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  Partner: UNT Libraries Government Documents Department
 Decade: 1950-1959
 Serial/Series Title: NACA Technical Notes
 Collection: National Advisory Committee for Aeronautics Collection
The aerodynamic design of supersonic propellers from structural considerations

The aerodynamic design of supersonic propellers from structural considerations

Date: December 1, 1952
Creator: Hammack, Jerome B
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic Effects Caused by Icing of an Unswept NACA 65A004 Airfoil

Aerodynamic Effects Caused by Icing of an Unswept NACA 65A004 Airfoil

Date: February 1, 1958
Creator: Gray, Vernon H.
Description: The effects of ice formations on the section lift, drag, and pitching-moment coefficients of an unswept NACA 65A004 airfoil section of 6-foot chord were studied.. The magnitude of the aerodynamic penalties was primarily a function of the shape and size of the ice formation near the leading edge of the airfoil. The exact size and shape of the ice formations were determined photographically and found to be complex functions of the operating and icing conditions. In general, icing of the airfoil at angles of attack less than 40 caused large increases in section drag coefficients (as much as 350 percent in 8 minutes of heavy glaze icing), reductions in section lift coefficients (up to 13 percent), and changes in the pitching-moment coefficient from diving toward climbing moments. At angles of attack greater than 40 the aerodynamic characteristics depended mainly on the ice type. The section drag coefficients generally were reduced by the addition of rime ice (by as much as 45 percent in 8 minutes of icing). In glaze icing, however, the drag increased at these angles of attack. The section lift coefficients were variably affected by rime-ice formations; however, in glaze icing, lift increases at high angles of attack ...
Contributing Partner: UNT Libraries Government Documents Department
The aerodynamic forces and moments on a 1/10-scale model of a fighter airplane in spinning attitudes as measured on a rotary balance in the Langley 20-foot free-spinning tunnel

The aerodynamic forces and moments on a 1/10-scale model of a fighter airplane in spinning attitudes as measured on a rotary balance in the Langley 20-foot free-spinning tunnel

Date: September 1, 1950
Creator: Stone, Ralph W , Jr
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic forces, moments, and stability derivatives for slender bodies of general cross section

Aerodynamic forces, moments, and stability derivatives for slender bodies of general cross section

Date: November 1, 1954
Creator: Sacks, Alvin H.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic forces, moments, and stability derivatives for slender bodies of general cross section

Aerodynamic forces, moments, and stability derivatives for slender bodies of general cross section

Date: November 1, 1954
Creator: Sacks, Alvin H
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic interference of slender wing-tail combinations

Aerodynamic interference of slender wing-tail combinations

Date: January 1, 1957
Creator: Sacks, Alvin H
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic investigation of a four-blade propeller operating through an angle-of-attack range from 0 to 180 degrees

Aerodynamic investigation of a four-blade propeller operating through an angle-of-attack range from 0 to 180 degrees

Date: June 1, 1954
Creator: Mclemore, H Clyde
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic investigation of a parabolic body of revolution at mach number of 1.92 and some effects of an annular supersonic jet exhausting from the base

Aerodynamic investigation of a parabolic body of revolution at mach number of 1.92 and some effects of an annular supersonic jet exhausting from the base

Date: September 1, 1956
Creator: Love, Eugene S
Description: An aerodynamic investigation of a slender pointed parabolic body of revolution was conducted at Mach number of 1.92 with and without the effects of an annular supersonic jet exhausting from the base. Measurements with the jet inoperative were made of lift, drag, pitching moment, base pressures, and radial and axial pressures. With the jet in operation, pressure measurements were made over the rear of the body with the primary variables being angle of attack, ratio of jet velocity to stream velocity, and ratio of pressure at jet exit to stream pressure.
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic loads on a leading-edge flap and a leading-edge slat on the NACA 64A010 airfoil section

Aerodynamic loads on a leading-edge flap and a leading-edge slat on the NACA 64A010 airfoil section

Date: June 1, 1954
Creator: Kelly, John A
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic mixing downstream from line source of heat in high-intensity sound field

Aerodynamic mixing downstream from line source of heat in high-intensity sound field

Date: August 1, 1956
Creator: Mickelson, William R
Description: Theory and measurement showed that the heat wake downstream from a line source is displaced by a transverse standing sound wave in a manner similar to a flag waving in a harmonic mode. With a 147 db, 104 cps standing wave, time-mean temperatures were reduced by an order of magnitude except near the displacement-pattern nodal points. The theory showed that a 161 db, 520 cps standing wave considerably increased the mixing in both the time-mean and instantaneous senses.
Contributing Partner: UNT Libraries Government Documents Department