Dryden Technical Report Server
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- STABILITY AND CONTROL MEASUREMENTS OBTAINED DURING USAF-NACA COOPERATIVE FLIGHT-TEST PROGRAM ON THE X-4 AIRPLANE (USAF NO. 46-677) , Research Memorandum
Authors: Melvin Sadoff, Herman O. Ankenbruck and William O’Hare
Report Number: NACA-RM-A51H09
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: Results obtained during the Air Force testing of the Northrop X-4 airplane are presented. Information is included on the stalling characteristics, the static and dynamic longitudinal- and lateral-stability characteristics, and the lateral-control characteristics. The data indicated that the stalling characteristics of the X-4 airplane in straight flight and in accelerated flight at low Mach numbers were satisfactory, but that at Mach numbers above 0.68, the airplane became longitudinally unstable at moderate lift coefficients.
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Report Date: October 1951
- FLIGHT MEASUREMENTS WITH THE DOUGLAS D-558-II (BUAERO NO. 37974) RESEARCH AIRPLANE: STATIC LONGITUDINAL STABILITY AND CONTROL CHARACTERISTICS AT MACH NUMBERS UP TO 0.87 , Research Memorandum
Authors: S. A. Sjoberg, James R. Peele and John H. Griffith
Report Number: NACA-RM-L50K13
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: The paper presents the results of flight measurements of the longitudinal stability and control characteristics of the Douglas D-558-II research airplane. Data are presented in the speed range from the stalling speed of the airplane up to a maximum Mach number of 0.87.
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Report Date: January 1951
- FLIGHT DETERMINATION OF THE EFFECTS OF WING VORTEX GENERATORS ON THE AERODYNAMIC CHARACTERISTICS OF THE DOUGLAS D-558-I AIRPLANE , Research Memorandum
Authors: De E. Beeler, Donald R. Bellman and John H. Griffith
Report Number: NACA-RM-L51A23
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: Tests were made to determine the effects of wing vortex generators on the handling and buffeting characteristics of the Douglas D-558-I airplane. Measurements of the chordwise pressure distribution over one section of the wing, the total-head losses in a portion of the wing wake, the total airplane drag, and the buffeting and handling characteristics were made with the basic configuration and with vortex generators of an arbitrary size, shape, and location installed on the wing.
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Report Date: August 1951
- TABULATED PRESSURE COEFFICIENTS AND AERODYNAMIC CHARACTERISTICS MEASURED ON THE WING OF THE BELL X-1 AIRPLANE IN AN UNACCELERATED STALL AND IN PULL-UPS AT MACH NUMBERS OF 0.74, 0.75, 0.94, AND 0.97 , Research Memorandum
Authors: Lawrence A. Smith
Report Number: NACA-RM-L51B23
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: Presents tabulated pressure coefficients and aerodynamic characteristics measured on the wing of the Bell X-1 research airplane in an unaccelerated stall and in pull-ups at Mach numbers of approximately 0.74, 0.75, 0.94, and 0.97.
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Report Date: June 1951
- FLIGHT MEASUREMENTS WITH THE DOUGLAS D-558-II (BUAERO NO. 37974) RESEARCH AIRPLANE: DYNAMIC LATERAL STABILITY , Research Memorandum
Authors: W. H. Stillwell and J. V. Wilmerding
Report Number: NACA-RM-L51C23
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: The paper presents flight measurements of the dynamic lateral stability of the D-558-II (BuAero No. 37974) research airplane. Data are presented for a range of calibrated airspeed from 167 miles per hour to 474 miles per hour.
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Report Date: June 1951
- FLIGHT INVESTIGATION OF THE LONGITUDINAL STABILITY AND CONTROL CHARACTERISTICS OF THE DOUGLAS D-558-I AIRPLANE (BUAERO NO. 37972) AT MACH NUMBERS UP TO 0.89 , Research Memorandum
Authors: Mrlvin Sadoff, William S. Roden and John M. Eggleston
Report Number: NACA-RM-L51D18
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: Results and analysis pertaining to the longitudinal stability and control characteristics of the Douglas D-558-I airplane (BuAero No. 37972) are presented. The results indicated that large and rapid changes in elevator deflection and force were required for balance above a Mach number of 0.84. Analysis indicated that a major part of these changes were due to a loss in elevator effectiveness. A large increase in the apparent stick-fixed stability parameter d delta (sub) e/dC (sub) N was also noted due to a loss in elevator effectiveness combined with an increase in airplane stability.
