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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
Aerodynamic characteristics of a two-blade NACA 10-(3)(062)-045 propeller and of a two-blade NACA 10-(3)(08)-045 propeller

Aerodynamic characteristics of a two-blade NACA 10-(3)(062)-045 propeller and of a two-blade NACA 10-(3)(08)-045 propeller

Date: January 1953
Creator: Solomon, William
Description: Characteristics are given for the two-blade NACA 10-(3)(062)-045 propeller and for the two-blade NACA 10-(3)(08)-045 propeller over a range of advance ratio from 0.5 to 3.8, through a blade-angle range from 20 degrees to 55 degrees measured at the 0.75 radius. Maximum efficiencies of the order of 91.5 to 92 percent were obtained for the propellers. The propeller with the thinner airfoil sections over the outboard portion of the blades, the NACA 10-(3)(062)-045 propeller, had lower losses at high tip speeds, the difference amounting to about 5 percent at a helical tip Mach number of 1.10.
Contributing Partner: UNT Libraries Government Documents Department
The aerodynamic characteristics of an aspect-ratio-20 wing having thick airfoil sections and employing boundary-layer control by suction

The aerodynamic characteristics of an aspect-ratio-20 wing having thick airfoil sections and employing boundary-layer control by suction

Date: August 1953
Creator: Cocke, Bennie W , Jr & Fink, Marvin P
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics of damping screens

Aerodynamic characteristics of damping screens

Date: January 1950
Creator: Schubauer, G B; Spangenberg, W G & Klebanoff, P S
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics of NACA 0012 airfoil section at angles of attack from 0 degrees to 180 degrees

Aerodynamic characteristics of NACA 0012 airfoil section at angles of attack from 0 degrees to 180 degrees

Date: January 1955
Creator: Critzos, Chris C; Heyson, Harry H & Boswinkle, Robert W , Jr
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics of several 6-percent-thick airfoils at angles of attack from 0 degrees to 20 degrees at high subsonic speeds

Aerodynamic characteristics of several 6-percent-thick airfoils at angles of attack from 0 degrees to 20 degrees at high subsonic speeds

Date: May 1955
Creator: Daley, Bernard N & Lord, Douglas R
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics of the NACA 64-010 and 0010-1.10 40/1.051 airfoil sections at Mach numbers from 0.30 to 0.85 and Reynolds numbers from 4.0 x 10(exp. 6) to 8.0 x 10(exp. 6)

Aerodynamic characteristics of the NACA 64-010 and 0010-1.10 40/1.051 airfoil sections at Mach numbers from 0.30 to 0.85 and Reynolds numbers from 4.0 x 10(exp. 6) to 8.0 x 10(exp. 6)

Date: August 1954
Creator: Loftin, Laurence K , Jr
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics of three deep-step planing-tail flying-boat hulls and a transverse-step hull with extended afterbody

Aerodynamic characteristics of three deep-step planing-tail flying-boat hulls and a transverse-step hull with extended afterbody

Date: August 1952
Creator: Riebe, John M & Naeseth, Rodger L
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic coefficients for an oscillating airfoil with hinged flap, with tables for a Mach number of 0.7

Aerodynamic coefficients for an oscillating airfoil with hinged flap, with tables for a Mach number of 0.7

Date: October 1950
Creator: Turner, M J & Rabinowitz, S
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The aerodynamic design and calibration of an asymmetric variable Mach number nozzle with a sliding block for the Mach number range 1.27 to 2.75

The aerodynamic design and calibration of an asymmetric variable Mach number nozzle with a sliding block for the Mach number range 1.27 to 2.75

Date: April 1953
Creator: Burbank, Paige B & Byrne, Robert W
Description: A method of designing as asymmetric, fixed geometry, variable Mach number nozzle has been developed by using the method of characteristics. A small nozzle conforming to the analytically determined ordinates was constructed and calibrated over a range of Mach numbers extending from 1.27 to 2.75. The results show the variation in Mach number to be plus or minus 0.01 or less and in the flow direction to be plus or minus 0.2 degrees within the test section. The range of Mach numbers from 1.27 to 2.75 was obtained by translating the lower block in a straight line parallel to the test-section center line for a distance of 2.17 test-section heights.
Contributing Partner: UNT Libraries Government Documents Department
The aerodynamic design of high Mach number nozzles utilizing axisymmetric flow with application to a nozzle of square test section

The aerodynamic design of high Mach number nozzles utilizing axisymmetric flow with application to a nozzle of square test section

Date: June 1952
Creator: Beckwith, Ivan E; Ridyard, Herbert W & Cromer, Nancy
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The aerodynamic design of supersonic propellers from structural considerations

The aerodynamic design of supersonic propellers from structural considerations

Date: December 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 1958
Creator: Gray, Vernon H. & vonGlahn, Uwe 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 1950
Creator: Stone, Ralph W , Jr; Burk, Sanger M , Jr & Bihrle, William, 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 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 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 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 1954
Creator: Mclemore, H Clyde & Cannon, Michael D
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 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 1954
Creator: Kelly, John A & Mccullough, George B
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 1956
Creator: Mickelson, William R & Baldwin, Lionel V
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
Aerodynamics of a rectangular wing of infinite aspect ratio at high angles of attack and supersonic speeds

Aerodynamics of a rectangular wing of infinite aspect ratio at high angles of attack and supersonic speeds

Date: July 1955
Creator: Martin, John C & Malvestuto, Frank S , Jr
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamics of slender wings and wing-body combinations having swept trailing edges

Aerodynamics of slender wings and wing-body combinations having swept trailing edges

Date: March 1954
Creator: Mirels, Harold
Description: None
Contributing Partner: UNT Libraries Government Documents Department
An air-flow-direction pickup suitable for telemetering use on pilotless aircraft

An air-flow-direction pickup suitable for telemetering use on pilotless aircraft

Date: October 1956
Creator: Ikard, Wallace L
Description: A vane-type air-flow-direction pickup is described which is suitable for telemetering angle-of-attack and angle-of-sideslip data from rocket-propelled pilotless aircraft models. Test results which are presented show that the device performs well under high accelerations and is stable throughout a Mach number rage from subsonic to above a Mach number of 2.5.
Contributing Partner: UNT Libraries Government Documents Department
Air forces and moments on triangular and related wings with subsonic leading edges oscillating in supersonic potential flow

Air forces and moments on triangular and related wings with subsonic leading edges oscillating in supersonic potential flow

Date: September 1951
Creator: Watkins, Charles E
Description: None
Contributing Partner: UNT Libraries Government Documents Department