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Effect of wing flexibility on the damping roll of a notched delta-wing body combination between Mach numbers 0.6 and approximately 2.2 as determined with rocket-propelled models

Description: Report presenting an investigation with sting-mounted rocket-propelled models in free flight at approximately zero lift to determine the effect of wing flexibility on the damping-in-roll characteristics of a wing-body combination over a range of Mach numbers.
Date: June 18, 1954
Creator: Bland, William M., Jr.
Partner: UNT Libraries Government Documents Department
open access

Aerodynamic characteristics including effects of wing fixes of a 1/20-scale model of the Convair F-102 airplane at transonic speeds

Description: From Introduction: "Results from the tests in the Langley 4- by 4-foot supersonic pressure tunnel at Mach numbers of 1.61 and 2.01 are presented in reference 1. Reported herein are results obtained from the tests in the Langley 8-foot transonic tunnel of the model with no control deflections at Mach numbers 0.6 to 1.12 for angles of attack up to 34^o
Date: March 18, 1954
Creator: Osborne, Robert S. & Wornom, Dewey E.
Partner: UNT Libraries Government Documents Department
open access

An Investigation of a Supersonic Aircraft Configuration Having a Tapered Wing With Circular-Arc Sections and 40 Degree Sweepback: Aerodynamic Characteristics of the Configuration Equipped With a Canard Control Surface at a Mach Number of 1.89

Description: Memorandum presenting an investigation conducted in the 4- by 4-foot supersonic pressure tunnel to determine the aerodynamic characteristics of a supersonic aircraft configuration equipped with a canard control surface at a Mach number of 1.89. The model had a 40 degree sweptback tapered wing with an aspect ratio of 4 and 10-percent-thick circular-arc sections normal to the quarter-chord line. Results regarding the pitching-moment characteristics, lift and longitudinal-force characteristics, lo… more
Date: October 18, 1954
Creator: Spearman, M. Leroy & Plazzo, Edward B.
Partner: UNT Libraries Government Documents Department
open access

Free-flight measurements of the rolling effectiveness and operating characteristics of a bellows-actuated split-flap aileron on a 60 degree delta wing at Mach numbers between 0.8 and 1.8

Description: Report presenting a free-flight investigation in a range of Mach numbers to determine the maximum deflection, zero-lift rolling effectiveness, and general operating characteristics of a bellows-actuated aileron control system energized by the pitot (impact) pressure. Testing of a system with a partial-span spit-flap aileron on a 60 degree delta wing showed that it is promising for obtaining lateral control at supersonic speeds. Results regarding aileron rolling effectiveness, aileron hinge mome… more
Date: October 18, 1954
Creator: Schult, Eugene D.
Partner: UNT Libraries Government Documents Department
open access

Static Longitudinal Stability Characteristics of a Composite-Plan-Form-Wing-Model Including Some Comparisons with a 45 Degree Sweptback Wing at Transonic Speeds

Description: Memorandum presenting an investigation made to determine the low-subsonic-speed static longitudinal stability characteristics of a composite-plan-form wing tested as a wing-fuselage combination and as a complete model. Also included is a comparison of the transonic-speed characteristics of the composite-plan-form wing alone and the 45 degree sweptback wing from which the composite wing was derived.
Date: August 18, 1954
Creator: Wolhart, Walter D.
Partner: UNT Libraries Government Documents Department
open access

Performance of two air-cooled turbojet engines determined analytically from engine component performance for a range of cooling-air weight flows

Description: Report presenting an analysis of two turbojet engines, including the component performance of the compressors and turbines, in order to determine the effect on engine performance and operation of bleeding the compressor to furnish cooling air for the turbine rotor blades. Results regarding the compressor and turbine performance characteristics and engine performance characteristics are provided.
Date: February 18, 1954
Creator: Ziemer, Robert R.; Schafer, Louis J., Jr. & Heaton, Thomas R.
Partner: UNT Libraries Government Documents Department
open access

