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Preliminary Measurements of the Dynamic Lateral Stability Characteristics of the Douglas D-588-II (BuAero No. 37974) Airplane

Description: "This paper presents some data on the dynamic lateral stability characteristics of the Douglas D-558-II (BuAero No. 37974) airplane. For the airplane in the clean condition, the lateral oscillations are lightly damped. In the landing condition, the airplane performs a constant-amplitude lateral oscillation" (p. 1).
Date: August 18, 1949
Creator: Sjoberg, Sigurd A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Flight Measurements With the Douglas D-558-II (BuAero No. 37974) Research Airplane: Static Lateral and Directional Stability Characteristics as Measured in Sideslips at Mach Numbers Up to 0.87

Description: Report presenting flight measurements in sideslips of the static lateral and directional stability characteristics of the Douglas D-558-II airplane. It is part of an investigation to determine the stability and control characteristics and aerodynamic loads acting on the wing and horizontal tail of an airplane from stalling speed up to a maximum Mach number of 0.90. Results regarding variations of rudder, total aileron, elevator control positions and control forces, aileron position, and aerodyn… more
Date: May 19, 1950
Creator: Sjoberg, S. A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Flight measurements with the Douglas D-558-II (BuAero No. 37974) research airplane : determination of the aerodynamic center and zero-lift pitching-moment coefficient of the wing-fuselage combination by means of tail-load measurements in the Mach num

Description: Report presenting flight measurements of aerodynamic tail loads made on the Douglas D-558-II from which the variation with Mach number of the wing-fuselage aerodynamic center, static-longitudinal-stability parameter, the tail load per g, and the zero-lift wing-fuselage pitching-moment coefficient determined up to Mach number 0.87.
Date: July 11, 1950
Creator: Mayer, John P.; Valentine, George M. & Mayer, Geraldine C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Flight Measurements With the Douglas D-558-II (BuAero No. 37974) Research Airplane: Lateral Control Characteristics as Measured in Abrupt Aileron Rolls at Mach Numbers Up to 0.86

Description: Report presenting flight measurements of the lateral control characteristics of the Douglas D-558-II airplane in abrupt rudder-fixed aileron rolls. Results regarding the aileron rolling effectiveness, time histories, and aileron effectiveness variation with Mach number are provided.
Date: July 20, 1950
Creator: Wilmerding, J. V.; Stillwell, W. H. & Sjoberg, S. A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Effect of an Autopilot Sensitive to Yawing Velocity on the Lateral Stability of the Douglas D-558-II Airplane

Description: A theoretical investigation has been made to determine the effect on the lateral stability of the Douglas D-58-II airplane of an autopilot sensitive to yawing velocity. The effects of inclination of the gyro spin axis to the flight path and of tire lag in the autopilot were also determined. The flight conditions investigated included landing at sea level, approach condition at 12,000 feet, and cruising at 50,000 feet at Mach numbers of 0.80 and 1.2. The results of the investigation indicated th… more
Date: August 17, 1950
Creator: Gates, Ordway B., Jr. & Sternfield, Leonard
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Flight Measurements With the Douglas D-558-II (BuAero No. 37974) Research Airplane: Measurements of the Buffet Boundary and Peak Airplane Normal-Force Coefficients at Mach Numbers Up to 0.90

Description: Report presenting measurements of the buffet boundary and peak normal-force coefficients for the Douglas D-558-II airplane up to a Mach number of 0.90. Results regarding airplane lift curves and a comparison between the maximum normal-force coefficients and buffet boundaries for this particular aircraft and the Bell X-1 airplane are also provided.
Date: August 28, 1950
Creator: Mayer, John P. & Valentine, George M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Flight Measurements With the Douglas D-558-II (BuAero No. 37974) Research Airplane: Low-Speed Stalling and Lift Characteristics

Description: Report presenting the low-speed stalling and lift characteristics of the Douglas D-558-II airplane measured in a series of 1 g stalls in four different airplane configurations. Various combinations of landing gear, flaps, inlet-duct flaps, and slats were tested at a range of altitudes.
Date: September 5, 1950
Creator: Stillwell, W. H.; Wilmerding, J. V. & Champine, R. A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Flight Measurements With the Douglas D-558-II (BuAero No. 37974) Research Airplane: Measurements of Wing Loads at Mach Numbers Up to 0.87

Description: Report presenting flight measurements of the aerodynamic wing normal force, bending moment, and pitching moment using strain gains on the D-558-II airplane at Mach numbers up to 0.87 and angles of attack up to 38 degrees. Results regarding Mach number effects and normal-force-coefficient effects are provided.
Date: December 26, 1950
Creator: Mayer, John P.; Valentine, George M. & Swanson, Beverly J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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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

Description: Report presenting flight measurements using the Douglas D-558-II airplane in order to determine the longitudinal stability and control characteristics in steady and accelerated flight. Results are given for various flap positions, especially in regards to degrees of instability present.
Date: January 17, 1951
Creator: Sjoberg, S. A.; Peele, James R. & Griffith, John H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Flight Measurements With the Douglas D-558-II (BuAero No. 37974) Research Airplane: Measurements of the Distribution of the Aerodynamic Load Among the Wing, Fuselage, and Horizontal Tail at Mach Numbers Up to 0.87

