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Flight Measurements of the Stability Characteristics of the Bell X-5 Research Airplane in Sideslips at 59 Deg Sweepback

Description: Flight measurements of the stability characteristics of the Bell X-5 research airplane at 59 deg sweepback were made in steady sideslips at Mach numbers from 0.62 to 0.97 at altitudes ranging between 35,000 and 40,000 feet. The results showed that the apparent directional stability was positive and increased at Mach numbers above 0.90. The apparent effective dihedral was positive and high, increasing at Mach numbers above 0.75. The cross-wind force coefficient per degree of sideslip was positive and increased rapidly at Mach numbers above 0.94.
Date: February 11, 1953
Creator: Childs, Joan M
Partner: UNT Libraries Government Documents Department

Preliminary Results of Stability and Control Investigation of the Bell X-5 Research Airplane

Description: During the acceptance tests of the Bell X-5 airplane, measurements of the static stability and control characteristics and horizontal-tail loads were obtained by the NACA High-Speed Flight Research Station. The results of the stability and control measurements are presented in this paper. A change in sweep angle between 20 deg and 59 deg had a minor effect on the longitudinal trim, with a maximum change of about 2.5 deg in elevator deflection being required at a Mach number near 0.85; however, sweeping the wings produced a total stick-force change of about 40 pounds.
Date: February 11, 1953
Creator: Finch, Thomas W. & Briggs, Donald W.
Partner: UNT Libraries Government Documents Department

Comparison of measured and predicted indicated angles of attack near the fuselages of a triangular-wing wind-tunnel model and a swept-wing fighter airplane in flight

Description: Report presenting measurements of the local flow angles near the fuselages of a triangular-wing wind-tunnel model and an F-86A-5 airplane in flight using airflow detectors on the fuselages. A comparison of the measured and predicted flow angles is provided. Results indicated that the accuracy of the predicted indicated angles of attack was not sufficient to eliminate the necessity of a flight calibration of a detector mounted on a fuselage.
Date: March 11, 1953
Creator: McFadden, Norman M.; McCloud, John L., III & James, Harry A.
Partner: UNT Libraries Government Documents Department

Investigation at transonic speeds of aerodynamic characteristics of a semielliptical air inlet in the root of a 45 degree sweptback wing

Description: Report presenting an investigation in the transonic blowdown tunnel at a range of Mach numbers to determine the increments in lift, drag, and pitching moments due to the installation of a semielliptical-shaped air inlet in the root of a 45 degree sweptback wing and to study the internal flow characteristics of the inlet. Results regarding the internal pressure measurements, effect of inlet installation on external aerodynamic characteristics, effect of boundary-layer removal on internal pressure recovery, and inlet performance are provided.
Date: December 11, 1953
Creator: Howell, Robert R. & Trescot, Charles D., Jr.
Partner: UNT Libraries Government Documents Department

Wind-tunnel oscillation tests of the Bendix-Friez aerovane anemometer

Description: Report presenting a Bendix-Friez Aerovane Anenometer oscillated in the streamwise direction at several frequencies for each of several low wind-tunnel airspeeds. Records of the displacement of the anenometer and velocity indicated by the instrument during oscillation are provided. The over-registration of this anenometer was found to be much smaller than predicted by theory.
Date: August 11, 1953
Creator: Fisher, Lewis R.
Partner: UNT Libraries Government Documents Department

Smoke studies of secondary flows in bends, tandem cascades, and high-turning configurations

Description: Flow-visualization studies, using smoke, were made of the secondary flows in rectangular bends, tandem cascades, and high-turning configurations. The roll-up of the wall boundary layer of a rectangular bend forms a passage vortex near the suction surface similar to that previously observed for cascades. The vortex so formed then shifts out into the main stream. Because of leading-edge effects, the boundary-layer flows in bends were found to be sufficiently different from the flows in blade rows to make direct application of bend results to blade rows inadvisable.
Date: March 11, 1953
Creator: Hansen, Arthur G.; Herzig, Howard Z. & Costello, George R.
Partner: UNT Libraries Government Documents Department

Experimental investigation of an axial-flow supersonic compressor having rounded leading-edge blades with an 8-percent mean thickness-chord ratio

Description: Report presenting testing of supersonic compressor blades with rounded leading edges with an 8-percent mean thickness-chord ratio and a solidity of about 2.5 were incorporated in a 16-inch-diameter rotor with and without guide vanes. Results regarding the overall performance, rotor-blade-element performance, and rotor without guide vanes are provided.
Date: December 11, 1953
Creator: Goldberg, Theodore J.; Boxer, Emanuel & Bernot, Peter T.
Partner: UNT Libraries Government Documents Department

A transonic investigation by the free-fall method of an airplane configuration having 45 degrees sweptback wing and tail surfaces

