Dryden Technical Report Server
From NTRS: Locate an electronic (PDF) copy of the document.
- A FLIGHT EVALUATION OF THE STABILITY AND CONTROL OF THE X-4 SWEPT-WING SEMITAILLESS AIRPLANE , Research Memorandum
Authors: Melvin Sadoff and A. Scott Crossfield
Report Number: NACA-RM-H54G16
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: A flight evaluation of the handling qualities of the swept-wing semitailless X-4 airplane was made. Static and dynamic stability and control investigation covered a speed range from stall to Mach numbers of 0.92. Typical swept-wing instability at moderate lifts was encountered. Unsatisfactory and dangerous self-excited dynamic motions occurred at the high-speed end of the range investigated.
Distribution/Availability: Unclassified - Unlimited
Availability:
From NTRS: Locate an electronic (PDF) copy of the document.
Report Date: August 1954
- DETERMINATION OF LONGITUDINAL HANDLING QUALITIES OF THE D-558-II RESEARCH AIRPLANE AT TRANSONIC AND SUPERSONIC SPEEDS TO A MACH NUMBER OF ABOUT 2.0 , Research Memorandum
Authors: Herman O. Ankenbruck
Report Number: NACA-RM-H54G29A
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: Flight tests were performed with the Douglas D-558-II research airplane to investigate the longitudinal handling qualities and trim characteristics at transonic and supersonic speeds. This paper describes the changes with Mach number of the lift, maneuvering, and trim characteristics with elevator and stabilizer to a Mach number of about 2.0.
Distribution/Availability: Unclassified - Unlimited
Availability:
From NTRS: Locate an electronic (PDF) copy of the document.
Report Date: November 1954
- WING PRESSURE DISTRIBUTION AT LOW LIFT FOR THE XF-92A DELTA-WING AIRPLANE AT TRANSONIC SPEEDS , Research Memorandum
Authors: Earl R. Keener
Report Number: NACA-RM-H54H06
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: Wing pressure distribution from dives at transonic speeds for the Convair XF-92A delta-wing airplane are presented. The data were obtained from five chordwise rows of orifices on the left wing throughout the Mach number range of 0.74 to 1.01 at an airplane normal-force coefficient of about 0.09, for which the left deflection was about 2 degrees up.
Distribution/Availability: Unclassified - Unlimited
Availability:
From NTRS: Locate an electronic (PDF) copy of the document.
Report Date: October 1954
- LONGITUDINAL STABILITY CHARACTERISTICS IN ACCELERATED MANEUVERS AT SUBSONIC AND TRANSONIC SPEEDS OF THE DOUGLAS D-558-II RESEARCH AIRPLANE EQUIPPED WITH A LEADING-EDGE WING CHORD-EXTENSIO , Research Memorandum
Authors: Jack Fischel and Cyril D. Brunn
Report Number: NACA-RM-H54H16
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: On the basis of improved longitudinal stability characteristics exhibited in wind-tunnel model tests, the Douglas D-558-II research airplane was modified to include wing at Mach numbers up to about 1.0. The results of subsonic and transonic flight measurements of the longitudinal stability characteristics of the airplane are presented. The levels of normal-force coefficient at which the stick-fixed stability decays and pitch-up starts have been determined through speed range tested as have the variation of the stability parameters d delta (sub) e/dC (sub) N (sub) A, dF (sub) e/dn, and dC (sub) N (sub) A/d sigma with Mach number. Comparisons of these data with comparable data for the unmodified airplane are also presented.
Distribution/Availability: Unclassified - Unlimited
Availability:
From NTRS: Locate an electronic (PDF) copy of the document.
Report Date: October 1954
- LIFT AND DRAG CHARACTERISTICS OF THE DOUGLAS X-3 RESEARCH AIRPLANE OBTAINED DURING DEMONSTRATION FLIGHT TO A MACH NUMBER OF 1.20 , Research Memorandum
Authors: Donald R. Bellman and Edward D. Murphy
Report Number: NACA-RM-H54I17
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: Lift and drag data for the Douglas X-3 airplane were obtained during some of the demonstration flights. The data extend over the Mach number range from 0.82 to 1.20 and for certain constant Mach numbers the lift coefficient range from 0 to 1.0 is covered. A comparison of the flight data with wind-tunnel and rocket-model tests shows that the model tests satisfactorily predict the performance of the airplane.
