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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
Acoustic radiation from two-dimensional rectangular cutouts in aerodynamic surfaces

Acoustic radiation from two-dimensional rectangular cutouts in aerodynamic surfaces

Date: August 1955
Creator: Krishnamurty, K
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Acoustic, thrust, and drag characteristics of several full-scale noise suppressors for turbojet engines

Acoustic, thrust, and drag characteristics of several full-scale noise suppressors for turbojet engines

Date: April 1958
Creator: Ciepluch, Carl C; North, Warren J; Coles, Willard D & Antl, Robert J
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Acoustical treatment for the NACA 8- by 6-foot supersonic propulsion wind tunnel

Acoustical treatment for the NACA 8- by 6-foot supersonic propulsion wind tunnel

Date: June 1955
Creator: Beranek, Leo L; Labate, Samuel & Ingard, Uno
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Additional static and fatigue tests of high-strength aluminum-alloy bolted joints

Additional static and fatigue tests of high-strength aluminum-alloy bolted joints

Date: July 1954
Creator: Hartmann, E C; Holt, Marshall & Eaton, I D
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The aerodynamic behavior of a harmonically oscillating finite sweptback wing in supersonic flow

The aerodynamic behavior of a harmonically oscillating finite sweptback wing in supersonic flow

Date: October 1951
Creator: Chang, Chieh-Chien
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics and flying qualities of a tailless triangular-wing airplane configuration as obtained from flights of rocket-propelled models at transonic and supersonic speeds

Aerodynamic characteristics and flying qualities of a tailless triangular-wing airplane configuration as obtained from flights of rocket-propelled models at transonic and supersonic speeds

Date: November 1956
Creator: Mitcham, Grady L; Stevens, Joseph E & Norris, Harry P
Description: A flight investigation of rocket-powered models of a tailless triangular-wing airplane configuration was made through the transonic and low supersonic speed range at the Langley Pilotless Aircraft Research Station at Wallops Island, Va. An analysis of the aerodynamic coefficients, stability derivatives, and flying qualities based on the results obtained from the successful flight tests of three models is presented.
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics at Reynolds numbers of 3.0 x 10(exp 6) and 6.0 x 10(exp 6) of three airfoil sections formed by cutting off various amounts from the rear portion of the NACA 0012 airfoil section

Aerodynamic characteristics at Reynolds numbers of 3.0 x 10(exp 6) and 6.0 x 10(exp 6) of three airfoil sections formed by cutting off various amounts from the rear portion of the NACA 0012 airfoil section

Date: April 1950
Creator: Smith, Hamilton A & Schaefer, Raymond F
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics of a circular cylinder at Mach number 6.86 and angles of attack up to 90 degrees

Aerodynamic characteristics of a circular cylinder at Mach number 6.86 and angles of attack up to 90 degrees

Date: January 1957
Creator: Penland, Jim A
Description: Pressure-distribution and force tests of a circular cylinder have been made in the Langley 11-inch hypersonic tunnel at a Mach number of 6.88, a Reynolds number of 129,000, and angles of attack up to 90 degrees. The results are compared with the hypersonic approximation of Grimminger, Williams, and Young and a simple modification of the Newtonian flow theory. An evaluation of the crossflow theory is made through comparison of present results with available crossflow Mach number drag coefficients.
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics of a refined deep-step planing-tail flying-boat hull with various forebody and afterbody shapes

Aerodynamic characteristics of a refined deep-step planing-tail flying-boat hull with various forebody and afterbody shapes

Date: June 1952
Creator: Riebe, John M & Naeseth, Rodger L
Description: An investigation was made in the Langley 300-mph 7- by 10-foot tunnel to determine the aerodynamic characteristics of a refined deep-step planing-tail hull with various forebody and afterbody shapes and, for comparison, a streamline body simulating the fuselage of a modern transport airplane. The results of the tests indicated that the configurations incorporating a forebody with a length-beam ratio of 7 had lower minimum drag coefficients than the configurations incorporating a forebody with length-beam ratio of 5. The lowest minimum drag coefficients, which were considerably less than that of a conventional hull and slightly less than that of a streamline body, were obtained on the length-beam-ratio-7 forebody, alone and with round center boom. Drag coefficients and longitudinal- and lateral-stability parameters presented include the interference of a 21-percent-thick support wing.
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics of a small-scale shrouded propeller at angles of attack from 0 to 90 degrees

Aerodynamic characteristics of a small-scale shrouded propeller at angles of attack from 0 to 90 degrees

Date: November 1955
Creator: Parlett, Lysle P
Description: None
Contributing Partner: UNT Libraries Government Documents Department
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