by National Aeronautics and Space Administration, Scientific and Technical Information Branch, For sale by the National Technical Information Service] in [Washington, D.C.], [Springfield, Va .
Written in English
|Statement||David E. Reubush and E. Ann Bare|
|Series||NASA technical memorandum -- 86361|
|Contributions||Bare, E. Ann, United States. National Aeronautics and Space Administration. Scientific and Technical Information Division|
|The Physical Object|
An investigation was conducted in the Langley Foot Transonic Tunnel to survey the flow field around a model of a supersonic cruise fighter configuration. Local values of angle of attack, side flow, Mach number, and total pressure ratio were measured with a single multi-holed probe in three survey areas on a model previously used for nacelle Author: D. E. Reubush and E. A. Bare. A NASA Langley investigation was conducted in the foot Transonic Tunnel to survey the flow field around a model of a Supersonic cruise fighter configuration. In this investigation, a model of a. Investigation of a supersonic cruise fighter model flow field / By David E. Reubush, E. Ann. Bare and Langley Research Center. Abstract. Prepared at Langley Research Center."November "es bibliographical references (p. 8).Mode of access: Internet. Measurement of aerodynamic forces. Air velocity and pressures are measured in several ways in wind tunnels. Air velocity through the test section is determined by Bernoulli's ement of the dynamic pressure, the static pressure, and (for compressible flow only) the temperature rise in the airflow. The direction of airflow around a model can be determined by tufts of yarn attached.
A Theoretical Investigation of Supersonic jets in Subsonic Flow Fields by c. Young by the fan efflux of a high bypass ratio engine at cruise Mach number, A method of calculating the pressure distribution on the gas generator would be stant in the entire flow field. Two-dimensional flow. Magnetohydrodynamic (MHD) power generation with supersonic non-equilibrium plasma is demonstrated. Capacitively coupled radio frequency (RF) discharge (6 MHz, maximum continual power output of W) was adopted to ionize the Mach number ( m/s), kg/m 3 airflow. In a MHD channel of 16 mm × 10 mm × 20 mm, MHD open voltage of 10 V is realized in the magnetic field of . The first turbojet fighter developed by Mikoyan-Gurevich OKB was the Mikoyan-Gurevich MiG-9, which appeared in the years immediately after World War used a pair of reverse-engineered German BMW engines. The MiG-9 was a troublesome design that suffered from weak, unreliable engines and control problems. Categorized as a first-generation jet fighter, it was designed with the straight. At supersonic flight Mach numbers the adiabatic compression of the flow by the shock waves in the inlet system results in an increase in temperature at the entrance to the compressor section (station 2) while leaving the stagnation enthalpy unchanged from its free stream value. Assuming, for the moment, that the ratio of specific heats remains constant permits us to calculate the stagnation.
Experimental investigation of flame-holding capability of hydrogen transverse jet in supersonic cross-flow Symposium (International) on Combustion, Vol. 27, No. 2 Control of Flame-Holding in Supersonic Airflow by Secondary Air Injection. Get this from a library! Theoretical and experimental flow fields for a supersonic cruise fighter forebody. [Steven F Yaros; United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch.]. American Institute of Aeronautics and Astronautics Sunrise Valley Drive, Suite Reston, VA A supersonic aircraft is an aircraft able to fly faster than the speed of sound (Mach number 1). Supersonic aircraft were developed in the second half of the twentieth century and have been used almost entirely for research and military purposes. Only two, Tupolev Tu (first flight - Decem ) and the Concorde (first flight - March 2, ), ever entered service for civil use as.