A study of polymers containing silicon- nitrogen bonds progress report, nov. 4 - dec. 3, 1964

Polymers containing silicon-nitrogen bonds as liquid and plastic materials in space and aviation technolog

Predicted performance benefits of an adaptive digital engine control system of an F-15 airplane

The highly integrated digital electronic control (HIDEC) program will demonstrate and evaluate the improvements in performance and mission effectiveness that result from integrating engine-airframe control systems. Currently this is accomplished on the NASA Ames Research Center's F-15 airplane. The two control modes used to implement the systems are an integrated flightpath management mode and in integrated adaptive engine control system (ADECS) mode. The ADECS mode is a highly integrated mode in which the airplane flight conditions, the resulting inlet distortion, and the available engine stall margin are continually computed. The excess stall margin is traded for thrust. The predicted increase in engine performance due to the ADECS mode is presented in this report

A study of polymers containing silicon- nitrogen bonds Annual summary report, May 4, 1965 - May 3, 1966

Polymers containing silicon-nitrogen bonds as elastomers with high thermal stability for aerospace application

The Institute of Archaeology & Siegfried H. Horn Museum Newsletter Volume 37.1

San Miceli 2015, Randall W. Younker ASOR 2015, Paul J. Ray, Jr. Random Surveyhttps://digitalcommons.andrews.edu/iaham-news/1065/thumbnail.jp

Institute of Archaeology & Horn Archaeological Museum Newsletter Volume 26.2

Madaba Museum Database Project, Randall W. Younker Administrative Wing Finished, Paul J. Ray, Jr. Photo Essay Be Our Partner Random Surveyhttps://digitalcommons.andrews.edu/iaham-news/1022/thumbnail.jp

The Institute of Archaeology & Siegfried H. Horn Museum Newsletter Volume 32.1

ASOR 2010 Annual Meeting, Paul J. Ray, Jr. Treasures of Jordan, Randall W. Younker Random Surveyhttps://digitalcommons.andrews.edu/iaham-news/1045/thumbnail.jp

High Reynolds number tests of a Boeing BAC I airfoil in the Langley 0.3-meter transonic cryogenic tunnel

A wind tunnel investigation of an advanced-technology airfoil was conducted in the Langley 0.3-Meter Transonic Cryogenic Tunnel (TCT). This investigation represents the first in a series of NASA/U.X. industry two dimensional airfoil studies to be completed in the Advanced Technology Airfoil Test program. Test temperature was varied from ambient to about 100 K at pressures ranging from about 1.2 to 6.0 atm. Mach number was varied from about 0.40 to 0.80. These variables provided a Reynolds number (based on airfoil chord) range from about .0000044 to .00005. This investigation was specifically designed to: (1) test a Boeing advanced airfoil from low to flight-equivalent Reynolds numbers; (2) provide the industry participant (Boeing) with experience in cryogenic wind-tunnel model design and testing techniques; and (3) demonstrate the suitability of the 0.3-m TCT as an airfoil test facility. All the objectives of the cooperative test were met. Data are included which demonstrate the effects of fixed transition, Mach number, and Reynolds number on the aerodynamic characteristics of the airfoil. Also included are remarks on the model design, the model structural integrity, and the overall test experience