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Report Date: June 1951
- LIFT AND DRAG COEFFICIENTS FOR THE BELL X-1 AIRPLANE (8-PERCENT-THICK WING) IN POWER-OFF TRANSONIC FLIGHT
Authors: L. Robert Carman and John R. Carden
Report Number: NACA-RM-L51E08
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: Drag coefficients have been determined by the accelerometer method for the Bell X-1 airplane with 8-percent-thick wing and 6-percent-thick tail in power-off flight over a Mach number range of 0.64 to 1.14 and at lift coefficients from 0.1 to 1.2.
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Report Date: June 1951
- TABULATED PRESSURE COEFFICIENTS AND AERODYNAMIC CHARACTERISTICS MEASURED IN FLIGHT ON THE WING OF THE D-558-I RESEARCH AIRPLANE THROUGH A MACH NUMBER RANGE OF 0.80 TO 0.89 AND THROUGHOUT THE NORMAL-FORCE-COEFFICIENT RANGE AT MACH NUMBERS OF 0.61, 0.70, 0. , Research Memorandum
Authors: Earl R. Keener and Rozalia M. Bandish
Report Number: NACA-RM-L51F12
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: Presents tabulated pressure coefficients and aerodynamic characteristics obtained in flight from pressure distributions over six chordwise rows of orifices on a wing of the Douglas D-558-I research airplane (BuAero No. 37972). It includes data obtained throughout a Mach number range of 0.80 to 0.89 and throughout the normal-force-coefficient range at M = 0.61, 0.70, 0.855, and 0.88.
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Report Date: August 1951
- TABULATED PRESSURE COEFFICIENTS AND AERODYNAMIC CHARACTERISTICS MEASURED ON THE WING OF THE BELL X-1 AIRPLANE IN AN UNACCELERATED LOW-SPEED STALL, IN PUSH-OVERS AT MACH NUMBERS OF 0.83 AND 0.99, AND IN A PULL-UP AT A MACH NUMBER OF 1.16 , Research Memorandum
Authors: Ronald J. Knapp
Report Number: NACA-RM-L51F24
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: Presents tabulated pressure coefficients and aerodynamic characteristics measured on the wing of the Bell X-1 research airplane in an unaccelerated low-speed stall, in push-overs at Mach numbers of 0.83 and 0.99, and in a pull-up at a Mach number of 1.16.
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Report Date: September 1951
- TABULATED PRESSURE COEFFICIENTS AND AERODYNAMIC CHARACTERISTICS MEASURED ON THE WING OF THE BELL X-1 AIRPLANE IN AN UNACCELERATED LOW-SPEED STALL, IN PUSH-OVERS AT MACH NUMBERS OF 0.83 AND 0.99, AND IN A PULL-UP AT A MACH NUMBER OF 1.16 , Research Memorandum
Authors: Ronald J. Knapp
Report Number: NACA-RM-L51F25
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: Presents tabulated pressure coefficients and aerodynamic characteristics measured on the wing of the Bell X-1 research airplane in an unaccelerated low-speed stall, in push-overs at Mach numbers of 0.83 and 0.99, and in a pull-up at a Mach number of 1.16.
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Report Date: September 1951
- ANALYSIS OF LONGITUDINAL STABILITY AND TRIM OF THE BELL X-1 AIRPLANE AT A LIFT COEFFICIENT OF 0.3 TO MACH NUMBERS NEAR 1.05 , Research Memorandum
Authors: Hubert M. Drake, John R. Carden and Harry P. Clagett
Report Number: NACA-RM-L51H01
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: An analysis has been made of the flight test data obtained with two X-1 airplane shaving 10-percent-thick wings and an 8-percent-thick tail and 8-percent-thick wings and a 6-percent-thick tail. The variation with Mach number of the rate of change of downwash angle of attack, the static stability, and the airplane trim were obtained at a lift coefficient of 0.3.
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Report Date: October 1951
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