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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.
Partner: UNT Libraries Government Documents Department
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.
Partner: UNT Libraries Government Documents Department
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Zero-Lift Drag of the Chance Vought Regulus II Missile at Mach Numbers Between 0.8 and 2.2 as Determined From the Flight Tests of Two 0.12-Scale Models: TED No. NACA AD 398

Description: Report presenting testing of two scale models of the Chance Vought Regulus II missile to investigate its drag characteristics for a range of Mach numbers from 0.8 to 2.2. Due to some of the differences between the observed drag values and previous testing, the exact drag level of the configuration tested is still in question. Results regarding total drag and external drag are provided.
Date: July 27, 1954
Creator: Church, James D.
Partner: UNT Libraries Government Documents Department
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
Partner: UNT Libraries Government Documents Department
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.
Partner: UNT Libraries Government Documents Department
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.
Partner: UNT Libraries Government Documents Department
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.
Partner: UNT Libraries Government Documents Department
open access

Tests of the Northrop XB-62 Missile in the Ames 40- by 80-Foot Wind Tunnel

Description: Memorandum presenting a series of tests made on a full-scale Northrop XB-62 missile to determine the cause of a directional out-of-trim condition which was encountered on the initial missile flight tests. The results indicated that the directional out-of-trim condition was caused by aerodynamic loads induced by engine operation.
Date: September 27, 1954
Creator: Graham, David
Partner: UNT Libraries Government Documents Department
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.
Partner: UNT Libraries Government Documents Department
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
Partner: UNT Libraries Government Documents Department
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.
Partner: UNT Libraries Government Documents Department
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.
Partner: UNT Libraries Government Documents Department
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.
Partner: UNT Libraries Government Documents Department
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.
Partner: UNT Libraries Government Documents Department
open access

AN ERROR ANALYSIS OF R-C TIMERS

Description: No Description Available.
Date: August 27, 1954
Creator: Stromberg, R.P.
Partner: UNT Libraries Government Documents Department
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.
Partner: UNT Libraries Government Documents Department
open access

Sample Collector and Counter

Description: From abstract: "An apparatus is described which automatically separates a flow of drops into a series of equal samples."
Date: July 27, 1954
Creator: Deal, James B., Jr. & Buchen, John F.
Partner: UNT Libraries Government Documents Department
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