Measured Data Pertaining to Buffeting at Supersonic Speeds of the Douglas D-558-II Research Airplane

Description: Report presenting data obtained from an investigation of the Douglas-D558-II airplane to determine its buffeting characteristics at high lift and supersonic speeds. From Summary: "Buffeting was encountered at normal-force coefficients greater than about 0.7 in the Mach number range from 0.96 to 1.27 but at Mach number of 1.57, a peak normal-force coefficient of 0.80 was attained with no indication of buffeting. The increase in buffet intensity with lift is very gradual at supersonic speed compa… more
Date: February 18, 1954
Creator: Baker, Thomas F.
Partner: UNT Libraries Government Documents Department
open access

Effects of high-lift devices and horizontal-tail location on the low-speed characteristics of a large-scale 45 degree swept-wing airplane configuration

Description: Report presenting a low-speed investigation of a large-scale model with a 45 degree swept wing of aspect ratio 3.5 and taper ratio 0.3. Wing-fuselage configurations with high-lift devices designed to delay the occurrence of stalled flow to a specific high lift coefficient at a specific angle of attack were tested. Results regarding the lift and drag characteristics, pitching-moment characteristics and effective downwash, rolling-moment characteristics, and performance characteristics are provid… more
Date: August 18, 1954
Creator: Maki, Ralph L. & Embry, Ursel R.
Partner: UNT Libraries Government Documents Department
open access

Analysis and Construction of Design Charts for Turbines with Downstream Stators

Description: From Introduction: "This paper describes the theoretical treatment that has been given the combustion process as it occurs in turbojet combustors. Various parts of this work have been previously published (refs. 1 to 3); this report presents a brief summary of this previous work together with new data which amplify the conclusions of references 1 to 3. Similar studies have been made of the ram-jet combustion process (ref. 4 and 5); however, the analysis for ram-jet combustion differs in some de… more
Date: November 18, 1954
Creator: Cavicchi, Richard H. & Constantine, Anita B.
Partner: UNT Libraries Government Documents Department
open access

Ground Tests of the Elevator Power Control System and Feel Device in a Boeing B-47A Airplane

Description: Memorandum presenting ground tests made on the longitudinal control system in a Boeing B-47A airplane. The simulator tests showed the pilot-airplane-control-system combination to be satisfactory in spite of the relatively large phase lags noticed in the frequency-response tests. Results regarding the relation between elevator angle and stick force, relation between stick angle and stick force, relation between elevator angle and stick angle, and the simulator tests are provided.
Date: October 18, 1954
Creator: Brown, B. Porter
Partner: UNT Libraries Government Documents Department
open access

Transonic Flight Test of a Rocket-Powered Model to Determine Propulsive Jet Influence on the Configuration Drag

Description: Report presenting testing of a rocket-powered cone-cylinder body with a conical boattail to determine the jet interference effects on drag at transonic Mach numbers. If the nozzle was overexpanded, it increased boattail pressure drag at transonic Mach numbers, but an underexpanded nozzle affected boattail drag at 1.59, followed by a drag reduction.
Date: June 18, 1954
Creator: deMoraes, Carlos A.
Partner: UNT Libraries Government Documents Department
open access

Flight investigation of the effects of horizontal-tail height, moment of inertia, and control effectiveness on the pitch-up characteristics of a 35 degree swept-wing fighter airplane at high subsonic speeds

Description: Report presenting a flight investigation conducted on a 35 degree swept-wing fighter airplane with two different horizontal-tail heights. The longitudinal stability and buffet characteristics were compared for the two configurations. Results regarding longitudinal stability, buffet, and pitch-up intensity are provided.
Date: January 18, 1954
Creator: McFadden, Norman M. & Heinle, Donovan R.
Partner: UNT Libraries Government Documents Department
open access

SOLUBILITY OF CARBON IN THORIUM

Description: No Description Available.
Date: February 18, 1954
Creator: Mickelson, R. & Peterson, D.
Partner: UNT Libraries Government Documents Department
open access

