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  Partner: UNT Libraries Government Documents Department
 Decade: 1940-1949
 Collection: Technical Report Archive and Image Library
Wind-tunnel investigation of an NACA 23012 airfoil with two sizes of balanced split flap

Wind-tunnel investigation of an NACA 23012 airfoil with two sizes of balanced split flap

Date: November 1, 1940
Creator: Purser, Paul E
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Wind-tunnel investigation of an NACA 23021 airfoil with a 0.32-airfoil-chord double slotted flap

Wind-tunnel investigation of an NACA 23021 airfoil with a 0.32-airfoil-chord double slotted flap

Date: October 1, 1944
Creator: Riebe, John M
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Wind-tunnel investigation of an NACA 23021 airfoil with two sizes of balanced split flaps

Wind-tunnel investigation of an NACA 23021 airfoil with two sizes of balanced split flaps

Date: February 1, 1941
Creator: Schuldenfrei, Marvin J
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Wind-tunnel investigation of an NACA 23030 airfoil with various arrangements of slotted flaps

Wind-tunnel investigation of an NACA 23030 airfoil with various arrangements of slotted flaps

Date: March 1, 1940
Creator: Recant, I G
Description: AN investigation was made of a large-chord NACA 23030 airfoil with a 40- and a 25.66 percent-chord slotted flap to determine the section aerodynamic characteristics of the airfoil affected by flap chord, slot shape, flap position, and flap deflection. The flap positions for maximum lift, the position for minimum drag at moderate and high lift coefficients, and the complete section aerodynamic characteristics of selected optimum arrangements are given. Envelope polar of various flap arrangements are included. The relative merits of slotted flaps of different chords on the NACA 23030 airfoil are discussed, and a comparison is made of each flap size with a corresponding flap size on the NACA 23021 and 23012 airfoils. The lowest profile drags at moderate lift coefficients were obtained with an easy entrance to the slot. The 25.66-percent-chord slotted flap gave lower drag than the 40-percent-chord flap for lift coefficients less than 1.8, but the 40-percent-chord flap gave considerably lower drag for lift coefficients. The drag coefficients at moderate and high lift coefficients were greater with both sizes of flap on the NACA 23030 airfoil than on either the NACA 23021 or the NACA 23012 airfoil. The maximum lift coefficient for the deflections tested with either ...
Contributing Partner: UNT Libraries Government Documents Department
Wind-tunnel investigation of an NACA full-span high-lift lateral-control combination I : section characteristics, NACA 23012 airfoil

Wind-tunnel investigation of an NACA full-span high-lift lateral-control combination I : section characteristics, NACA 23012 airfoil

Date: July 1, 1942
Creator: Lowry, John G
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Wind-Tunnel Investigation of an NACA Low-Drag Tapered Wing with Straight Trailing Edge and Simple Split Flaps, Special Report

Wind-Tunnel Investigation of an NACA Low-Drag Tapered Wing with Straight Trailing Edge and Simple Split Flaps, Special Report

Date: December 1, 1941
Creator: Muse, Thomas C. & Neely, Robert H.
Description: An investigation was conducted in the NACA 19-foot pressure wind tunnel of a tapered wing with straight railing edge having NACA 66 series low-drag airfoil sections and equipped with full-span and partial-span simple split flaps. The airfoil sections used were the NACA 66,2-116 at the root and the 66,2-216 at the tip. The primary purpose of the investigation was to determine the effect of the split flaps on the aerodynamic characteristics of the tapered wing. Complete lift, drag, and pitching-moment coefficients were determined for the plain wing and for each flap arrangement through a Reynold number range of 2,600,000 to 4,600,000. The results of this investigation indicate that values of maximum lift coefficient comparable to values obtained on tapered wings with conventional sections and similar flap installations can be obtained from wings with the NACA low-drag sections. The increment of maximum lift due to the split flap was found to vary somewhat with Reynold number over the range investigated. The C(sub L)max of the wing alone is 1.49 at a Reynolds number of 4,600,000; whereas with the partial-span simple split flap it is 2.22 and with the full-span arrangement, 2.80. Observations of wool tufts on the wing indicate that the ...
Contributing Partner: UNT Libraries Government Documents Department
Wind-tunnel investigation of bomb-bay configurations intended to minimize the tumbling of light-weight bombs

Wind-tunnel investigation of bomb-bay configurations intended to minimize the tumbling of light-weight bombs

Date: June 25, 1947
Creator: Kuhn, Richard E & Polhamus, Edward C
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Wind-tunnel investigation of boundary-layer control by suction on NACA 655-424 airfoil with double slotted flap

Wind-tunnel investigation of boundary-layer control by suction on NACA 655-424 airfoil with double slotted flap

Date: June 1, 1948
Creator: Racisz, Stanley F & Quinn, John H
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Wind-tunnel investigation of boundary-layer control by suction on the NACA 653-418, a = 1.0 airfoil section with a 0.29-airfoil-chord double slotted flap

Wind-tunnel investigation of boundary-layer control by suction on the NACA 653-418, a = 1.0 airfoil section with a 0.29-airfoil-chord double slotted flap

Date: June 1, 1946
Creator: Quinn, John H , Jr
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Wind-tunnel investigation of carburetor-air inlets

Wind-tunnel investigation of carburetor-air inlets

Date: February 1, 1942
Creator: Csarnecki, K R
Description: None
Contributing Partner: UNT Libraries Government Documents Department