Distribution/Availability: Unclassified - Unlimited
Availability:
From NTRS: Locate an electronic (PDF) copy of the document.
Report Date: December 1954
- LATERAL MOTIONS ENCOUNTERED WITH THE DOUGLAS D-558-II ALL-ROCKET RESEARCH AIRPLANE DURING EXPLORATORY FLIGHTS TO A MACH NUMBER OF 2.0 , Research Memorandum
Authors: Herman O. Ankenbruck and Chester H. Wolowicz
Report Number: NACA-RM-H54I27
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: Flight tests were performed with the Douglas D-558-II research airplane to investigate the lateral motions obtained during exploratory flights at supersonic speeds. This paper describes the effects of Mach number and angle of attack on the lateral handling qualities during oscillations at supersonic speeds. Some calculations of period and damping are included. Also shown are the results of some measurements of the variation of rudder hinge moments with sideslip and the effects of power on the variation.
Distribution/Availability: Unclassified - Unlimited
Availability:
From NTRS: Locate an electronic (PDF) copy of the document.
Report Date: December 1954
- A FLIGHT INVESTIGATION OF THE EFFECTS OF INCLINATION OF THE PRINCIPAL AXIS OF INERTIA ON THE DYNAMIC LATERAL STABILITY OF THE REPUBLIC XF-91 AIRPLANE , Research Memorandum
Authors: Thomas W. Finch
Report Number: NACA-RM-L53I28
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: A flight investigation has been conducted to determine the effect of variable wing incidence angle on the dynamic lateral stability of the Republic XF-91 airplane. The tests were conducted over a Mach number range of 0.3 to 0.9 at altitudes of 10,000, 20,000, 30,000 and 37,500 feet at wing incidence angles of –2 degrees, 2 degrees, 4 degrees, and 5.65 degrees.
Distribution/Availability: Unclassified - Unlimited
Availability:
From NTRS: Locate an electronic (PDF) copy of the document.
Report Date: July 1954
- DETERMINATION OF LONGITUDINAL STABILITY IN SUPERSONIC ACCELERATED MANEUVERS FOR THE DOUGLAS D-558-II RESEARCH AIRPLANE , Research Memorandum
Authors: Herman O. Ankenbruck
Report Number: NACA-RM-L53J20
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: Flight tests were performed with the Douglas D-558-II research airplane to investigate the longitudinal stability of the airplane in accelerated flight at supersonic speeds to a Mach number of 1.67. This paper shows the conditions where instability occurs at supersonic speeds.
Distribution/Availability: Unclassified - Unlimited
Availability:
From NTRS: Locate an electronic (PDF) copy of the document.
Report Date: February 1954
- PRELIMINARY DRAG MEASUREMENTS OF THE CONSOLIDATED VULTEE XF-92A DELTA-WING AIRPLANE IN FLIGHT TESTS TO A MACH NUMBER OF 1.01 , Research Memorandum
Authors: Donald R. Bellman and Thomas R. Sisk
Report Number: NACA-RM-L53J23
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: Lift and drag data for the Consolidated Vultee XF-92A delta-wing airplane were obtained for Mach numbers from 0.63 to 0.90. The drag coefficients for a lift coefficient of 0.08 are extended to a Mach number of 1.01.
Distribution/Availability: Unclassified - Unlimited
Availability:
From NTRS: Locate an electronic (PDF) copy of the document.
