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 Decade: 1940-1949
 Year: 1943
 Serial/Series Title: NACA Advanced Confidential Report
 Collection: Technical Report Archive and Image Library
Wind-Tunnel Investigation of a Low-Drag Airfoil Section with a Double Slotted Flap

Wind-Tunnel Investigation of a Low-Drag Airfoil Section with a Double Slotted Flap

Date: September 1, 1943
Creator: Bogdonoff, Seymour M.
Description: Tests were made of an 0.309-chord double-slotted flap on an NACA 65, 3-118, a equals 1.0 airfoil section to determine drag, lift, and pitching-moment characteristics for a range of flap deflections. Results indicate that combination of a low-drag airfoil and a double-slotted flap, of which the two parts moved as a single unit, gave higher maximum lift coefficients than have been obtained with plain, split, or slotted flaps on low-drag airfoils. Pitching moments were comparable to those obtained with other high-lift devices on conventional airfoils for similar lift coefficients.
Contributing Partner: UNT Libraries Government Documents Department
Wind-tunnel data on the aerodynamic characteristics of airplane control surfaces

Wind-tunnel data on the aerodynamic characteristics of airplane control surfaces

Date: December 1, 1943
Creator: Sears, Richard I
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Preliminary Investigation of the Effect of Compressibility on the Maximum Lift Coefficient, Special Report

Preliminary Investigation of the Effect of Compressibility on the Maximum Lift Coefficient, Special Report

Date: February 1, 1943
Creator: Stack, John; Fedziuk, Henry A. & Cleary, Harold E.
Description: Preliminary data are presented on the variation of the maximum lift coefficient with Mach number. The data were obtained from tests in the 8-foot high-speed tunnel of three NACA 16-series airfoils of 1-foot chord. Measurements consisted primarily of pressure-distribution measurements in order to illustrate the nature of the phenomena. It was found that the maximum lift coefficient of airfoils is markedly affected by compressibility even at Mach numbers as low as 0.2. At high Mach numbers pronounced decrease of the maximum lift coefficient was found. The magnitude of the effects of compressibility on the maximum lift coefficient and the low speeds at which these effects first appear indicate clearly that consideration of the take-off thrust for propellers will give results seriously in error if these considerations are based on the usual low-speed maximum-lift-coefficient data generally used.
Contributing Partner: UNT Libraries Government Documents Department
A comparison at high speed of the aerodynamic merits of models of medium bombers having thickened wing roots and having wings with nacelles

A comparison at high speed of the aerodynamic merits of models of medium bombers having thickened wing roots and having wings with nacelles

Date: December 1, 1943
Creator: Draley, Eugene C
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Flight tests of an all-movable vertical tail on the Fairchild XR2K-1 airplane

Flight tests of an all-movable vertical tail on the Fairchild XR2K-1 airplane

Date: June 1, 1943
Creator: Kleckner, Harold F
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Wind tunnel tests of ailerons at various speeds I : ailerons of 0.20 airfoil chord and true contour with 0.35 aileron-chord extreme blunt nose balance on the NACA 66,2-216 airfoil

Wind tunnel tests of ailerons at various speeds I : ailerons of 0.20 airfoil chord and true contour with 0.35 aileron-chord extreme blunt nose balance on the NACA 66,2-216 airfoil

Date: June 1, 1943
Creator: Letko, W; Denaci, H. G. & Freed, C
Description: Hinge-moment, lift, and pressure-distribution measurements were made in the two-dimensional test section of the NACA stability tunnel on a blunt-nose balance-type aileron on an NACA 66,2-216 airfoil at speeds up to 360 miles per hour corresponding to a Mach number of 0.475. The tests were made primarily to determine the effect of speed on the action of this type of aileron. The balance-nose radii of the aileron were varied from 0 to 0.02 of the airfoil chord and the gap width was varied from 0.0005 to 0.0107 of the airfoil chord. Tests were also made with the gap sealed.
Contributing Partner: UNT Libraries Government Documents Department
Wind-tunnel tests of ailerons at various speeds III : ailerons of 0.20 airfoil chord and true contour with 0.35-aileron-chord Frise balance on the NACA 23012 airfoil

Wind-tunnel tests of ailerons at various speeds III : ailerons of 0.20 airfoil chord and true contour with 0.35-aileron-chord Frise balance on the NACA 23012 airfoil

Date: September 1, 1943
Creator: Kemp, W B
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Wind-tunnel tests of ailerons at various speeds II : ailerons of 0.20 airfoil chord and true contour with 0.60 aileron-chord sealed internal balance on the NACA 66,2-216 airfoil

Wind-tunnel tests of ailerons at various speeds II : ailerons of 0.20 airfoil chord and true contour with 0.60 aileron-chord sealed internal balance on the NACA 66,2-216 airfoil

Date: June 1, 1943
Creator: Bird, J D
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Wind tunnel tests of ailerons at various speeds V : pressure distributions over the NACA 66,2-216 and NACA 23012 airfoils with various balances on 0.20-chord ailerons

Wind tunnel tests of ailerons at various speeds V : pressure distributions over the NACA 66,2-216 and NACA 23012 airfoils with various balances on 0.20-chord ailerons

Date: November 1, 1943
Creator: Denaci, H G
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Wind tunnel tests of ailerons at various speeds IV : ailerons of 0.20 airfoil chord and true contour with 0.35 aileron-chord extreme blunt-nose balance on the NACA 23012 airfoil

Wind tunnel tests of ailerons at various speeds IV : ailerons of 0.20 airfoil chord and true contour with 0.35 aileron-chord extreme blunt-nose balance on the NACA 23012 airfoil

Date: August 1, 1943
Creator: Anderson, R A
Description: None
Contributing Partner: UNT Libraries Government Documents Department
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