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  1. FLIGHT MEASUREMENTS OF THE STABILITY CHARACTERISTICS OF THE BELL X-5 RESEARCH AIRPLANE IN SIDESLIPS AT 59-DEGREE SWEEPBACK , Research Memorandum
    Authors: Joan M. Childs
    Report Number: NACA-RM-L52K13B
    Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
    Abstract: Flight measurements of the stability characteristics of the Bell X-5 research airplane were made in steady sideslips at 59 degree sweepback at Mach numbers from 0.62 to 0.97 at altitudes varying from 35,000 to 40,000 feet.
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    Report Date: February 1953


  2. PRELIMINARY RESULTS OF STABILITY AND CONTROL INVESTIGATION OF THE BELL X-5 RESEARCH AIRPLANE , Research Memorandum
    Authors: Thomas W. Finch and Donald W. Briggs
    Report Number: NACA-RM-L52K18B
    Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
    Abstract: Results obtained during the acceptance tests of the X-5 airplane are presented. Information on the stalling characteristics, static longitudinal stability characteristics, and lateral control characteristics at various sweep angles is included.
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    Report Date: February 1953


  3. FLIGHT MEASUREMENTS OF PRESSURES ON BASE AND REAR PART OF FUSELAGE OF THE BELL X-1 RESEARCH AIRPLANE AT TRANSONIC SPEEDS, INCLUDING POWER EFFECTS , Research Memorandum
    Authors: Ronald J. Knapp and Wallace E. Johnson
    Report Number: NACA-RM-L52L01
    Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
    Abstract: Flight measurements of the pressure distribution over the base and rear portion of fuselage of the Bell X-1 rocket-propelled airplane at transonic speeds, including power effects, are presented.
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    Report Date: January 1953


  4. SOME MEASUREMENTS OF FLYING QUALITIES OF A DOUGLAS D-558-II RESEARCH AIRPLANE DURING FLIGHTS TO SUPERSONIC SPEEDS , Research Memorandum
    Authors: Herman O. Ankenbruck and Theordore E. Dahlen
    Report Number: NACA-RM-L53A06
    Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
    Abstract: Results of measurements of lateral and longitudinal flying qualities of the Douglas D-558-II research airplane in flight to a Mach number of 1.87 and an altitude of 67,000 feet are presented.
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    Report Date: March 1953


  5. FLIGHT DETERMINATION OF THE STATIC LONGITUDINAL STABILITY BOUNDARIES OF THE BELL X-5 RESEARCH AIRPLANE WITH 59-DEGREE SWEEPBACK , Research Memorandum
    Authors: Thomas W. Finch and Joseph A. Walker
    Report Number: NACA-RM-L53A09B
    Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
    Abstract: Results obtained during flights of the Bell X-5 airplane with 59 degree sweepback are presented showing the variation with Mach number of the normal-force coefficient at the longitudinal reduction in stability. Results are given for a Mach number range of 0.67 to 0.98.
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    Report Date: February 1953


  6. LIFT AND DRAG CHARACTERISTICS OF THE BELL X-5 RESEARCH AIRPLANE AT 59-DEGREE SWEEPBACK FOR MACH NUMBERS FROM 0.60 TO 1.03 , Research Memorandum
    Authors: Donald R. Bellman
    Report Number: NACA-RM-L53A09C
    Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
    Abstract: Lift and drag coefficients for the 59-degree sweptback configuration of the Bell X-5 airplane were determined from flight tests covering the Mach number range 0.60 to 1.03. A brief comparison is made between the 20-degree and 59-degree sweptback configuration.
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    Report Date: February 1953


  7. FLIGHT DETERMINATION OF THE LONGITUDINAL STABILITY IN ACCELERATED MANEUVERS AT TRANSONIC SPEEDS FOR THE DOUGLAS D-558-II RESEARCH AIRPLANE INCLUDING THE EFFECTS OF AN OUTBOARD WING FENC , Research Memorandum
    Authors: Jack Fischel and Jack Nugent
    Report Number: NACA-RM-L53A16
    Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
    Abstract: The results of transonic flight measurements of the longitudinal stability characteristics of the Douglas D-558-II research the wings are presented. The levels of normal-force coefficient at which the stability decreases and pitch-up starts have been determined for both airplane configurations at Mach numbers up to about 0.94.
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    Report Date: March 1953


  8. PRELIMINARY MEASUREMENTS OF STATIC LONGITUDINAL STABILITY AND TRIM FOR THE XF-92A DELTA-WING RESEARCH AIRPLANE IN SUBSONIC AND TRANSONIC FLIGHT , Research Memorandum
    Authors: Thomas R. Sisk and John M. Mooney
    Report Number: NACA-RM-L53B06
    Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
    Abstract: Preliminary longitudinal-trim and static longitudinal stability measurements were made on the XF-92A delta-wing research airplane from Mach number of 0.18 to 0.97 at altitudes from 11,000 to 40,000 feet.
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    Report Date: March 1953


