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Release of the X-15 from NB-52A took place at an altitude of about 8.5 miles (13.7 km) (45,000 feet) and a speed of about 500 miles per hour (805 km/h). [8] The X-15 fuselage was long and cylindrical, with rear fairings that flattened its appearance, and thick, dorsal
where a 0 is 1,225 km/h (661.45 kn) (the standard speed of sound at 15 °C), M is the Mach number, P is static pressure, and P 0 is standard sea level pressure (1013.25 hPa). Combining the above with the expression for Mach number gives EAS as a function of impact pressure and static pressure (valid for subsonic flow):
TAS can be calculated as a function of Mach number and static air temperature: =, where is the speed of sound at standard sea level (661.47 knots (1,225.04 km/h; 340.29 m/s)),
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.
The flights of the North American X-15, an experimental American spaceplane built by North American Aviation and operated by the United States Air Force and NASA, were conducted from 1959 to 1968. Twelve pilots flew three X-15 spaceplanes, flying record high-altitude flights, high-speed flights, and sub-orbital spaceflights .
In November 1961, Air Force Major Robert White flew the X-15 research aircraft at speeds over Mach 6. [4] [5] On 3 October 1967, in California, an X-15 reached Mach 6.7. [6] The reentry problem of a space vehicle was extensively studied. [7] The NASA X-43A flew on scramjet for 10 seconds, and then glided for 10 minutes on its last flight in 2004.
The external tanks were jettisoned 67.4 seconds after launch at a speed of Mach 2.0 and 70,000 feet. The total engine burn time during the flight was 141.4 seconds. After Flight 188, 11 more X-15 flights were made before the program was retired. The X-15 program data was used in the planning of future aircraft and spacecraft designs.
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.