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Effects on control effectiveness of systematically varying the size and location of trailing-edge flaps on a 45 degrees sweptback wing at a Mach number of 1.9

Description: Report presenting the effect of control effectiveness of systematically varying the size and location of trailing-edge flaps on a 45 degree sweptback wing at a Mach number of 1.9. The wing model had an aspect ratio of 2.5, a taper ratio of 0.625, and 6-percent-thick hexagonal airfoil sections. Results regarding the rolling-moment and yawing-moment coefficients, lift, rolling-moment, and pitching-moment effectiveness parameters, and flap characteristics are provided.
Date: December 4, 1951
Creator: Jacobsen, Carl R.
Partner: UNT Libraries Government Documents Department

Investigation of turbines for driving supersonic compressors 5: design and performance of third configuration with nontwisted rotor blades

Description: Report presenting the design and performance of a turbine with nontwisted rotor blades designed to drive a high-speed, high-specific-mass-flow supersonic compressor. Results regarding turbine performance, entrance Mach number, radial temperature surveys, and loading are provided.
Date: September 4, 1953
Creator: Whitney, Warren J.; Stewart, Warner L. & Monroe, Daniel E.
Partner: UNT Libraries Government Documents Department

The use of a leading-edge area-suction flap and leading-edge modifications to improve the high-lift characteristics of an airplane model with a wing of 45 degree sweep and aspect ratio 2.8

Description: Report presenting an investigation on an airplane model with drooped horizontal tail and a highly tapered wing of aspect ratio 2.8 and 45 degrees of sweep. The primary purpose of the investigation was to determine what improvements in the control of leading-edge stall would be possible with the use of area suction on a leading-edge flap and with the leading-edge flap used with a modified or bulbous leading edge and chord extension.
Date: November 4, 1957
Creator: Koenig, David G. & Aoyagi, Kiyoshi
Partner: UNT Libraries Government Documents Department

Preliminary flight measurements of the total-pressure recovery of a split-wing ram-jet inlet at Mach numbers from 1.4 to 3.16

Description: Report presenting flight tests to determine the total-pressure recovery of a split-wing ram-jet inlet with a fixed area exit 20 percent larger than the inlet throat over a range of Mach numbers. Total-pressure-recovery measurements at the diffuser exit station indicated abrupt pressure changes in the total-pressure profile throughout the Mach number range.
Date: March 4, 1954
Creator: Hinners, Arthur H., Jr.
Partner: UNT Libraries Government Documents Department

Preliminary drag measurements of the consolidated Vultee XF-92A delta-wing airplane in flight tests to a Mach number of 1.01

Description: Report presenting preliminary drag data obtained for the XF-92A delta wing airplane during demonstration tests after it had been modified to use the J33-A-29 turbojet engine. Drag data, lift coefficients, and lift-curve slopes are provided.
Date: January 4, 1954
Creator: Bellman, Donald R. & Sisk, Thomas R.
Partner: UNT Libraries Government Documents Department

Pressure distribution at low speed on a 1/4-scale Bell X-5 airplane model

Description: From Summary: "This paper contains the results of measurements at 20 degrees and 60 degrees wing sweep of the low-speed pressure distribution on the wing, wing slat, wing leading-edge fillet, and fuselage of a 1/4-scale model of a preliminary Bell X-5 airplane design. The pressure-distribution measurements were made to obtain specific aerodynamic load information for application to the Bell X-5 airplane. Some of the results, however, are useful for application to swept-wing airplanes in general."
Date: December 4, 1951
Creator: Kemp, William B., Jr. & Few, Albert G., Jr.
Partner: UNT Libraries Government Documents Department

Buffeting forces on two-dimensional airfoils as affected by thickness and thickness distribution

Description: Report presenting an experimental investigation to determine the effect of thickness and of thickness distribution on the fluctuations of normal-force and pitching-moment coefficients of airfoils. Seven symmetrical airfoils were tested. Two types of pressure pulsations were noted in the study: pulsations from an intermittent build-up and dropping of the pressure peak near the leading edge and pulsations attributable to shock-wave motion and unsteady air flow following the shock wave.
Date: February 4, 1954
Creator: Coe, Charles F. & Mellenthin, Jack A.
Partner: UNT Libraries Government Documents Department

The calculated and experimental incremental loads and moments produced by split flaps of various spans and spanwise locations on a 45 degrees sweptback wing of aspect ratio 8

Description: Report presenting the incremental lift and pitching moments produced by 20-percent-chord split flaps of various spans at various spanwise positions on two 45 degree sweptback wings of aspect ratio 8.02 as obtained by pressure-distribution testing. Inboard flaps were found to be far more effective in producing lift than outboard flaps. Results regarding spanwise loading and pitching moment are provided.
Date: September 4, 1953
Creator: Kelly, H. Neale
Partner: UNT Libraries Government Documents Department

