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Aerodynamic heating is the heating of a solid body produced by its high-speed passage through air. In science and engineering, an understanding of aerodynamic heating is necessary for predicting the behaviour of meteoroids which enter the Earth's atmosphere, to ensure spacecraft safely survive atmospheric reentry, and for the design of high-speed aircraft and missiles.
When the speed is reduced and the aircraft approaches stall, the local flow at the leading edge is diverted outwards; this spanwise component of velocity around the vortilon creates a vortex streamed around the top surface, which energises the boundary layer. [6] A more turbulent boundary layer, in turn, delays the local flow separation.
These are the Aerodynamic Heating Facility (AHF), the Turbulent Flow Duct (TFD), the Panel Test Facility (PTF), and the Interaction Heating Facility (IHF). The support equipment includes two D.C. power supplies, a steam ejector-driven vacuum system, a water-cooling system, high-pressure gas systems, data acquisition system, and other auxiliary ...
The Fay-Riddell equation is widely used in the design and analysis of thermal protection systems for re-entry vehicles. [3] [4] [5] It provides engineers with a crucial tool for estimating the severe aerodynamic heating conditions encountered during atmospheric entry and for designing appropriate thermal protection measures.
The Meredith effect is a phenomenon whereby the aerodynamic drag produced by a cooling radiator may be offset by careful design of the cooling duct such that useful thrust is produced by the expansion of the hot air in the duct. The effect was discovered in the 1930s and became more important as the speeds of piston-engined aircraft increased ...
Begun in 1960, ASSET was originally designed to verify the superalloy heat shield of the X-20 Dyna-Soar prior to full-scale crewed flights. The vehicle's biconic shape and low delta wing were intended to represent Dyna-Soar's forward nose section, where the aerodynamic heating would be the most intense; in excess of an estimated 2200 °C (4000 °F) at the nose cap.
The first manufactured object to achieve hypersonic flight was the two-stage Bumper rocket, consisting of a WAC Corporal second stage set on top of a V-2 first stage. In February 1949, at White Sands, the rocket reached a speed of 8,290 km/h (5,150 mph), or about Mach 6.7. [2]
Kinetic heating from the high speed boundary layer caused the skin to heat up during supersonic flight. [105] Every surface, such as windows and panels, was warm to the touch by the end of the flight. [106] Apart from the engine bay, the hottest part of any supersonic aircraft's structure is the nose, due to aerodynamic heating.
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