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Analysis of spanwise temperature distribution in three types of air-cooled turbine blade

Description: From Summary: An approximate method for determining the allowable stress-limited blade-temperature distribution is included, with brief accounts of a method for determining the maximum allowable effective gas temperatures and the cooling-air requirements. Numerical examples that illustrate the use of the various temperature-distribution equations and of the nondimensional charts are also included.
Date: March 1, 1950
Creator: Livingood, John N. B. & Brown, W. Byron
Partner: UNT Libraries Government Documents Department
open access

Characteristics of loads in rough air at transonic speeds of rocket-powered models of a canard and a conventional-tail configuration

Description: Report presenting results from flight tests at transonic speeds for a canard and a conventional-tail rocket-powered model in continuous rough air. The use of an airspeed-fluctuation instrument for measuring the turbulence intensity experienced is described as well as the resulting improvement in the technique of testing rocket models in rough air. The short-period frequency was dominant in the center-of-gravity normal-acceleration response for both models.
Date: March 1, 1955
Creator: Vitale, A. James
Partner: UNT Libraries Government Documents Department
open access

Error in Airspeed Measurement Due to Static-Pressure Field Ahead of the Wing Tip of a Swept-Wing Airplane Model at Transonic Speeds

Description: From Summary: "As part of a study of means of airspeed measurement at transonic speeds the use of static orifices located ahead of the wing tip has been investigated for possible application to service or research airspeed installations. The local static pressure and local Mach number have been measured at a distance of 1 tip chord ahead of the wing tip of a model of a swept-wing fighter airplane at true Mach numbers between 0.7 and 1.08 by the NACA wing-flow method. All measurements were made … more
Date: March 1, 1951
Creator: Danforth, Edward C. B. & O'Bryan, Thomas C.
Partner: UNT Libraries Government Documents Department
open access

The Hydrodynamic Force Characteristics of Streamline Bodies of Revolution Having Fineness Ratios of 6, 9, and 12 With and Without Chine Strips

Description: Report presenting hydrodynamic force characteristic for three streamline bodies of revolution equipped with chine strips and with fineness ratios of 6, 9, and 12. Testing was also performed on the bodies with the chine strips removed and with the tail cones removed. Hydrodynamic resistance, pitching moment, wetted length, and height of the model above the water surface for a range of trim, load, and speed are provided.
Date: March 1, 1955
Creator: Weinflash, Bernard & Fontana, Rudolph E.
Partner: UNT Libraries Government Documents Department
open access

Low-speed wind-tunnel investigation of leading-edge porous suction on a 4-percent-thick 60 degree delta wing

Description: Report presenting testing of a 60-degree delta-wing-fuselage model with a 4-percent-thick airfoil section with large leading-edge radius in the 19-foot pressure tunnel to determine the effectiveness of porous-leading-edge suction in delaying and reducing the leading-edge separation and accompanying high drag. Results regarding the delta wing, including pump power, lift, pitching moment, pressure distributions, the clipped wing, and some comments on the application of leading-edge suction to del… more
Date: March 1, 1955
Creator: Yates, E. Carson, Jr.
Partner: UNT Libraries Government Documents Department
open access

Minimum-drag ducted and pointed bodies of revolution based on linearized supersonic theory

Description: The linearized drag integral for bodies of revolution at supersonic speeds is presented in a double-integral form which is not based on slender-body approximations but which reduces to the equal slender-body expression in the proper limit. With the aid of a suitably chosen auxiliary condition, the minimum-external-wave-drag problem is solved for a transition section connecting two semi-infinite cylinders. The projectile tip is a special case and is compared with the Von Karman projectile tip. C… more
Date: March 1, 1954
Creator: Parker, Hermon M.
Partner: UNT Libraries Government Documents Department
open access

Model investigation of the effect of mounting hydro-skis on shock absorbers

Description: Report presenting a rough-water landing investigation of a model of a hydro-ski seaplane design to determine the effect on the landing motions and vertical accelerations of mounting the hydro-ski on shock-absorber struts. The tests occurred at one landing trim and wave height over a range of wave length for three hydro-ski configurations. Results regarding the landings, effect of artificial stabilization, damping in trim, and reductions in vertical accelerations are provided.
Date: March 1, 1955
Creator: Hoffman, Edward L. & Fisher, Lloyd J.
Partner: UNT Libraries Government Documents Department
open access

Preliminary investigation of the delay of turbulent flow separation by means of wedge-shaped bodies

Description: Report presenting an experimental investigation of pyramidal, wedge-like bodies as devices for delaying separation of a turbulent boundary layer. Within certain limits, effective boundary-layer control was obtainable with wedges of different geometry, but the drag of the wedges was high, making it desirable to keep their size to a minimum. Greater maximum lift was obtainable by placing the wedges well forward along the chord and by allowing open spaces between adjacent wedges.
Date: March 1, 1951
Creator: McCullough, George B.; Nitzberg, Gerald E. & Kelly, John A.
Partner: UNT Libraries Government Documents Department
open access

Summary of Spin and Recovery Characteristics of 12 Models of Flying-Wing and Unconventional-Type Airplanes

Description: Report presenting a compilation of free-spinning model results of investigations of the spin and recovery characteristics of 12 flying-wing and unconventional-type designs. Dimensional data, mass data, and three-view drawings of the models that correspond to each of the 12 airplane designs are provided. Results regarding erect spins, inverted spins, and spin-recovery parachutes are also provided.
Date: March 1, 1951
Creator: Stone, Ralph W., Jr. & Hultz, Burton E.
Partner: UNT Libraries Government Documents Department
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