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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

Analysis of off-design operation of high Mach number supersonic turbojet engines

Description: From Introduction: "Because of the lack of data on compressor characteristics at 130 or 145 percent of design equivalent rotational speed, several simplifying assumptions were made regarding the compressor characteristics during operation at equivalent rotational speeds above the design value (hereinafter called "compressor overspeeding"). In addition to results based on these assumptions, the effect of deviation from these assumptions is discussed."
Date: February 4, 1954
Creator: English, Robert E & Cavicchi, Richard H
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

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

Investigation of turbines suitable for use in a turbojet engine with high compressor pressure ratio and low compressor-tip speed 1: turbine-design requirements for several engine operating conditions

Description: In order to insure satisfactory turbine performance under five turbojet-engine operating conditions, turbine design requirements were determined for the following operating conditions: take-off, maximum thrust at altitude, altitude cruising at rated rotative speed, altitude cruising with maximum-thrust exhaust nozzle area, and engine acceleration at 80 percent equivalent design rotative speed. If cruising is to be at rated engine speed, both cruising and take-off should be considered in turbine design. Design requirements for the other conditions are nearly identical. Without compressor-exit bleed, a turbine cannot accelerate this compressor at 80 percent of rated speed; with 28.6-percent bleed, the design requirements are within those for take-off.
Date: March 4, 1952
Creator: English, Robert E.; Silvern, David H. & Davison, Elmer H.
Partner: UNT Libraries Government Documents Department

The effects of a modified roll-command system on the flight-path stability and tracking accuracy of an automatic interceptor

Description: From Summary: "In order to improve the tracking characteristics of an automatic interceptor, a revised roll-command computer was tested both on an analog computer and in flight. This report presents flight-test results which indicate a significant improvement in flight-path stability and tracking accuracy. The modified roll computer was designed on the basis of previous analytical studies."
Date: March 4, 1958
Creator: Triplett, William C.
Partner: UNT Libraries Government Documents Department