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
Two-dimensional wind-tunnel investigation of four types of high-lift flap on an NACA 65-210 airfoil section

Two-dimensional wind-tunnel investigation of four types of high-lift flap on an NACA 65-210 airfoil section

Date: February 1, 1947
Creator: Cahill, Jones F
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Summary of section data on trailing-edge high-lift devices

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

Date: January 1, 1949
Creator: Cahill, Jones F
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.
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic data for a wing section of the Republic XF-12 airplane equipped with a double slotted flap

Aerodynamic data for a wing section of the Republic XF-12 airplane equipped with a double slotted flap

Date: January 1, 1946
Creator: Cahill, Jones F.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic tests of an NACA 66(215)-116, a=0.6 airfoil with a 0.25c slotted flap for the Fleetwings XA-39 airplane

Aerodynamic tests of an NACA 66(215)-116, a=0.6 airfoil with a 0.25c slotted flap for the Fleetwings XA-39 airplane

Date: November 1, 1944
Creator: Cahill, Jones F.
Description: None
Contributing 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

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

Date: June 30, 1947
Creator: Cahill, Jones F.
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.
Contributing 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

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

Date: May 1, 1948
Creator: Racisz, Stanley F & Cahill, Jones F
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Wind-tunnel development of optimum double-slotted-flap configurations for seven thin NACA airfoil sections

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

Date: April 28, 1947
Creator: Cahill, Jones F & Racisz, Stanley F
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Wind-tunnel investigation of seven thin NACA airfoil sections to determine optimum double-slotted-flap configurations

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

Date: April 1, 1948
Creator: Cahill, Jones F & Racisz, Stanley F
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Low-speed tests of a free-to-yaw model in two wind tunnels of different turbulence

Low-speed tests of a free-to-yaw model in two wind tunnels of different turbulence

Date: February 26, 1952
Creator: Cahill, Jones F & Bird, John D
Description: None
Contributing 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

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

Date: June 29, 1953
Creator: Newman, Ernest E & Cahill, Jones F
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Review of the maximum-lift characteristics of thin and swept wings

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

Date: June 5, 1951
Creator: Lowry, John G & Cahill, Jones F
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Low-speed aerodynamic characteristics of a series of swept wings having NACA 65A006 airfoil sections

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

Date: October 17, 1950
Creator: Cahill, Jones F & Gottlieb, Stanley M
Description: None
Contributing 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

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

Date: December 2, 1949
Creator: Bidwell, Jerold M & Cahill, Jones F
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Preliminary investigation at subsonic and transonic speeds of the aerodynamic characteristics of a biplane composed of a sweptback and a sweptforward wing joined at the tips

Preliminary investigation at subsonic and transonic speeds of the aerodynamic characteristics of a biplane composed of a sweptback and a sweptforward wing joined at the tips

Date: March 12, 1954
Creator: Cahill, Jones F & Stead, Dexter H
Description: None
Contributing 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

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

Date: September 23, 1952
Creator: Cahill, Jones F & Nuber, Robert J
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic forces and loadings on symmetrical circular-arc airfoils with plain leading-edge and plain trailing-edge flaps

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

Date: January 1, 1953
Creator: Cahill, Jones F; Underwood, William J; Nuber, Robert J & Cheesman, Gail A
Description: 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. The section drag characteristics were obtained for the 6-percent-thick airfoil with the flaps partly deflected as low-drag-control flaps and for airfoils with the flaps neutral. Surface pressures were measured on the 6-percent-thick airfoil section with the flaps deflected either individually or in appropriate combination to furnish flap load and hinge-moment data applicable to the structural design of the airfoil. A generalized method is developed that permits the determination of the chordwise pressure distribution over sharp-edge airfoils with plain leading-edge flaps and plain trailing-edge flaps of arbitrary size and deflection.
Contributing Partner: UNT Libraries Government Documents Department