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Flight investigation of the aerodynamic forces on a wing-mounted external-store installation on the Douglas D-558-II research airplane

Description: Report presenting aerodynamic forces for an external-store installation on the Douglas D-558-II research airplane. Store-pylon, pylon-alone, and fin loads were determined during angle-of-attack and angle-of-sideslip maneuvers over a range of Mach numbers. Results regarding the side-force coefficients, normal-force coefficients, external-store-load parameters, external-store fin loads, and wing-panel aerodynamic loads are provided.
Date: May 13, 1958
Creator: Johnson, Clinton T.
Partner: UNT Libraries Government Documents Department

Maximum altitude and maximum Mach number obtained with the modified Douglas D-558-II research airplane during demonstration flights

Description: From Summary: "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 represents an airspeed of 1243 miles per hour."
Date: April 20, 1953
Creator: Dahlen, Theodore E.
Partner: UNT Libraries Government Documents Department

Exploratory investigation of external stores in the aerodynamic characteristics of a 1/16-scale model of the Douglas D-558-II research airplane at a Mach number of 2.01

Description: Report presenting an investigation of stores on the Douglas D-558-II research airplane in the wind tunnel and in flight using various store configurations. The drag measured for all store configurations was high, from two to three times the free-air drag estimated for the store and pylon. Results regarding longitudinal characteristics and lateral characteristics are provided.
Date: August 25, 1954
Creator: Smith, Norman F.
Partner: UNT Libraries Government Documents Department

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.
Partner: UNT Libraries Government Documents Department

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: From Summary: "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, for all flight configurations, the increase in airplane normal-force coefficient above the angle of attack at which the wing reaches its maximum normal-force coefficient is due principally to the contribution of the fuselage to the airplane normal-force coefficient."
Date: January 19, 1951
Creator: Mayer, John P. & Valentine, George M.
Partner: UNT Libraries Government Documents Department

Flight-determined pressure distributions over a section of the 35 degree swept wing of the Douglas D-558-II research airplane at Mach numbers up to 2.0

Description: From Summary: "Measurements of pressure distributions have been made over a wing midsemispan station on the 35 degree sweptback wing of the Douglas D-558-II research airplane at Mach numbers from 1.17 to 2.0. The results of the investigation indicate that, as the angle of attack increased at the higher Mach numbers, the pressure coefficient for a vacuum limited the extent to which the upper-surface pressures could expand. Consequently most of the increase in section normal-force coefficient at high angles of attack can be attributed to the increase in pressure over the lower surface."
Date: March 25, 1955
Creator: Jordan, Gareth H. & Keener, Earl R.
Partner: UNT Libraries Government Documents Department

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.
Partner: UNT Libraries Government Documents Department

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 compared with the buffet intensity-lift variation at subsonic Mach numbers."
Date: February 18, 1954
Creator: Baker, Thomas F.
Partner: UNT Libraries Government Documents Department

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 that the lateral stability characteristics of the D-558-II airplane for the flight condition discussed should satisfy the Air Force - Navy period-damping criterion when the proposed autopilot is installed. Airplane motions in sideslip subsequent to a disturbance in sideslip are presented for several representative flight conditions in which a time lag in the autopilot of 0.10 second was assumed.
Date: August 17, 1950
Creator: Gates, Ordway B., Jr. & Sternfield, Leonard
Partner: UNT Libraries Government Documents Department

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.
Partner: UNT Libraries Government Documents Department

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.
Partner: UNT Libraries Government Documents Department

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.
Partner: UNT Libraries Government Documents Department

An analysis of surface pressures and aerodynamic load distribution over the swept wing of the Douglas D-558-II research airplane at Mach numbers from 0.73 to 1.73

Description: Report presenting the wing-section pressure-distribution and wing-panel load characteristics of the Douglas D-558-II airplane for a range of Mach numbers and airplane normal-force coefficients. At subsonic speeds, the pressure distributions are characterized by a high negative-pressure peak with an abrupt pressure recovery as a result of the leading-edge expansion over the upper surface at moderate angles of attack.
Date: April 21, 1958
Creator: Taillon, Norman V.
Partner: UNT Libraries Government Documents Department

Wind-tunnel investigation of the damping in roll of the Douglas D-558-II research airplane and its components at supersonic speeds

Description: Experimental values of damping in roll at zero angle of attack of the Douglas D-558-II research airplane and its components have been obtained at five different Mach numbers. Large effects of Reynolds number, boundary layer, and wing-incidence angle on the damping in roll were obtained.
Date: September 7, 1956
Creator: McDearmon, Russell W.
Partner: UNT Libraries Government Documents Department

Preliminary measurements of the dynamic lateral stability characteristics of the Douglas D-588-II (BuAero No. 37974) airplane

Description: From Summary: "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."
Date: August 18, 1949
Creator: Sjoberg, Sigurd A.
Partner: UNT Libraries Government Documents Department

Investigation at high subsonic speeds of the effects of various underwing external-store arrangements on the aerodynamic characteristics of a 1/16-scale model of the Douglas D-558-II Research Airplane

Description: Report presenting an investigation at high subsonic speeds of various arrangements of underwing external stores on a model of the Douglas D-558-II research airplane. Three sizes of a short-cylinder shape and two sizes of a long-cylinder shape were investigated with three thicknesses of pylon support on one store configuration. Results regarding drag characteristics and lift and pitch characteristics are provided.
Date: July 18, 1955
Creator: Silvers, H. Norman & King, Thomas J., Jr.
Partner: UNT Libraries Government Documents Department

Effects of canopy, revised vertical tail, and a yaw-damper vane on the aerodynamic characteristics of a 1/16-scale model of the Douglas D-558-II research airplane at a Mach number of 2.01

Description: Report discussing the aerodynamic characteristics in pitch and sideslip of a model of a Douglas D-558-II airplane with and without a yaw-damper vane at Mach number 2.01. A revised model was tested using a canopy and modified vertical tail. The revised configuration was found to have higher directional stability, trim lift coefficients, drag, and more positive effective dihedral than the original configuration.
Date: August 30, 1954
Creator: Robinson, Ross B.
Partner: UNT Libraries Government Documents Department

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
Partner: UNT Libraries Government Documents Department

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.
Partner: UNT Libraries Government Documents Department

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.
Partner: UNT Libraries Government Documents Department

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.
Partner: UNT Libraries Government Documents Department

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.
Partner: UNT Libraries Government Documents Department

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.
Partner: UNT Libraries Government Documents Department

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.
Partner: UNT Libraries Government Documents Department