Report Date: January 1954
- MEASURED DATA PERTAINING TO BUFFETING AT SUPERSONIC SPEEDS OF THE DOUGLAS D-558-II RESEARCH AIRPLANE , Research Memorandum
Authors: Thomas F. Baker
Report Number: NACA-RM-L53L10
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: Data pertaining to buffeting have been measured at supersonic speed and high lift with the Douglas D-558-II airplane. 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 a Mach number of 1.57, a peak normal-force coefficient of 0.80 was attained with no indication of buffeting. Buffet intensities at normal-force coefficients up to 1.5 are given for low supersonic Mach numbers. Sample records of flight in rough air at supersonic speed are included.
Distribution/Availability: Unclassified - Unlimited
Availability:
From NTRS: Locate an electronic (PDF) copy of the document.
Report Date: February 1954
- EFFECT OF WING SLATS AND INBOARD WING FENCES ON THE LONGITUDINAL STABILITY CHARACTERISTICS OF THE DOUGLAS D-558-II RESEARCH AIRPLANE IN ACCELERATED MANEUVERS AT SUBSONIC AND TRANSONIC SPEEDS , Research Memorandum
Authors: Jack Fischel
Report Number: NACA-RM-L53L16
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: The results of subsonic and transonic flight measurements of the longitudinal stability characteristics of the Douglas D-558-II research airplane for several wing-slat and inboard wing-fence configurations are presented at Mach numbers up to 1.0. The improvement provided by fully extended slats, compared to the stability characteristics of the slats-retracted configuration, is shown; and the effects of inboard wing fences on the stability characteristics with slats fully extended are also discussed. Limited data obtained with slats half extended indicated the similarity of this configuration to the slats-retracted configuration. The effects of a bungee (which improved the stick-free stability characteristics) in alleviating the stability changes apparent to the pilot are also discussed.
Distribution/Availability: Unclassified - Unlimited
Availability:
From NTRS: Locate an electronic (PDF) copy of the document.
Report Date: February 1954
- FLIGHT-DETERMINED PRESSURE MEASUREMENTS OVER THE WING OF THE DOUGLAS D-558-II RESEARCH AIRPLANE AT MACH NUMBERS UP TO 1.14 , Research Memorandum
Authors: James R. Peele
Report Number: NACA-RM-L54A07
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: A flight investigation of the section and panel characteristics and loads obtained from pressure measurements over a 35-degrees sweptback wing at level-flight lifts has been made through the Mach number range of 0.65 to 1.14. The section pressure distributions at the root, midspan, and tip stations varied from a subsonic type of distribution at a Mach number of 0.65 to a supersonic type of distribution at Mach numbers above 1.0.
Distribution/Availability: Unclassified - Unlimited
Availability:
From NTRS: Locate an electronic (PDF) copy of the document.
Report Date: March 1954
- FLIGHT DETERMINATION OF THE BUFFETING CHARACTERISTICS OF THE BELL X-5 RESEARCH AIRPLANE AT 58.7-DEGREES SWEEPBACK , Research Memorandum
Authors: Donald W. Briggs
Report Number: NACA-RM-L54C17
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: Flight measurements were made of the buffeting characteristics of the Bell X-5 research airplane at 58.7-degrees sweepback in the Mach number range from 0.65 to approximately 1.03 at altitudes from 37,000 to 43,000 feet. Maximum airplane normal-force coefficients were attained for Mach numbers up to 0.96.
Distribution/Availability: Unclassified - Unlimited
Availability:
From NTRS: Locate an electronic (PDF) copy of the document.
Report Date: May 1954
- LIFT AND DRAG CHARACTERISTICS OF THE DOUGLAS D-558-II RESEARCH AIRPLANE OBTAINED IN EXPLORATORY FLIGHTS TO A MACH NUMBER OF 2.0 , Research Memorandum
Authors: Jack Nugent
Report Number: NACA-RM-L54F03
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: A flight investigation was made of the Douglas D-558-II swept-wing airplane in the slats-retracted configuration. Lift and drag were determined for Mach numbers up to 2.0. The lift-coefficient range extended from below 0.1 to about 0.7.
Distribution/Availability: Unclassified - Unlimited
Availability:
From NTRS: Locate an electronic (PDF) copy of the document.
Report Date: August 1954
|