Bismuth Phosphate process under 215 MWD program

Description: In the Bismuth Phosphate process, 100 tons of 215 MWD uranium can be processed each month using the present equipment. The activation of equipment in spare cells, contemplated process improvements, and transfer piping changes could increase the capacity of the process by about 20%. As the program is inaugurated, dissolver and extraction sections will control productive capacity of the process and first efforts will be directed toward increasing the efficiency and flexibility of operations in th… more
Date: March 18, 1954
Creator: Browne, W. G. & Beaulieu, O. F.
Partner: UNT Libraries Government Documents Department
open access

Electronuclear Research Division Semiannual Progress Report

Description: Nuclear physics research with 22-Mev protons in the 86-in. cyclotron included angular-distribution measurements of neutrons from (p,n) reactions in nine target elements; measurement of the angular distribution of fission fragments from proton-induced fission of U233, U225, U228, Th230, and Th232; measurement of alpha-particle angular distributions from (p,α) reactions a study of the neutron-deficient isotopes of terbium and completion of an extensive program of the measurement of activation cr… more
Date: November 18, 1954
Creator: Livingston, R. S. & Howard, F. T.
Partner: UNT Libraries Government Documents Department
open access

An experimental investigation of reduction in transonic drag rise at zero lift by the addition of volume to the fuselage of a wing-body-tail configuration and a comparison with theory

Description: "An experimental investigation was made by the free-fall recoverable-model technique to assess at zero lift the possibilities of reducing the drag-rise coefficients of a wing-body-cruciform-tail combination by adding volume to the fuselage. The basic features of the test model were an unswept aspect-ratio-3.1 thin wing, a fineness-ratio-12.4 fuselage, and four 45 degrees sweptback tail surfaces. The tests covered a Mach number range of 0.84 to 1.15 with Reynolds numbers of 6.000.000 to 14,000,0… more
Date: August 18, 1954
Creator: Holdaway, George H.
Partner: UNT Libraries Government Documents Department
open access

Rapid Estimation of Bending Frequencies of Rotating Beams

Description: Memorandum presenting a procedure in the form of charts which permits the rapid estimation of the natural bending frequencies of helicopter rotor blades, both rotating and nonrotating. An evaluation of the method with regard to such things as higher modes, blade offset, and variable mass and stiffness distributions is also given. The valuation shows that, when nonrotating beam bending modes are used, Southwell's equation yields reasonably accurate bending frequencies for rotating helicopter bla… more
Date: August 18, 1954
Creator: Yntema, Robert T.
Partner: UNT Libraries Government Documents Department
open access

Experimental Determination of Linear Dynamics of Two-Spool Turbojet Engines

Description: Transfer functions descriptive of the response of most engine variables were determined from transient data that were obtained from approximate step inputs in fuel flow and in exhaust-nozzle area. The speed responses of both spools to fuel flow and to turbine-inlet temperature appeared as identical first-order lags. Response to exhaust-nozzle area was characterized by a first-order lag response of the outer-spool speed, accompanied by virtually no change in inner-spool speed.
Date: October 18, 1954
Creator: Novik, David & Heppler, Herbert
Partner: UNT Libraries Government Documents Department
open access

Preliminary Investigation of the Static Longitudinal and Lateral Stability Characteristics of a 0.05-Scale Model of the Convair F2Y-1 Airplane at High Subsonic Speeds

Description: At the request of the Bureau of Aeronautics, Department of the Navy, National Advisory Committee for Aeronautics has conducted a preliminary investigation at high subsonic speeds of the static longitudinal and lateral stability characteristics of a 0.05-scale model of the Convair F2Y-1 water-based fighter airplane. The tests covered a Mach number range from 0.5 to 0.94 and corresponding Reynolds numbers, based on the wing mean aerodynamic chord, from 3.3 x 10(exp 6) to 4.3 x 10(exp 6). The maxi… more
Date: January 18, 1954
Creator: Spreemann, Kenneth P. & Few, Albert G., Jr.
Partner: UNT Libraries Government Documents Department
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