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- LONGITUDINAL FREQUENCY-RESPONSE CHARACTERISTICS OF THE DOUGLAS D-558-I AIRPLANE AS DETERMINED FROM EXPERIMENTAL TRANSIENT-RESPONSE HISTORIES TO A MACH NUMBER OF 0.90 , Research Memorandum
Authors: Ellwyn E. Angle and Euclid C. Holleman
Report Number: NACA-RM-L51K28
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: Transient responses from elevator pulses of the Douglas D-558-I research airplane are analyzed by the Fourier transform to give the longitudinal frequency response of the airplane to a Mach number of 0.90 at altitudes between 30,000 and 37,000 feet.
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- HANDLING QUALITIES OF HIGH-SPEED AIRPLANES , Research Memorandum
Authors: W. C. Williams and A. S. Crossfield
Report Number: NACA-RM-L52A08
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: Because there have been such drastic changes in the speed range and the configuration of airplanes in the past decade it becomes necessary to re-examine the requirements for satisfactory handling qualities as proposed by Gilruth in 1940. This paper does not attempt to describe completely the handling qualities of all the research airplanes but does attempt to describe the objectionable characteristics and those which indicate review of the requirements. The research airplanes discussed are the X-1, D-558-1, D-558-2, X-4, F-86A, and the XF-92A.
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- TIME-HISTORY DATA OF MANEUVERS PERFORMED BY A MCDONNELL F2H-2 AIRPLANE DURING SQUADRON OPERATIONAL TRAINING , Research Memorandum
Authors: Carl R. Huss, William H. Andrews and Harold A. Hamer
Report Number: NACA-RM-L52B29
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: Preliminary results of 276 maneuvers of all types performed by an F2H-2 jet fighter airplane during normal operational training are presented in time history form and are summarized as plots of load factors and angular accelerations against indicated airspeed.
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Report Date: May 1952
- LONGITUDINAL FREQUENCY-RESPONSE AND STABILITY CHARACTERISTICS OF THE DOUGLAS D-558-II AIRPLANE AS DETERMINED FROM TRANSIENT RESPONSE TO A MACH NUMBER OF 0.96 , Research Memorandum
Authors: Euclid C. Holleman
Report Number: NACA-RM-L52E02
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: By an application of the Fourier transformation to transient-flight data the longitudinal frequency response of the Douglas D-558-II airplane has been determined over a Mach number range of 0.62 to 0.96 at altitudes between 21,000 and 43,000 feet; however, the results have been reduced to airplane stability derivatives which are presented as functions of Mach number.
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Report Date: September 1952
- FLIGHT INVESTIGATION OF THE AILERON EFFECTIVENESS OF THE REPUBLIC XF-91 AIRPLANE OVER A MACH NUMBER RANGE FROM 0.40 , Research Memorandum
Authors: Thomas R. Sisk
Report Number: NACA-RM-L52E07A
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: A flight investigation has been conducted to determine the aileron effectiveness of the Republic XF-91 airplane. The tests were conducted over a Mach number range from 0.40 to 0.91 at approximate altitudes of 13,000, 24,000, and 32,000 feet.
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Report Date: September 1952
- PRELIMINARY RESULTS OF HORIZONTAL-TAIL LOAD MEASUREMENTS OF THE BELL X-5 RESEARCH AIRPLANE , Research Memorandum
Authors: John T. Rogers and Angel H. Dunn
Report Number: NACA-RM-L52G14
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: Horizontal-tail load measurements were made during the Bell acceptance tests of a transonic speed research airplane having wings variable in flight between 20 degrees and 60 degrees sweepback. Load measurements were made during sweep changes in level flight from Mach numbers of 0.5 to 0.85, and during pull-ups at a Mach number of 0.83 at sweep angles of 20 degrees, 45 degrees, and 59 degrees.
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Report Date: August 1952
- FIRST LANDING OF BELL X-2 RESEARCH AIRPLANE , Research Memorandum
Authors: Richard E. Day and Wendell H. Stillwell
Report Number: NACA-RM-L52I11
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: The Bell X-2 supersonic research airplane is equipped with a skid main landing gear and a nose wheel. Pending completion of the rocket engine, glide flights are being performed to determine low-speed handling qualities of the airplane and the landing characteristics with the ski type landing gear. The present paper presents data obtained during the approach and landing of X-2 airplane on its first flight.
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Report Date: October 1952
- MEASUREMENTS OF AERODYNAMIC HEATING OBTAINED DURING DEMONSTRATION FLIGHT TESTS OF THE DOUGLAS D-558-II AIRPLANE , Research Memorandum
Authors: Ira P. Jones, Jr.
Report Number: NACA-RM-L52I26A
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: Measurements of transient skin and canopy-glass temperature and stagnation temperature were made on the Douglas D-558-II research airplane up to a Mach number of 1.89 and to an altitude of about 77,000 feet. The maximum temperatures that were obtained for the positions measured were not great enough to cause loss in structural strength.
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Report Date: November 1952
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