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  Partner: UNT Libraries Government Documents Department
 Decade: 1940-1949
Wind-tunnel investigation of plain ailerons for a wing with a full-span flap consisting of an inboard Fowler and an outboard retractable split flap

Wind-tunnel investigation of plain ailerons for a wing with a full-span flap consisting of an inboard Fowler and an outboard retractable split flap

Date: March 1, 1941
Creator: Purser, Paul E
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Wind-tunnel investigation of profile drag and lift of an intermediate wing section of the XP-51 airplane with beveled trailing-edge and contour ailerons

Wind-tunnel investigation of profile drag and lift of an intermediate wing section of the XP-51 airplane with beveled trailing-edge and contour ailerons

Date: January 1, 1943
Creator: Underwood, William J
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Wind tunnel investigation of rear underslung fuselage ducts

Wind tunnel investigation of rear underslung fuselage ducts

Date: September 1, 1943
Creator: Nelson, W J
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Wind-Tunnel Investigation of Rectangular Air-Duct Entrances in the Leading Edge of an NACA 23018 Wing, Special Report

Wind-Tunnel Investigation of Rectangular Air-Duct Entrances in the Leading Edge of an NACA 23018 Wing, Special Report

Date: September 1, 1940
Creator: Biermann, David & McLellan, Charles H.
Description: A preliminary investigation of a number of duct entrances of rectangular shape installed in the leading edge of a wing was conducted in the NACA 20-foot tunnel to determine the external drag, the available pressure, the critical Mach numbers, and the effect on the maximum lift. The results showed that the most satisfactory entrances, which had practically no effect on the wing characteristics, had their lips approximately in the vertical plane of the leading edge of the wing. This requirement necessitated extending the lips outside the wing contour for all except the small entrances. Full dynamic pressure was found to be available over a fairly wide range of angle of attack. The critical Mach number for a small entrance was calculated to be as high as that for the plain wing but was slightly lower for the larger entrances tested.
Contributing Partner: UNT Libraries Government Documents Department
Wind-tunnel investigation of rounded horns and of guards on a horizontal tail surface

Wind-tunnel investigation of rounded horns and of guards on a horizontal tail surface

Date: October 1, 1944
Creator: Lockwood, Vernard E
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Wind-tunnel investigation of seven thin NACA airfoil sections to determine optimum double-slotted-flap configurations

Wind-tunnel investigation of seven thin NACA airfoil sections to determine optimum double-slotted-flap configurations

Date: April 1, 1948
Creator: Cahill, Jones F & Racisz, Stanley F
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Wind-tunnel investigation of several factors affecting the performance of a high-speed pursuit airplane with air-cooled radial engine

Wind-tunnel investigation of several factors affecting the performance of a high-speed pursuit airplane with air-cooled radial engine

Date: November 1, 1941
Creator: Wenzinger, C. J.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Wind-Tunnel Investigation of Shielded Horn Balances and Tabs on a 0.7-Scale Model of XF6F Vertical Tail Surface

Wind-Tunnel Investigation of Shielded Horn Balances and Tabs on a 0.7-Scale Model of XF6F Vertical Tail Surface

Date: March 1, 1944
Creator: Lowry, John G.; Maloney, James A. & Garner, I Elizabeth
Description: Results of subject tests indicate the difficulty of obtaining closely balanced rudder surfaces for most tail assemblies with shielded horns and maintaining a near zero rate-of-change of hinge-moment coefficient without an additional balancing device. A comparison is made between shielded and unshielded horn test results. Pressure distribution and tuft tests of flow over different shaped horns showed higher critical speed for medium-taper nosed horn. The trim tab nose shape had little effect on tab test results.
Contributing Partner: UNT Libraries Government Documents Department
Wind-tunnel investigation of split trailing-edge lift and trim flaps on a tapered wing with 23 degree sweepback

Wind-tunnel investigation of split trailing-edge lift and trim flaps on a tapered wing with 23 degree sweepback

Date: July 1, 1947
Creator: Letko, William & Feigenbaum, David
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Wind-tunnel investigation of spoiler, deflector, and slot lateral-control devices on wings with full-span split and slotted flaps

Wind-tunnel investigation of spoiler, deflector, and slot lateral-control devices on wings with full-span split and slotted flaps

Date: January 1, 1941
Creator: Wenzinger, Carl J & Rogallo, Francis M
Description: Report presents the results of an extensive investigation made in the NACA 7 by 10-foot wind tunnel of spoiler, deflector, and slot types of lateral-control device on wings with full-span split and slotted flaps. The static rolling and yawing moments were determined for all the devices tested, and the static hinge moments and the time response were determined for a few devices of each type.
Contributing Partner: UNT Libraries Government Documents Department