  9. MAXIMUM ALTITUDE AND MAXIMUM MACH NUMBER OBTAINED WITH THE MODIFIED DOUGLAS D-558-II RESEARCH AIRPLANE DURING DEMONSTRATION FLIGHTS , Research Memorandum
    Authors: Theordore E. Dahlen
    Report Number: NACA-RM-L53B24
    Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
    Abstract: The maximum values of Mach number and altitude obtained with the Douglas D-558-II all-rocket research airplane and determined by the radar-phototheodolite method are presented in this paper.
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    Report Date: April 1953


  10. BUFFET REGION OF A SWEPT-WING RESEARCH AIRPLANE DURING FLIGHTS TO SUPERSONIC MACH NUMBERS , Research Memorandum
    Authors: Thomas F. Baker
    Report Number: NACA-RM-L53D06
    Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
    Abstract: Limited measurements have been made of the region in which buffeting has been experienced by the swept-wing Douglas D-558-II research airplane during flights to supersonic Mach numbers. Buffet intensities and frequencies are given.
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    Report Date: May 1953


  11. LOADS EXPERIENCED IN FLIGHTS OF TWO SWEPT-WING RESEARCH AIRPLANES IN THE ANGLE-OF-ATTACK RANGE OR REDUCED STABILITY , Research Memorandum
    Authors: Hubert M. Drake, Glenn H. Robinson and Albert E. Kuhl
    Report Number: NACA-RM-L53D16
    Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
    Abstract: Loads imposed upon the Bell X-5 and Douglas D-558-II swept-wing research airplanes during flights in which reductions of longitudinal stability followed attempted moderate-lift maneuvers are discussed. Information regarding horizontal- and vertical-tail loads, wing loads, and normal-force coefficients obtained during the high-angle-of-attack, unstable portions of the flights are presented.
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    Report Date: June 1953


  12. DETERMINED PRESSURE DISTRIBUTIONS OVER THE WING OF THE BELL X-1 RESEARCH AIRPLANE (10-PERCENT-THICK WING) AT SUBSONIC AND TRANSONIC SPEEDS , Research Memorandum
    Authors: Ronald J. Knapp and Gareth H. Jordan
    Report Number: NACA-RM-L53D20
    Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
    Abstract: Aerodynamic section characteristics for various span locations, as determined by pressure distribution measurements in flight to high lift at Mach numbers between 0.30 and 1.19, are presented for the 10-percent-thick wing of the Bell X-1 research airplane.
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    Report Date: June 1953


  13. AILERON AND ELEVATOR HINGE MOMENTS OF THE BELL X-1 AIRPLANE MEASURED IN TRANSONIC FLIGHT , Research Memorandum
    Authors: Hubert M. Drake and John B. McKay
    Report Number: NACA-RM-L53E04
    Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
    Abstract: Hinge moments have been measured on the aileron and elevator of the Bell X-1 airplane having the 10-percent-thick wing and 8-percent-thick tail. The aileron measurements were made by means of strain gages and pressure distributions while the elevator measurements were made by means of the wheel-force strain gases. The elevator hinge-moment characteristics were determined to a Mach number of 1.18 and the aileron hinge moments to a Mach number of 1.13.
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    Report Date: June 1953


  14. PRELIMINARY FLIGHT MEASUREMENTS OF THE DYNAMIC LONGITUDINAL STABILITY CHARACTERISTICS OF THE CONVAIR XF-92A DELTA-WING AIRPLANE , Research Memorandum
    Authors: Euclid C. Holleman, John H. Evans and William C. Triplett
    Report Number: NACA-RM-L53E14
    Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
    Abstract: Longitudinal airplane oscillations obtained during U.S. Air Force performance tests of the Convair XF-92A airplane have been analyzed to give limited static stability and damping measurements for a Mach number range of 0.59 to 0.94.
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    Report Date: June 1953


  15. LONGITUDINAL FLIGHT CHARACTERISTICS OF THE BELL X-5 RESEARCH AIRPLANE AT 59-DEGREE SWEEPBACK WITH MODIFIED WING ROOTS , Research Memorandum
    Authors: James A. Martin
    Report Number: NACA-RM-L53E28
    Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
    Abstract: In an attempt to improve the longitudinal stability characteristics of the Bell X-5 research airplane at 59-degrees sweepback the wing-root leading edge was modified, the original 52.5-degrees sweptback leading-edge fillets being replaced by rounded leading-edge fillets. The two fillet configurations are compared in this paper on the basis of results obtained from maneuvers into the region of reduced stability at pressure altitudes from 28,000 to 40,000 feet and in the Mach number range from that for stall approach in the clean condition to a Mach number of 0.97.
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    Report Date: August 1953