Analysis of part-speed operation for high-pressure-ratio multistage axial-flow compressors

Description: From Introduction: "For the analysis reported herein, the same hypothetical 12-stage compressor discussed in reference 6 was chosen, and the effects of inlet-stage stall characteristics and stage interactions were estimated by arbitrary adjustment of the stall characteristics and stage interactions were estimated by arbitrary adjustment of the stalled characteristics of the individual stages."
Date: December 4, 1953
Creator: Benser, William A.
Partner: UNT Libraries Government Documents Department

Effects of increasing Reynolds number from 2 x 10(exp 6) to 6 x 10(exp 6) on the aerodynamic characteristics at transonic speeds of a 45 degree swept wing with 6 degree leading-edge droop

Description: Report presenting an investigation in the 16-foot and 8-foot transonic tunnel to determine the effects of Reynolds number and on a swept wing with camber. The wing had 45 degrees sweepback of the quarter-chord line, an aspect ratio of 4, a taper ratio of 0.6, and NACA 65A006 airfoil sections parallel to the plane of symmetry. Results regarding the effect of Reynolds number on the aerodynamic characteristics and effects of roughness strips are provided.
Date: February 4, 1955
Creator: Schmeer, James W. & Cooper, J. Lawrence
Partner: UNT Libraries Government Documents Department

Experimental determination of gas motion accompanying screeching combustion in a 6-inch simulated afterburner

Description: Report presenting an investigation to develop screech instrumentation and study the mechanism of screech in a simulated afterburner. Results regarding the screech mechanism, effect of system variables on screech, speculation regarding screech mechanism, and suggested techniques for elimination or control of screech are provided.
Date: December 4, 1953
Creator: Blackshear, Perry L.; Rayle, Warren D. & Tower, Leonard K.
Partner: UNT Libraries Government Documents Department

Static stability and control of canard configurations at Mach numbers from 0.70 to 2.22: lateral-directional characteristics of a triangular wing and canard

Description: Report presenting the results of an investigation of the static lateral-directional stability characteristics of a canard airplane configuration without analysis for a range of Mach numbers. Data are presented for various combinations of the canard, body, wing, and vertical tail. Data were obtained at a variety of angles of attack, sideslip angles, and canard angles.
Date: March 4, 1958
Creator: Peterson, Victor L. & Menees, Gene P.
Partner: UNT Libraries Government Documents Department

Static shear strength of 2117-T4 (A17S-T4) aluminum-alloy rivets at elevated temperatures

Description: Report presenting static single shear tests of 3/16-inch-diameter 2117-T4 (A17S-T4) aluminum-alloy rivets at elevated temperatures. The maximum temperature tested was 800 degrees Fahrenheit and the time at temperature prior to testing range from 1/2 hour to 720 hours.
Date: January 4, 1956
Creator: Dewalt, W. J. & Bogardus, K. O.
Partner: UNT Libraries Government Documents Department

Wing loads on the Bell X-1 research airplane (10 percent thick wing) as determined by pressure-distribution measurements in flight at subsonic and transonic speeds

Description: Report presenting measurements of wing loads made on the left wing of the Bell X-1 research airplane. Data are presented within a wing-panel normal-force coefficient and Mach number range. Results regarding span load distributions, wing-panel aerodynamic characteristics, and wing-to-fuselage carry over are provided.
Date: November 4, 1953
Creator: Knapp, Ronald J. & Jordan, Gareth H.
Partner: UNT Libraries Government Documents Department

Investigation of low-pressure performance of experimental tubular combustors differing in air-entry-hole geometry

Description: Report presenting an investigation to determine, by experiments within the scope of air-entry-hole geometry, design criteria for tubular combustors with good low-pressure performance. Combustion efficiency, operable fuel-air-ratio and pressure ranges, and minimum ignition pressures were determined for several combustor configurations at conditions simulating a 5.2-pressure-ratio turbojet engine operating at 85 percent of rated rotor speed, a flight Mach number of 0.6, and altitudes from 56,000 to 80,000 feet.
Date: September 4, 1953
Creator: Dittrich, Ralph T.
Partner: UNT Libraries Government Documents Department

A wind-tunnel investigation of the aerodynamic characteristics of a full-scale sweptback propeller and two related straight propellers

Description: Report presenting an investigation of an NACA 10-(1.7)(062)-057-27 two-blade swept propeller was conducted int he 16-foot high-speed tunnel over a range of blade-angle settings. Two related straight propellers were also tested over the same operating range as the swept propeller. Results regarding envelope efficiency, effect of compressibility on maximum efficiency, effect of sweep on power coefficient, constant-power propeller operation, and effect of sweep on propeller-blade loading are provided.
Date: January 4, 1951
Creator: Evans, Albert J. & Liner, George
Partner: UNT Libraries Government Documents Department