Description: Report presenting a free-fall investigation of airplanes in the transonic range using a configuration with 45 degree sweptback wing and tail surfaces. The lift, drag, and longitudinal static and dynamic stability and control characteristics were obtained at a range of operating lift coefficients and Mach numbers.
Date: June 11, 1953
Creator: Faber, Stanley & Eggleston, John M.
Partner: UNT Libraries Government Documents Department

Utilization of external-compression diffusion principle in design of shock-in-rotor supersonic compressor blading

Description: Report presenting the application of the external-compression principle to a cascade of blades in an attempt to achieve a closer approach to isentropic contraction ratios in supersonic compressor blading. Tests of a rotor designed to incorporate the external-compression principle are provided. Results regarding overall performance, performance at design speed and peak efficiency, off-design performance, and some considerations for future designs are provided.
Date: September 11, 1953
Creator: Creagh, John W. R. & Klapproth, John F.
Partner: UNT Libraries Government Documents Department

An investigation of continuous boundary-layer removal in an axial flow compressor with porous walls

Description: Report presenting an investigation made to improve compressor performance by bleedoff of detrimental boundary layer through a porous compressor casing. The results were compared to the performance characteristics of the original engine. Bleedoff was found to increase the efficiency of the compression process, but the overall performance of the turbojet suffered.
Date: December 11, 1953
Creator: Wlodarski, John
Partner: UNT Libraries Government Documents Department

Experimental investigation of the zero-lift drag of a fin-stabilized body of fineness ratio 10 at Mach numbers between 0.6 and 10

Description: Report presenting free-flight measurements of the zero-lift drag of a cruciform-finned body at a range of Mach and Reynolds numbers. Results regarding experimental total drag, comparison of theory with experiment, comparison of experiment with NOL results, boundary-layer transition, Reynolds number effects, and fin leading-edge shape are provided.
Date: June 11, 1953
Creator: James, Carlton S. & Carros, Robert J.
Partner: UNT Libraries Government Documents Department

Wind-tunnel investigation of stall control by suction through a porous leading edge on a 37 degree sweptback wing of aspect ratio 6 at Reynolds numbers from 2.50 x 10(exp 6) to 8.10 x 10(exp 6)

Description: Report presenting an investigation of the effects of suction through a porous leading-edge surface in the 19-foot pressure tunnel on a wing with 37 degrees of sweepback of the leading edge, an aspect ratio of 6, taper ratio of 0.5, and NACA 64(sub 1)-212 airfoil sections normal to the 27-percent-chord line. Results regarding the wing without flaps, wing with trailing-edge flaps, and power requirements for porous-leading-edge suction are provided.
Date: March 11, 1953
Creator: Graham, Robert R. & Jacques, William A.
Partner: UNT Libraries Government Documents Department

Wind-Tunnel Investigation at Low Speed of the Static Longitudinal and Lateral Stability Characteristics of a 1/9-Scale Powered Model of the Convair XFY-1 Vertically Rising Airplane

Description: An experimental investigation has been made in the Langley stability tunnel at low speed to determine the static longitudinal and lateral stability characteristics of a l/9-scale powered model of the Convair XFY-1 vertically rising airplane. Effects of thrust coefficient were investigated for the complete model and for certain components of the model. Effects of control deflections and of propeller-blade angle were investigated briefly for the complete model. Most of the tests were made through an angle-of-attack range from about -4 deg. to 29 deg, and the thrust-coefficient range was from 0 t o 0.7. In order to expedite distribution of these data to interested persons, no analysis of the data has been prepared for this report,.
Date: February 11, 1953
Creator: Queijo, M. J.; Wolhart, W. D. & Fletcher, H. S.
Partner: UNT Libraries Government Documents Department

Flow Coefficients for Orifices in Base of Transpiration-Cooled Turbine Rotor Blade

Description: Static tests on a segment of a transpiration-cooled turbine rotor blade with a wire-cloth shell were conducted to determine the flow coefficients associated with some representative metering orifices. Average flow coefficients from 0.96 to 0.79 were obtained for orifices of 0.031 to 0.102 inch diameter.
Date: December 11, 1953
Creator: Donoughe, Patrick L. & Prasse, Ernst I.
Partner: UNT Libraries Government Documents Department

Drag and static stability at low lift of rocket-powered models of the Convair MX-1626 airplane at Mach numbers from 0.7 to 1.5

Description: Report presenting flight testing on models of the proposed Consolidated Vultee Aircraft Corporation MX-1626 airplane with nacelles and without nacelles. Results regarding drag level, design modifications, dampening, trimming, and the use of ventral boosters are provided.
Date: June 11, 1953
Creator: Hall, James R. & Hopko, Russell N.
Partner: UNT Libraries Government Documents Department