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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 compared with the buffet intensity-lift variation at subsonic Mach numbers."
Date: February 18, 1954
Creator: Baker, Thomas F.
Partner: UNT Libraries Government Documents Department

Some measurements of the buffet region of a swept-wing research airplane during flight to supersonic Mach numbers

Description: Report presenting measurements of the intensity of buffeting experienced by the Douglas D-558-II research airplane at a range of Mach numbers. Buffeting was encountered at both subsonic and supersonic Mach numbers and the intensity of the buffeting varied with Mach number and airplane normal-force coefficient.
Date: May 28, 1953
Creator: Baker, Thomas F.
Partner: UNT Libraries Government Documents Department

Some measurements of buffeting encountered by Douglas D-558-II research airplane in the Mach number range from 0.5 to 0.95

Description: Report presenting a flight investigation of the variation of the intensity of buffeting with lift and Mach number using a Douglas D-558-II research airplane over a range of Mach numbers and altitudes. Buffeting was encountered during flight at all Mach numbers attained and during level flight at Mach numbers above 0.9. Results regarding the relationship between lift, angle of attack, and buffeting, buffet frequencies, and intensity of buffeting are provided.
Date: November 20, 1953
Creator: Baker, Thomas F.
Partner: UNT Libraries Government Documents Department

Results of measurements of maximum lift and buffeting intensities obtained during flight investigation of the Northrop X-4 research airplane

Description: The variation of the intensity of buffeting experienced throughout the operational region of the semitailless Northrop X-4 airplane and the values of maximum and peak normal-force coefficients in the Mach number range from 0.42 to 0.92 have been determined. The results are compared with data obtained with the swept-wing Douglas D-558-II airplane.
Date: August 20, 1953
Creator: Baker, Thomas F.
Partner: UNT Libraries Government Documents Department

Flight measurements at transonic speeds of the buffeting characteristics of the XF-92A delta-wing research airplane

Description: Report presenting testing on a 60 degree delta-wing XF-92A airplane at a variety of Mach numbers to obtain measurements regarding buffet-induced fluctuations in normal acceleration and of fluctuations in structural shear load of the left wing. The altitudes tested ranged from 25,000 to 38,000 feet. Results regarding the buffet boundary, wing flow conditions, buffet frequencies, buffet intensities, and a comparison to buffeting of other airplanes are provided.
Date: April 28, 1955
Creator: Baker, Thomas F. & Johnson, Wallace E.
Partner: UNT Libraries Government Documents Department

A Study of the Correlation Between Flight and Wind-Tunnel Buffeting Loads

Description: Report presenting a comparison of the buffet loads measured on wind-tunnel models with loads measured in flight, which indicate that a simple strain-gage measurement can be used in wind tunnel testing that can be used to predict the wing buffet loads on the airplane. The technique appears to be usable for both unswept and swept configurations.
Date: July 19, 1955
Creator: Huston, Wilber B.; Rainey, A. Gerald & Baker, Thomas F.
Partner: UNT Libraries Government Documents Department

Flight data pertinent to buffeting and maximum normal-force coefficient of the Douglas X-3 research airplane

Description: Report presenting the X-3 airplane, which has a straight 4.5-percent-thick wing of modified hexagonal section, which has been flown to maximum wing normal-force coefficients in the Mach number range from 0.7 to 1.1 at an average altitude of 30,000 feet. Measurements were made of airplane and wing-panel maximum normal-force coefficients and of some buffeting characteristics.
Date: November 20, 1957
Creator: Baker, Thomas F.; Martin, James A. & Scott, Betty J.
Partner: UNT Libraries Government Documents Department