Experimental investigation of screeching combustion in full-scale afterburner

Description: Report presenting an investigation using a number of systematic configuration modifications to an afterburner to determine their effect on screech characteristics. The modifications included changes in the afterburner diffuser, the fuel system, and the flame holder. Results regarding some of the characteristics of screeching combustion, effect of diffuser flow conditions, and effect of fuel system and flame holder are provided.
Date: December 4, 1953
Creator: Usow, Karl H.; Meyer, Carl L. & Schulze, Frederick W.
Partner: UNT Libraries Government Documents Department

Flight investigation of the low-speed characteristics of a 45 degree swept-wing fighter-type airplane with blowing boundary-layer control applied to the trailing edge flaps

Description: Report presenting a flight investigation to determine the low-speed flight characteristics of a 45 degree swept-wing fighter-type airplane with boundary-layer control on the trailing-edge flaps. The effectiveness of the flap with and without boundary-layer control was determined in conjunction with several slat modifications. The study also included low-speed flying qualities and a pilot evaluation of the operational use of the boundary-layer control system in landing approaches.
Date: August 4, 1958
Creator: Quigley, Hervey C.; Anderson, Seth B. & Innis, Robert C.
Partner: UNT Libraries Government Documents Department

Static lateral-directional stability characteristics of five contemporary airplane models from wind-tunnel tests at high subsonic and supersonic speeds

Description: Report presenting the static lateral-directional stability characteristics of several airplane models that cover many of the geometric arrangements of high-speed airplane components of current interest. The results are presented for a subsonic Mach number of 0.9 and for supersonic Mach numbers ranging from 1.2 to 1.9. Five different models are described and tested.
Date: January 4, 1956
Creator: Smith, Willard G. & Ball, Louis H.
Partner: UNT Libraries Government Documents Department

Study of exit phase of flight of a very high altitude hypersonic airplane by means of a pilot-controlled analog computer

Description: Report using an analog computer to study the effects of aerodynamic parameters on the ability of a pilot to control a hypersonic research airplane capable of flight at very high altitudes. The results, which are based on pilot opinion of the difficulty of the control task, are illustrated by time histories of angle of attack, angle of sideslip, and roll angle. The basic airplane configuration was generally found to be unflyable and the arrangement of the information on the pilot's display was found to have an important influence on the control task.
Date: March 4, 1958
Creator: Sherman, Windsor L.; Faber, Stanley & Whitten, James B.
Partner: UNT Libraries Government Documents Department

Inlet-air distortion effects on stall, surge, and acceleration margin of a turbojet engine equipped with variable compressor inlet guide vanes

Description: Report presenting an investigation of a turbojet engine in an altitude test chamber to determine the effects of a wide range of uneven inlet-air pressure distributions on transient characteristics and stall phenomenon. Circumferential, radial, and mixed pressure variations were run at three simulated altitudes and a simulated Mach number of 0.80. Results regarding the compressor characteristics, compressor stage performance, and acceleration margin are provided.
Date: October 4, 1955
Creator: Harry, David P., III & Lubick, Robert J.
Partner: UNT Libraries Government Documents Department

Investigation of a High-Pressure-Ratio Eight-Stage Axial-Flow Research Compressor With Two Transonic Inlet Stages 1: Aerodynamic Design

Description: Memorandum presenting an eight-stage high-pressure-ratio axial-flow compressor designed for use as a research unit in which the problems associated with design and off-design performance of transonic stages combined with highly loaded subsonic stages could be studied. The report discusses the design procedure and presents the experimentally determined overall performance of the compressor.
Date: December 4, 1953
Creator: Voit, Charles H.
Partner: UNT Libraries Government Documents Department

Evaluation of a silicone-diester lubricant in bench studies and in a turbopropeller engine

Description: Report presenting an investigation of a silicone-diester blend (SD-17) in various bench studies and in a turbopropeller engine to determine its suitability as a lubricant for aircraft engines. The performance of the fluid was satisfactory during more than 17 hours of operation in a T-38 engine with power levels from 1745 to 2400 horsepower. Results regarding bench studies and turbopropeller engine study are provided.
Date: May 4, 1954
Creator: Johnson, Robert L.; Murray, S. F. & Bisson, Edmund E.
Partner: UNT Libraries Government Documents Department

Free-flight zero-lift drag-rise measurements of equivalent bodies of revolution of several versions of the Douglas XF4D-1 airplane at transonic speeds: TED No. NACA AD 394

Description: From Summary: "Free-flight tests have been conducted with small equivalent bodies of revolution representing different versions of the Douglas XF4D-1 airplane to determine the reduction in drag that would result from various modifications to the airplane. Results indicated that, at Mach numbers greater than 1, considerable reduction in drag would result from a thinner wing and tail, a reduction in wing-fillet thickness, and modified forward and rearward fuselage lines."
Date: November 4, 1954
Creator: Mitcham, Grady L.
Partner: UNT Libraries Government Documents Department