Numéro : 2175 - Year : 1992

Application of a full potential code for definition of a transonic test section

X. VAUCHERET, OFFICE NATIONAL D'ETUDES ET DE RECHERCHES AEROSPATIALES (ONERA)
R. PICHON, OFFICE NATIONAL D'ETUDES ET DE RECHERCHES AEROSPATIALES (ONERA)

The N.2 test section of the S1 Modane wind tunnel, 14 meters in length and 8 meters in diameter, until now restricted to special low speed tests, will be transformed into an additional transonic test section. The areas of high-quality flow are defined, i. e. those areas with gradients less or equal to 0.001 for the Mach number and 0.01 degree for the angle of attack and the sideslip. The size of this area is optimised to permit testing of large sting-mounted civil aircraft models 5 meters long or of half models mounted from the floor and for Mach numbers reaching 0.95. Joining transition sections between the circular convergent nozzle and diffuser and the test section, which is a dodecagon, have been defined with care. The flow into the test section is determined with a structured progressive mesh of 80,000 hexahedrons. The full potential code authorizes shocks of weak intensity.

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