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Comparison of the transonic drag characteristics of two wing-body combinations differing only in the location of the 45 degree sweptback wing

Description: Report presenting the drag of a series of wing-body combinations by the free-fall method in order to provide information on the drag characteristics of promising transonic and supersonic airplane arrangements. Time histories, Mach number variations, and drag coefficients for several areas of the body are provided.
Date: December 8, 1947
Creator: Mathews, Charles W. & Thompson, Jim Rogers
Partner: UNT Libraries Government Documents Department
open access

Investigation of a Thin Wing of Aspect Ratio 4 in the Ames 12-Foot Pressure Wind Tunnel 5: Static Longitudinal Stability and Control Throughout the Subsonic Speed Range of a Semispan Model of a Supersonic Airplane

Description: Memorandum presenting wind-tunnel tests of a semispan model of a hypothetical supersonic airplane to determine the static longitudinal stability and control characteristics of the airplane throughout the range of subsonic Mach numbers up to 0.95. The model had a long slender fuselage and a wing and horizontal tail of aspect ratio 4 and taper ratio 0.5. Results regarding the force and moment characteristics, wing wake and effective downwash at the horizontal tail, effects of compressibility, and… more
Date: December 8, 1949
Creator: Johnson, Ben H., Jr. & Rollins, Francis W.
Partner: UNT Libraries Government Documents Department
open access

An empirical criterion for fin stabilizing jettisonable nose sections of airplanes

Description: "Investigations in the Langley 20-foot free-spinning tunnel of models of five jettisonable nose sections have shown that the airplane nose sections are inherently unstable but can be stabilized by the addition of suitable fins. An empirical criterion has been developed which indicates the fin area required for stabilizing an airplane jettisonable nose section" (p. 1).
Date: December 8, 1949
Creator: Scher, Stanley H.
Partner: UNT Libraries Government Documents Department
open access

Wind-Tunnel Investigation of the Stability of the Jettisonable Nose Section of the X-3 Airplane

Description: "Because previous work has indicated that jettisonable nose sections of airplanes may be inherently unstable, and thus may cause dangerous centripetal accelerations on a pilot after jettisoning during high-speed flight, an investigation has been conducted in the Langley 20-foot free-spinning tunnel to determine the behavior in descent of a model of the jettisonable nose section of the Douglas X-3 airplane. The effects of varying the center-of-gravity position, of attaching fins of various sizes… more
Date: December 8, 1946
Creator: Scher, Stanley H.
Partner: UNT Libraries Government Documents Department
open access

Evaluation of Gust and Draft Velocities from Flights of P-61C Airplanes within Thunderstorms July 12, 1947 to July 18, 1947 at Clinton County Army Air Field, Ohio

Description: The gust and draft velocities from records of NACA instruments installed in P-61c airplanes participating in thunderstorm flights at Clinton County Army Air Field, Ohio, from July 12, to July 18, 1947 are presented.
Date: December 8, 1947
Creator: Funk, Jack
Partner: UNT Libraries Government Documents Department
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