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Pulse Amplifiers Using Transistor Circuits

Description: From Introduction: "The high frequency response remains important even when pulse shaping is introduced. Pulse shaping is used to improve the time resolution of the system, to minimize overload distortion, or to facilitate the action of discriminating and recording circuits. The amplifier response may be optimized by such shaping, but in general the overall characteristics will be fixed by the particular detector system."
Date: January 23, 1958
Creator: Graveson, R. T. & Sadowski, H.
Item Type: Report
Partner: UNT Libraries Government Documents Department

Engineering Test Reactor Critical Facility Hazards Summary Report, Supplement I

Description: Report that "is a supplement to IDO-16332, "The Engineering Test Reactor Critical Facility Hazards Summary Report", presenting information on the conduct in the Facility of certain experiments which are expected to be operated in the Engineering Test Reactor" (p. 3).
Date: January 24, 1958
Creator: DeBoisblanc, D. R.; Burdick, Earl E. & DeBoer, T. K.
Item Type: Report
Partner: UNT Libraries Government Documents Department

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

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 amounted to as much as 9 percent for an icing time of 8 minutes. Pitching-moment-coefficient changes in icing conditions were somewhat erratic and depended on the icing condition. Rotation of the iced airfoil to angles of attack other than that at which icing occurred caused sufficiently large changes in the pitching-moment coefficient that, in flight, rapid corrections in trim might be required in order to avoid a hazardous situation.
Date: February 1958
Creator: Gray, Vernon H. & vonGlahn, Uwe H.
Item Type: Report
Partner: UNT Libraries Government Documents Department

Compilation of information on the transonic attachment of flows at the leading edges of airfoils

Description: Schlieren photographs have been compiled of the two-dimensional flow at transonic speeds past 37 airfoils. These airfoils have variously shaped profiles, and some are related in thickness and camber. The data for these airfoils were analyzed to provide basic information on the flow changes involved and to determine factors affecting transonic-flow attachment, which is a transition from separated to unseparated flow at the leading edges of two-dimensional airfoils at fixed angles as the subsonic Mach number is increased.
Date: February 1, 1958
Creator: Lindsey, Walter F & Landrum, Emma Jean
Item Type: Report
Partner: UNT Libraries Government Documents Department

Correlations Among Ice Measurements, Impingement Rates Icing Conditions, and Drag Coefficients for Unswept NACA 65A004 Airfoil

Description: An empirical relation has been obtained by which the change in drag coefficient caused by ice formations on an unswept NACA 65AO04 airfoil section can be determined from the following icing and operating conditions: icing time, airspeed, air total temperature, liquid-water content, cloud droplet impingement efficiencies, airfoil chord length, and angles of attack. The correlation was obtained by use of measured ice heights and ice angles. These measurements were obtained from a variety of ice formations, which were carefully photographed, cross-sectioned, and weighed. Ice weights increased at a constant rate with icing time in a rime icing condition and at progressively increasing rates in glaze icing conditions. Initial rates of ice collection agreed reasonably well with values predicted from droplet impingement data. Experimental droplet impingement rates obtained on this airfoil section agreed with previous theoretical calculations for angles of attack of 40 or less. Disagreement at higher angles of attack was attributed to flow separation from the upper surface of the experimental airfoil model.
Date: February 1, 1958
Creator: Gray, Vernon H.
Item Type: Report
Partner: UNT Libraries Government Documents Department