  16. FLIGHT MEASUREMENTS OF LIFT AND DRAG FOR THE BELL X-1 RESEARCH AIRPLANE HAVING A 10-PERCENT-THICK WING , Research Memorandum
    Authors: Edwin J. Saltzman
    Report Number: NACA-RM-L53F08
    Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
    Abstract: Lift and drag results have been obtained from power-off flight tests of the Bell X-1 (10-percent-thick wing) airplane for Mach numbers 0.68 to 1.01. Comparisons of drag are made with 8-percent-thick-wing flight tests and 10-percent-thick-wing wind tunnel results.
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    Report Date: September 1953


  17. TRANSONIC FLIGHT MEASUREMENTS OF THE AERODYNAMIC LOAD ON THE EXTENDED SLAT OF THE DOUGLAS D-558-II RESEARCH AIRPLANE , Research Memorandum
    Authors: James R. Peele
    Report Number: NACA-RM-L53F29
    Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
    Abstract: The results of transonic flight measurements of the aerodynamic load encountered over a partial-span leading-edge slat on the 35-degrees sweptback wing of the Douglas D-558-II research airplane are presented for the lift range at Mach numbers from 0.45 to 0.98.
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    Report Date: August 1953


  18. HORIZONTAL-TAIL LOAD MEASUREMENTS AT TRANSONIC SPEEDS OF THE BELL X-1 RESEARCH AIRPLANE , Research Memorandum
    Authors: John T. Rogers
    Report Number: NACA-RM-L53F30
    Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
    Abstract: Flight measurements of aerodynamic tail loads have been made on the Bell X-1 research airplane from which the balancing tail loads, the static-longitudinal stability parameter (dC sub M/dC sub L) WF, wing-fuselage aerodynamic center, and zero-lift wing-fuselage combination pitching moment coefficient have been determined from a Mach number of 0.7 to a Mach number greater than 1.0. A comparison was made of measured tail loads and loads calculated using available wing-tunnel data.
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    Report Date: September 1953


  19. MEASUREMENTS OBTAINED DURING THE GLIDE-FLIGHT PROGRAM OF THE BELL X-2 RESEARCH AIRPLANE , Research Memorandum
    Authors: Richard E. Day
    Report Number: NACA-RM-L53G03A
    Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
    Abstract: Results obtained during the glide-flight program of the Bell X-2 research airplane are presented. Landing characteristics and limited data evaluating static longitudinal stability at low speeds are included.
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    Report Date: July 1953


  20. RESULTS OF MEASUREMENTS OF MAXIMUM LIFT AND BUFFETING INTENSITIES OBTAINED DURING FLIGHT INVESTIGATION OF THE NORTHROP X-4 RESEARCH AIRPLANE , Research Memorandum
    Authors: Thomas F. Baker
    Report Number: NACA-RM-L53G06
    Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
    Abstract: 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.
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    Report Date: August 1953


  21. WING LOADS ON THE BELL X-1 RESEARCH AIRPLANE (10-PERCENT-THICK WING) AS DETERMINED BY PRESSURE-DISTRIBUTION MEASUREMENTS IN FLIGHT AT SUBSONIC AND TRANSONIC SPEEDS , Research Memorandum
    Authors: Ronald J. Knapp and Gareth H. Jordan
    Report Number: NACA-RM-L53G14
    Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
    Abstract: The wing loads (including some wing-to-fuselage load carry over) and some aerodynamic characteristics as determined by pressure-distribution measurements in flight to high lift at Mach numbers from 0.50 to 1.19 for the 10-percent-thick wing of the Bell X-1 research airplane are presented.
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    Report Date: November 1953


  22. FUSELAGE PRESSURES MEASURED ON THE BELL X-1 RESEARCH AIRPLANE IN TRANSONIC FLIGHT , Research Memorandum
    Authors: Ronald J. Knapp, Gareth H. Jordan and Wallace E. Johnson
    Report Number: NACA-RM-L53I15
    Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
    Abstract: Fuselage pressure distributions and integrated normal load on the fuselage of the Bell X-1 research airplane (10-percent-thick wing) in flight during pull-ups to near maximum lift at Mach numbers of about 0.78, 0.85, 0.88, and 1.02 are presented.
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    Report Date: November 1953


  23. SOME MEASUREMENTS OF BUFFETING ENCOUNTERED BY A DOUGLAS D-558-II RESEARCH AIRPLANE IN THE MACH NUMBER RANGE FROM 0.5 TO 0.95 , Research Memorandum
    Authors: Thomas F. Baker
    Report Number: NACA-RM-L53I17
    Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
    Abstract: Measurements of the intensity of buffeting were made with a swept-wing Douglas D-558-II research airplane at subsonic speeds. The variation of buffet intensity with lift, angle of attack, and Mach number is presented. The results are compared with similar measurements made with another Douglas D-558-II airplane at high subsonic and supersonic speeds.
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    Report Date: November 1953
 
 
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