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Positronic is a manufacturing company based in Springfield, Missouri. The company manufactures and supplies electronic connectors that are utilized in a variety of industries worldwide including military , aerospace , telecommunications , medical , industrial and test equipment among others.
The drag-divergence Mach number (not to be confused with critical Mach number) is the Mach number at which the aerodynamic drag on an airfoil or airframe begins to increase rapidly as the Mach number continues to increase. [1] This increase can cause the drag coefficient to rise to more than ten times its low-speed value.
Jack T. Gentry (born December 6, 1923, in Kansas City, Kansas, United States; died September 23, 2006, in Springfield, Missouri) was a World War II and Korean War veteran, a metallurgical engineer, and an entrepreneur. [1] He was the founder and former president of Positronic, a manufacturing company based in Springfield, Missouri. [2] [3]
Dimensionless numbers (or characteristic numbers) have an important role in analyzing the behavior of fluids and their flow as well as in other transport phenomena. [1] They include the Reynolds and the Mach numbers, which describe as ratios the relative magnitude of fluid and physical system characteristics, such as density, viscosity, speed of sound, and flow speed.
The subsonic speed range is that range of speeds within which, all of the airflow over an aircraft is less than Mach 1. The critical Mach number (Mcrit) is lowest free stream Mach number at which airflow over any part of the aircraft first reaches Mach 1. So the subsonic speed range includes all speeds that are less than Mcrit. Transonic: 0.8–1.2
Alfvén and Mach were physicists who studied shock waves. Along with the sonic Mach number, the Alfvén Mach number is frequently used to characterize shock fronts [1] [2] [3] and turbulence [4] [5] in magnetized plasmas. [6] [7] = where M A is the Alfvén Mach number, u is the flow velocity, and
Mach number is more useful, and most high-speed aircraft are limited to a maximum operating Mach number, also known as M MO. For example, if the M MO is Mach 0.83, then at 9,100 m (30,000 ft) where the speed of sound under standard conditions is 1,093 kilometres per hour (590 kn), the true airspeed at M MO is 906 kilometres per hour (489 kn).
In aerodynamics, the normal shock tables are a series of tabulated data listing the various properties before and after the occurrence of a normal shock wave. [1] With a given upstream Mach number, the post-shock Mach number can be calculated along with the pressure, density, temperature, and stagnation pressure ratios.