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Flight measurements of the pressure distribution on the wing of the X-1 airplane (10 percent thick wing) over a chordwise station near the midspan, in level flight at Mach numbers from 0.79 to 1.00 and in a pull up at a Mach number of 0.98

Description: Report presenting measurements of chordwise pressure distribution over the 10-percent-thick wing of the X-1 research airplane at a section near the midspan of the left wing. Results regarding the upper- and lower-surface pressure distributions at a range of Mach numbers and section loads are provided.
Date: September 12, 1950
Creator: Carner, H. Arthur & Knapp, Ronald J.
Partner: UNT Libraries Government Documents Department

Investigation of a three-stage transonic research axial-flow compressor: aerodynamic design and overall performance

Description: Report discussing an investigation of the performance of a three-stage transonic compressor with high stage pressure ratios to investigate problems encountered when high-pressure-ratio transonic stages are grouped together to form a multistage compressor. Results are presented regarding overall performance in Freon, stage performance, and radial variation in overall stagnation pressure ratio.
Date: October 27, 1955
Creator: Savage, Melvyn & Beatty, Loren A.
Partner: UNT Libraries Government Documents Department

An investigation of a supersonic aircraft configuration having a tapered wing with circular-arc sections and 40 degrees sweepback: estimated downwash angles derived from pressure measurements on the tail at Mach numbers of 1.40 and 1.59

Description: Report presenting estimates of downwash angles determined from an analysis of pressures measured on the horizontal tail of a supersonic aircraft configuration. The results are compared to an approximate application of linearized theory and force-test results for the same configuration.
Date: March 10, 1952
Creator: Grant, Frederick C. & Gapcynski, John P.
Partner: UNT Libraries Government Documents Department

Flight investigation of the pressure distributions and loads on a front and rear sliding canopy

Description: From Summary: "Pressure-distribution measurements and load-coefficient data at low speeds obtained in flight for a conventional front and rear sliding canopy are presented. The load-coefficient data indicate that the highest net aerodynamic load for the front canopy was in the exploding direction and occurred with the front and rear canopies closed. The highest net load for the rear canopy was in the crushing direction with the front canopy open and the rear canopy closed."
Date: April 4, 1950
Creator: Huston, Wilber B. & Skopinski, T. H.
Partner: UNT Libraries Government Documents Department

Free-fall measurements of the effects of wing-body interference on the transonic drag characteristics of swept-wing-slender-body configurations

Description: Report presenting the results of testing of bodies and wing-body combinations by the free-fall method in order to provide information about drag characteristics of airplanes and their component parts at transonic speeds. Two models with a fineness-ratio-12 body of revolution with 45 degree sweptback wings located at different positions were dropped and equipped with improved drag measuring instrumentation and pressure measuring orifices on the portion of the body expected to be influenced by the presence of the wing. Results regarding pressure data and drag data are provided.
Date: May 28, 1953
Creator: Kurbjun, Max C. & Thompson, Jim Rogers
Partner: UNT Libraries Government Documents Department

Flight-determined pressure distributions over the wing of the Bell X-1 research airplane (10-percent-thick wing) at subsonic and transonic speeds

Description: Report presenting measurements of chordwise pressure distributions at four spanwise stations over a 10-percent-thick wing of the Bell X-1 airplane. Results regarding pressure distributions at the various stations and section aerodynamic characteristics are presented. The data was obtained for a range of Mach numbers from 0.30 to 11.9 and altitudes from 17,000 to 47,000 with several different types of maneuvers.
Date: June 29, 1953
Creator: Knapp, Ronald J. & Jordan, Gareth H.
Partner: UNT Libraries Government Documents Department

Wind-tunnel investigation of a wing-root inlet configuration with various modifications at Mach numbers of 1.41, 1.81, and 2.01

Description: Report presenting a wing-root inlet configuration with varying inlet components that were tested in the supersonic pressure tunnel at several Mach numbers, angles of attack, and sideslip angles. The intent was to determine the effects on inlet performance and engine-face total-pressure distributions of variations in these variables. Some inlet-lip stagger was found to improve pressure recoveries at high angles of attack with little to not compromise at an angle of attack of 0.
Date: September 26, 1957
Creator: Robins, A. Warner
Partner: UNT Libraries Government Documents Department

Wing-flow study of pressure-drag reduction at transonic speed by projecting a jet of air from the nose of a prolate spheroid of fineness ratio 6

Description: Report presenting a study of the pressure-drag reduction obtained by projecting a high-energy jet of air from the nose of a prolate spheroid at transonic speeds. Results regarding the pressure distribution on the body, pressure drag, shadowgraphs, and some notes regarding the slope of the body and level of shear at the jet exit are provided.
Date: October 26, 1951
Creator: Lopatoff, Mitchell
Partner: UNT Libraries Government Documents Department

Transonic wind-tunnel investigation of static-pressure fluctuations in duct of a scale inlet model of a supersonic fighter-bomber airplane

Description: Report presenting a transonic investigation of the static-pressure fluctuations in the left duct of a scale inlet model of a supersonic fighter-bomber airplane. The amplitude and frequency of pressure fluctuations were measured using an electrical pressure gage mounted on the diffuser wall at several Mach numbers and mass-flow ratios. Results regarding amplitude characteristics of pressure fluctuations, power-spectral analyses, and flow distortions at compressor face are provided.
Date: August 6, 1957
Creator: Brooks, Joseph D.
Partner: UNT Libraries Government Documents Department

Flight-determined pressure measurements over the wing of the Douglas D-558-II research airplane at Mach numbers up to 1.14

Description: Report presenting an investigation of the section and panel characteristics and loads obtained from pressure measurements over a 35 degree sweptback wing at level-flight lifts for a range of Mach numbers. Section pressure distributions were taken at the root, midspan, and tip stations of a Douglas D-558-II airplane.
Date: March 12, 1954
Creator: Peele, James R.
Partner: UNT Libraries Government Documents Department

Performance at Mach numbers 3.07, 1.89, and 0 of inlets designed for inlet-engine matching up to Mach 3

Description: Report presenting performance of a two-dimensional external-compression inlet designed for various methods of inlet-engine matching up to Mach 3 at Mach 1.89 and Mach 0. Results regarding shock geometry, two-shock ramps, isentropic ramps, profiles, and cowl drag for the various Mach number tests are provided.
Date: May 20, 1958
Creator: Gertsma, L. W. & Beheim, M. A.
Partner: UNT Libraries Government Documents Department