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  Partner: UNT Libraries Government Documents Department
 Serial/Series Title: NACA Advanced Confidential Report
 Collection: National Advisory Committee for Aeronautics Collection
Wind-tunnel investigation of an NACA 66-series 16-percent-thick low-drag tapered wing with Fowler and split flaps

Wind-tunnel investigation of an NACA 66-series 16-percent-thick low-drag tapered wing with Fowler and split flaps

Date: January 1, 1946
Creator: Foster, Gerald V
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 control-surface characteristics XIII : various flap overhangs used with a 30-percent-chord flap in an NACA 66-009 airfoil

Wind-tunnel investigation of control-surface characteristics XIII : various flap overhangs used with a 30-percent-chord flap in an NACA 66-009 airfoil

Date: July 1, 1943
Creator: Lockwood, Vernard E
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Wind-tunnel investigation of control-surface characteristics XIX : a double flap with an overhang and an internal aerodynamic balance

Wind-tunnel investigation of control-surface characteristics XIX : a double flap with an overhang and an internal aerodynamic balance

Date: June 1, 1944
Creator: Liddell, Robert B
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Wind-tunnel investigation of control-surface characteristics XV : various contour modifications of a 0.30-airfoil-chord plain flap on an NACA 66(215)-014 airfoil

Wind-tunnel investigation of control-surface characteristics XV : various contour modifications of a 0.30-airfoil-chord plain flap on an NACA 66(215)-014 airfoil

Date: December 1, 1943
Creator: Riebe, John M
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Wind-tunnel investigation of control-surface characteristics XVII : beveled-trailing-edge flaps of 0.20, 0.30, and 0.40 airfoil chord on an NACA 0009 airfoil

Wind-tunnel investigation of control-surface characteristics XVII : beveled-trailing-edge flaps of 0.20, 0.30, and 0.40 airfoil chord on an NACA 0009 airfoil

Date: April 1, 1944
Creator: Lockwood, Vernard E
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Wind-tunnel investigation of control-surface characteristics XVIII : a linked overhang aerodynamic balance

Wind-tunnel investigation of control-surface characteristics XVIII : a linked overhang aerodynamic balance

Date: February 1, 1944
Creator: Liddell, Robert B
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Wind-tunnel investigation of effects of a pusher propeller on lift, profile drag, pressure distribution, and boundary-layer transition of a flapped wing

Wind-tunnel investigation of effects of a pusher propeller on lift, profile drag, pressure distribution, and boundary-layer transition of a flapped wing

Date: April 1, 1945
Creator: Sandahl, Carl A
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 tests of a blunt-nose aileron with beveled trailing edge on an NACA 66(215)-216 airfoil with several modifications of aileron nose and adjacent airfoil contour

Wind-tunnel tests of a blunt-nose aileron with beveled trailing edge on an NACA 66(215)-216 airfoil with several modifications of aileron nose and adjacent airfoil contour

Date: February 1, 1945
Creator: Bird, J D
Description: None
Contributing Partner: UNT Libraries Government Documents Department