the errors are decreased by the ratio of the sensing to supply voltage. An interesting conclusion from this analysis is that if the ratio of supply to sensing voltages is maintained constant, no change in timing will result.
Date: August 27, 1954
Creator: Stromberg, R. P. (Robert P.)
Item Type: Refine your search to only Report
open access

Experimental Investigation at High Subsonic Speeds to Determine the Rolling-Stability Derivatives of Three Wing-Fuselage Configurations

Description: Memorandum presenting rolling-stability derivatives for three wing configurations, which were tested on the same fuselage, over a range of Mach numbers and angles of attack. The wings were assorted plan-form configurations of current interest and were not part of a geometrically related series of plan forms. Results regarding basic damping-in-roll results, estimation of rolling derivatives, and estimated effects of Reynolds number are provided.
Date: October 27, 1954
Creator: Sleeman, William C., Jr.
Item Type: Refine your search to only Report
open access

Hot semiworks Redox studies

Description: The separations Hot Semiworks at the Hanford Atomic Products Operation was built in order to: (1) develop optimum conditions for the economic operation of the Redox and TBP plants, (2) procure engineering design data which would allow the specification of process equipment required for new processes such as Purex, (3) provide facilities for the study of future process and engineering problems on a semiworks scale employing radioactive process solutions, and (4) provide facilities for immediate … more
Date: January 27, 1954
Creator: Evans, T. F. & Tomlinson, R. E.
Item Type: Refine your search to only Report
open access

Influence of Combustion-chamber Length on Afterburner Performance

Description: Memorandum presenting an investigation of the influence of combustion-chamber length on afterburner performance under conditions simulating altitude flight. Results regarding afterburner-inlet conditions, operational limits, and structural cooling requirements are provided.
Date: August 27, 1954
Creator: Useller, James W.; Braithwaite, Willis M. & Rudey, Carl J.
Item Type: Refine your search to only Report
open access

Influence of combustion-chamber length on afterburner performance

Description: Report presenting an investigation of the influence of combustion-chamber length on afterburner performance under conditions simulating altitude flight. The component design and arrangement were selected from the results of previous investigations to produce maximum thrust augmentation near the stoichiomtric condition. Results regarding afterburner-inlet conditions, operational limits, and structural cooling requirements are provided.
Date: August 27, 1954
Creator: Useller, James W.; Braithwaite, Willis M. & Rudey, Carl J.
Item Type: Refine your search to only Report
open access

Investigation of several double-ramp side inlets

Description: Report presenting an investigation of several double-ramp inlets utilizing a variable-angle second ramp mounted on the fuselage of a supersonic airplane with a twin-duct air intake system and investigated at several Mach numbers. With all of the inlets, the boundary-layer air from the precompression ramp bridged across the leading edge of the variable ramp.
Date: August 27, 1954
Creator: Stitt, Leonard E. & Wise, George A.
Item Type: Refine your search to only Report
open access

Longitudinal Stability Characteristics in Accelerated Maneuvers at Subsonic and Transonic Speeds of the Douglas D-558-II Research Airplane Equipped with a Leading-Edge Wing Chord-Extension

Description: Memorandum presenting an investigation of the Douglas D-558-II swept-wing research airplane with various modifications designed to alleviate swept-wing instability and pitch-up. In this study, the airplane was modified to include wing-chord extensions and was flight-tested.
Date: October 27, 1954
Creator: Fischel, Jack & Brunn, Cyril D.
Item Type: Refine your search to only Report
open access

Low-Speed Measurements of Rolling and Yawing Stability Derivatives of a 60 Degree Delta-Wing Model

Description: Memorandum presenting an investigation in the free-flight tunnel to determine the low-speed rolling and yawing stability derivatives of a 60 degree delta-wing model from 0 to 30 degrees angle of attack. The derivatives were measured by the free-to-damp oscillation technique and by the steady-roll technique.
Date: December 27, 1954
Creator: Johnson, Joseph L., Jr.
Item Type: Refine your search to only Report
open access

Measurements of Normal-Force-Coefficient Fluctuation on Four 9-Percent-Thick Airfoils Having Different Locations of Maximum Thickness

Description: Memorandum presenting a two-dimensional wind-tunnel investigation of the effects of maximum-thickness location on fluctuating pressures and normal-force coefficients on 9-percent-thick airfoils, which indicated that for normal-force coefficients up to 0.6, the section variables had little effect on the pressure pulsations and root-mean-square normal-force-coefficient fluctuations. Results regarding pressure fluctuations and normal-force-coefficient fluctuations are provided.
Date: April 27, 1954
Creator: Humphreys, Milton D.
Item Type: Refine your search to only Report
open access

Performance of a 16-inch ram-jet engine with a can-type combustor at Mach numbers of 1.50 to 2.16

Description: Report presenting an investigation in the supersonic wind tunnel to evaluate the performance of a 16-inch ramjet engine using a can-type-combustor configuration. Data were obtained over a range of fuel-air ratios, free-stream Mach numbers, and angles of attack. Combustion efficiencies were generally unaffected by free-stream Mach number and varied between 60 and 90 percent with JP-4 fuel.
Date: August 27, 1954
Creator: Hearth, Donald P. & Perchonok, Eugene
Item Type: Refine your search to only Report
open access

A Preliminary Flight Investigation of an Oil-Flow Technique for Air-Flow Visualization

Description: Report presenting a preliminary flight investigation to evaluate an oil-flow technique for air-flow visualization. Mixtures of silicone oil and finely powdered graphite particles were spread on a wing panel of a swept-wing jet airplane and photographs were taken of the oil patterns that formed in flight at transonic speeds and on the ground. An interpretation of the photographs is provided.
Date: October 27, 1954
Creator: Johnson, Harold I. & Mungall, Robert G.
Item Type: Refine your search to only Report
open access

Preliminary investigation of an annular turbojet combustor having a catalytic-coated liner

Description: From Summary: "The performance of an experimental annular turbojet combustor was investigated at a low-pressure operating condition with an uncoated liner, with an identical liner having a ceramic coating on the inner walls, and with this same liner having a catalytic coating added onto the ceramic coating. The combustion efficiency was approximately the same for all three liners, thus indicating no gain in performance through the use of the catalytic coating."
Date: January 27, 1954
Creator: Norgren, Carl T. & Childs, J. Howard
Item Type: Refine your search to only Report
Back to Top of Screen