UNT Libraries Government Documents Department - 8 Matching Results

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Wind-Tunnel Investigation at Low Speed of Sideslipping, Rolling, Yawing, and Pitching Characteristics for a Model of a 45 Degree Swept-Wing Fighter-Type Airplane

Description: Report presenting an investigation in the stability tunnel at low speed to determine the rolling characteristics at combined angles of attack and sideslip for a model of a fighter-type airplane with a 45 degree sweptback wing. Testing was performed with the original vertical tail and a vertical tail with a 27 percent larger exposed area. Results regarding the static longitudinal stability, directional stability, and effect of the different tails are presented.
Date: September 1, 1955
Creator: Jaquet, Byron M. & Fletcher, H. S.
Item Type: Refine your search to only Report
open access

Longitudinal Aerodynamic Characteristics at Transonic Speeds of a Complete Model With an Unswept Wing and a Sweptback Horizontal Tail at Two Vertical Locations

Description: Memorandum presenting an investigation to determine the static longitudinal stability contribution of a horizontal tail at two vertical locations behind a 4-percent-thick unswept-wing-fuselage combination at transonic speeds. The model used in tests is comprised of an unswept wing located in the midwing position on a body of revolution and a sweptback horizontal tail mounted on a vertical tail.
Date: September 1, 1955
Creator: Hieser, Gerald & Kudlacik, Louis
Item Type: Refine your search to only Report
open access

Hydrodynamic Pressure Distribution Obtained With a Streamline Body Equipped With Chine Strips

Description: Memorandum presenting an investigation to determine the nature of the pressure distribution and the order of magnitude of the pressures on a streamline body moving on a water surface. The body of revolution was equipped with chine strips and had a fineness ratio of 9. The results from the investigation indicate that there is a characteristic pattern of hydrodynamic pressure distribution for streamline bodies equipped with chine strips and moving on a water surface.
Date: September 1, 1955
Creator: Weinflash, Bernard
Item Type: Refine your search to only Report
open access

Horizontal-Tail Load Measurements at Transonic Speeds of the Bell X-1 Research Airplane

Description: Report presenting a flight investigation to determine horizontal-tail loads at transonic speeds of the Bell X-1. The tests were made through the transonic region and at high lift coefficients. Results regarding the time histories, tail load data, aerodynamic-center positions, and potential load discrepancy explanations are presented.
Date: September 1, 1953
Creator: Rogers, John T.
Item Type: Refine your search to only Report
open access

A Brief Hydrodynamic Investigation of a Navy Seaplane Design Equipped With a Hydro-Ski

Description: Report presenting testing of a model of a Navy Bureau of Aeronautics design in Langley tank no. 2 to determine the calm-water take-off and rough-water landing characteristics of the design with particular attention paid to the take-off resistance and landing accelerations. Results regarding resistance, take-off stability, landing stability, spray, and landing acceleration are provided.
Date: September 1, 1953
Creator: Fisher, Lloyd J. & Hoffman, Edward L.
Item Type: Refine your search to only Report
open access

Transonic Aerodynamic Characteristics of an NACA 64A006 Airfoil Section With a 15-Percent-Chord Leading-Edge Flap

Description: Report presenting information about airfoil section normal-force, drag, pitching-moment, flap-normal-force, and hinge-moment characteristics at Mach numbers from 0.5 to 1.0 on an NACA 64A006 airfoil with 15-percent-chord leading-edge flap. Differing results were noted in the Mach ranges of 0.5 to 0.8 and over 0.8.
Date: September 1, 1953
Creator: Humphreys, Milton D.
Item Type: Refine your search to only Report
open access

Static lateral stability characteristics of an airplane model having a 47.7 degree sweptback wing of aspect ratio 6 and the contribution of various model components at a Reynolds number of 4.45 x 10(exp 6)

Description: Report presenting an investigation to determine the low-speed yaw characteristics of an airplane model with a 47.7 degree sweptback wing of aspect ratio 6 and to determine lateral stability contributions of various model components and associated mutual interference. The complete airplane model was directionally stable through the yaw-angle range for angles of attack up to 23 degrees.
Date: September 1, 1953
Creator: Griner, Roland F.
Item Type: Refine your search to only Report
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