Description: "Flight measurements of the aerodynamic wing and tail loads have been made on the Douglas D-558-II airplane from which the distribution of the aerodynamic load among the wing, fuselage, and horizontal tail has been determined at Mach numbers up to 0.87. These measurements indicate that, for normal-force coefficients less than 0.7, the distribution of air load among the airplane components does not change appreciably with Mach number at Mach number up to 0.87. The measurements also indicate that… more
Date: January 19, 1951
Creator: Mayer, John P. & Valentine, George M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Flight Measurements With the Douglas D-558-II (BuAero No. 37974) Research Airplane: Dynamic Lateral Stability

Description: 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.
Date: June 18, 1951
Creator: Stillwell, W. H. & Wilmerding, J. V.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Wind-Tunnel Investigation of the Low-Speed Static and Rotary Stability Derivatives of a 0.13-Scale Model of the Douglas D-558-II Airplane in the Landing Configuration

Description: Report presenting a wind-tunnel investigation to determine the low-speed static and rotary stability derivatives of a model of the Douglas D-558-II airplane in the landing configuration. Results regarding the static longitudinal characteristics, static lateral characteristics, characteristics in rolling flow, and characteristics in yawing flow are provided.
Date: August 27, 1952
Creator: Queijo, M. J. & Wells, Evalyn G.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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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

Description: Report presenting the longitudinal frequency-response characteristics and the stability derivatives of the Douglas D-558-II airplane at a range of Mach numbers and altitudes. Results of experimentation were compared to computed values.
Date: September 18, 1952
Creator: Holleman, Euclid C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Some Measurements of Flying Qualities of a Douglas D-558-II Research Airplane During Flights to Supersonic Speeds

Description: Report presenting some measurements of the dynamic lateral stability and lateral and longitudinal trim of a Douglas D-558-II in flights up to a Mach number of 1.87 and an altitude of about 67,000 feet. Testing indicated that the airplane flying in low density air at supersonic speeds had poor dynamic lateral stability, which worsened as the Mach number was increased to 1.85.
Date: March 10, 1953
Creator: Ankenbruck, Herman O. & Dahlen, Theodore E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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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 Fence

Description: The results of transonic flight measurements of the longitudinal stability characteristics of the Douglas D-558-II research airplane in the original configuration and with outboard fences mounted on 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.
Date: March 13, 1953
Creator: Fischel, Jack & Nugent, Jack
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Maximum Altitude and Maximum Mach Number Obtained With the Modified Douglas D-558-II Research Airplane During Demonstration Flights

Description: "Flights to explore the high altitude and Mach number regions were made with the Douglas D-558-II research airplane in August 1951. Maximum pressure altitude recorded was 77,500 feet and the maximum geometric altitude obtained from radar data was 79,500 feet above sea level. The maximum Mach number obtained was 1.87. When a standard atmosphere is assumed, this value represents a true airspeed of 1238 miles per hour; or at the existing temperature, 3 degrees Fahrenheit above standard, this repre… more
Date: April 20, 1953
Creator: Dahlen, Theodore E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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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.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Loads experienced in flights of two swept-wing research airplanes in the angle-of-attack range of reduced stability

Description: Report presenting load measurements using the swept-wing Bell X-5 and Douglas D-558-II research airplanes during flights in which reductions of longitudinal stability were experienced when pilots attempted to perform routine test maneuvers at moderate values of lift. Results regarding the maximum angles of attack and sideslip measured, pitching accelerations, horizontal-tail loads, wing loads, and stability deficiencies are provided.
Date: June 5, 1953
Creator: Robinson, Glenn H.; Drake, Hubert M. & Kuhl, Albert E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Transonic Flight Measurement of the Aerodynamic Load on the Extended Slat of the Douglas D-558-II Research Airplane

Description: Report presenting a flight investigation of the aerodynamic loads of a partial-span extended leading-edge slat on the 35-degree sweptback wing of the Douglas D-558-II research airplane. The slat normal-force coefficient was found to increase with airplane normal-force coefficient until peak slat normal-force-coefficient was reached at approximately 2.2 to 2.4.
Date: August 27, 1953
Creator: Peele, James R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Static Longitudinal Stability and Control Characteristics of a 1/16 -Scale Model of the Douglas D-558-II Research Airplane at Mach Numbers of 1.61 and 2.01

Description: Memorandum presenting an investigation in the 4- by 4-foot supersonic pressure tunnel at Mach numbers of 1.61 and 2.01 to determine the static longitudinal stability and control characteristics of a 1/16-scale model of the Douglas D-558-II research airplane. The results indicated a high degree of longitudinal stability that decreased slightly with increasing Mach number and lift coefficient.
Date: November 6, 1953
Creator: Spearman, M. Leroy
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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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.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Determination of Longitudinal Stability in Supersonic Accelerated Maneuvers for the Douglas D-558-II Research Airplane

Description: Report discussing testing of a Douglas D-558-II to investigate its longitudinal stability characteristics in accelerated flight at supersonic speeds. Information about the normal-force coefficients and their relation to stability and pitch-up of the aircraft is included.
Date: February 17, 1954
Creator: Ankenbruck, Herman O.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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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 compa… more
Date: February 18, 1954
Creator: Baker, Thomas F.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Flight-Determined Pressure Measurements Over the Wing of the Douglas D-558-II Research Airplane at Mach Numbers Up to 1.14

Description: Report presenting an investigation of the section and panel characteristics and loads obtained from pressure measurements over a 35 degree sweptback wing at level-flight lifts for a range of Mach numbers. Section pressure distributions were taken at the root, midspan, and tip stations of a Douglas D-558-II airplane.
Date: March 12, 1954
Creator: Peele, James R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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