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  Partner: UNT Libraries Government Documents Department
 Serial/Series Title: NACA Advanced Confidential Report
 Collection: National Advisory Committee for Aeronautics Collection
High-speed investigation of low-drag wing inlets

High-speed investigation of low-drag wing inlets

Date: September 1, 1944
Creator: Smith, Norman F
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Effect of Compressibility on the Pressure and Forces Acting on a Modified NACA 65,3-019 Airfoil Having a 0.20-Chord Flap

Effect of Compressibility on the Pressure and Forces Acting on a Modified NACA 65,3-019 Airfoil Having a 0.20-Chord Flap

Date: January 1, 1946
Creator: Lindsey, W F
Description: An investigation has been conducted in the Langley rectangular high-speed tunnel to determine the effect of compressibility on the pressure distribution for a modified NACA 65,3-019 airfoil having a 0.20-chord flap. The investigation was made for an angle-of-attack range extending from -2 to 12 deg at .20 flap deflections from 0 to -12 deg. Test data were obtained for Mach numbers from 0.28 to approximately 0.74. The results show that the effectiveness of the trailing-edge-type control surface rapidly decreased and approached zero as the Mach number increased above the critical value.
Contributing Partner: UNT Libraries Government Documents Department
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
Two-dimensional wind-tunnel investigation of 0.20-airfoil-chord plain ailerons of different contour on an NACA 65(sub 1)-210 airfoil section

Two-dimensional wind-tunnel investigation of 0.20-airfoil-chord plain ailerons of different contour on an NACA 65(sub 1)-210 airfoil section

Date: December 1, 1945
Creator: Cahill, Jones F
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Effects of specific types of surface roughness on boundary-layer transition

Effects of specific types of surface roughness on boundary-layer transition

Date: February 1, 1946
Creator: Loftin, Laurence K
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The effects of roughness at high Reynolds numbers on the lift and drag characteristics of three thick airfoils

The effects of roughness at high Reynolds numbers on the lift and drag characteristics of three thick airfoils

Date: August 1, 1944
Creator: Turner, Harold R , Jr
Description: None
Contributing Partner: UNT Libraries Government Documents Department
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 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
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
A method for the rapid estimation of turbulent boundary-layer thickness for calculating profile drag

A method for the rapid estimation of turbulent boundary-layer thickness for calculating profile drag

Date: July 1, 1944
Creator: Tetervin, Neal
Description: None
Contributing Partner: UNT Libraries Government Documents Department