17 Matching Results

Search Results

Summary of section data on trailing-edge high-lift devices

Description: A summary has been made of available data on the characteristics of airfoil sections with trailing-edge high-lift devices. Data for plain, split, and slotted flaps are collected and analyzed. The effects of each of the variables involved in the design of the various types of flap are examined and, in cases where sufficient data are given, optimum configurations are deduced. Wherever possible, the effects of airfoil section, Reynolds number, and leading-edge roughness are shown. For single and double slotted flaps, where a large amount of unrelated data are available, maximum lift coefficients of many configurations are presented in tables.
Date: January 1, 1949
Creator: Cahill, Jones F
Partner: UNT Libraries Government Documents Department

Effect of Slot-Entry Skirt Extensions on Aerodynamic Characteristics of a Wing Section of the XB-36 Airplane Equipped with a Double Slotted Flap

Description: An investigation was made in the Langley two-dimensional low-turbulence tunnel on a wing section for the XB-36 airplane equipped with a double slotted flap to determine the effect on lift and drag of various slot-entry skirt extension. A skirt extension of 0.787 deg. was found to provide the best combination of high maximum lift with flap deflected and law drag with flap retracted. The data showed that the maximum lift at intermediate (20 deg. to 45 deg.) flap deflections was lowered considerably by the slot-entry extension; but at high flap deflections the effect was small. An increase in Reynolds number from 2.4 million to 6.0 million increased the maximum.lift coefficient at a flap deflection of 55 deg. from 3.12 to 3.30 and from 1.18 to 1.40 for the flap retracted condition, but did not greatly affect the maximum lift coefficient for intermediate flap deflections. The flap and fore flap load data indicated that the maximum lift coefficients at high flap deflections are limited by a breakdown in the flow over the .flaps.
Date: June 30, 1947
Creator: Cahill, Jones F.
Partner: UNT Libraries Government Documents Department

Low-speed aerodynamic characteristics of a series of swept wings having NACA 65A006 airfoil sections (Revised)

Description: Report presenting an investigation to determine the effect of sweep, taper ratio, and aspect ratio on the aerodynamic characteristics of nine semispan wings with NACA 65A006 airfoil sections with and without split flaps. Lift, drag, pitching-moment, and wing-root bending-moment characteristics are presented for a range of Reynolds numbers.
Date: October 17, 1950
Creator: Cahill, Jones F. & Gottlieb, Stanley M.
Partner: UNT Libraries Government Documents Department

Survey of two-dimensional data on pitching-moment changes near maximum lift caused by deflection of high-lift devices

Description: Report presenting a survey of two-dimensional data on trim changes near maximum lift resulting from deflection of various types of leading-edge and trialing-edge high lift devices. Results regarding pitching-moment coefficients, pitching-moment increments, and maximum lift coefficients are provided.
Date: December 2, 1949
Creator: Bidwell, Jerold M. & Cahill, Jones F.
Partner: UNT Libraries Government Documents Department

Aerodynamic load measurements over a leading-edge slat on a 40 degree sweptback wing at Mach numbers from 0.10 to 0.91

Description: Report presenting an investigation of the aerodynamic loads on a leading-edge slat on a 40 degree sweptback wing with NACA 64(sub 1)-112 airfoil sections in the low-turbulence pressure tunnel. Results regarding wing force data, slat force data, and slat pressure distributions are provided.
Date: September 23, 1952
Creator: Cahill, Jones F. & Nuber, Robert J.
Partner: UNT Libraries Government Documents Department

Wing-tunnel investigation of effects of forward movements of transition on section characteristics of a low-drag airfoil with a 0.24-chord sealed plain aileron

Description: Report presenting an investigation to determine the effects of forward movements of transition on the section characteristics of a 12-percent-thick low-drag airfoil section with a 0.24-chord sealed plain aileron. Section lift and aileron section hinge-moment and seal-pressure characteristics were determined at a specific Reynolds number for aerodynamically smooth surfaces and with fixed transition at two different points.
Date: May 1948
Creator: Racisz, Stanley F. & Cahill, Jones F.
Partner: UNT Libraries Government Documents Department

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

Description: Report presenting an investigation to determine optimum double-slotted-flap configurations for seven thin NACA airfoil sections. Lift characteristics, pitching moment, and optimum positioning are explored.
Date: April 1948
Creator: Cahill, Jones F. & Racisz, Stanley F.
Partner: UNT Libraries Government Documents Department

Review of the maximum-lift characteristics of thin and swept wings

Description: Report discussing several investigations into the maximum-lift capabilities of aircraft wings at high speeds. Testing of thin unswept and swept wings at subsonic and transonic speeds, thin and thick wings, and the effect of airfoil sections on various airplanes is presented and compared.
Date: June 5, 1951
Creator: Lowry, John G. & Cahill, Jones F.
Partner: UNT Libraries Government Documents Department

Wind-tunnel development of optimum double-slotted-flap configurations for seven thin NACA airfoil sections

Description: Report presenting an investigation in the two-dimensional low-turbulence tunnels to develop optimum double-slotted-flap configurations for seven thin NACA airfoil sections. Each was equipped with the same flaps and measured at the same Reynolds numbers. Results regarding the lift characteristics and pitching moment are provided.
Date: April 28, 1947
Creator: Cahill, Jones F. & Racisz, Stanley F.
Partner: UNT Libraries Government Documents Department

Investigation at low speed of the flow field behind the lifting surfaces of a model equipped with a 60 degree triangular wing and a 60 degree triangular canard tail

Description: Report presenting an investigation of the flow behind the lifting surfaces of a model equipped with a 60 degree triangular wing and a 60 degree triangular canard tail. Results regarding the force and moment data, air-stream surveys behind the wing, effective values of downwash and dynamic-pressure ratio, effect of tail height and length, a comparison with previous data, the effects of component area and ratio, and the effect of a canard tail are provided.
Date: June 29, 1953
Creator: Newman, Ernest E. & Cahill, Jones F.
Partner: UNT Libraries Government Documents Department

Aerodynamic forces and loadings on symmetrical circular-arc airfoils with plain leading-edge and plain trailing-edge flaps

Description: From Summary: "An investigation has been made in the Langley two-dimensional low-turbulence tunnel and in the Langley two-dimensional low-pressure tunnel of 6- and 10-percent-thick symmetrical circular-arc airfoil sections at low Mach numbers and several Reynolds numbers. The airfoils were equipped with 0.15-chord plain leading-edge flaps and 0.20-chord plan trailing-edge flaps. The section lift and pitching-moment characteristics were determined for both airfoils with the flaps deflected individually and in combination."
Date: 1953
Creator: Cahill, Jones F.; Underwood, William J.; Nuber, Robert J. & Cheesman, Gail A.
Partner: UNT Libraries Government Documents Department