Mathematical expressions are presented for predicting pressures and heating rates resulting from three-dimensional shock wave-turbulent boundary layer interactions created by a sharp unswept fin adjacent to a flat surface and at various angles to a high speed flow. The new expressions are based on correlation of 3-D flow interaction pressure and heating test data and include those expressions for initial peak pressures and heating rates, located upstream of the shock wave, for higher peak pressures and heating rates, located downstream of the shock wave, and for the extent of flow disturbance. These expressions provide methods for obtaining 3-D interaction pressure and heating profiles when the freestream flow parameters, the fin location, and the fin deflection angles are specified. The methods improve capabilities for designing high speed aircraft configurations with minimum 3-D interaction heating and aircraft structures with minimum weight for protecting the regions where the 3-D interaction heating occurs.(Kursetz)
Expressions for predicting 3-D shock wave-turbulent boundary layer interaction pressures and heating rates
Mathematischer Ausdruck der Vorbestimmung einer dreidimensionalen Stosswelle. Wechselwirkung von turbulenten Grenzschichten sowie Druck- und Erwaermungsmessgroessen
AIAA-Papers ; 1-12
1978
12 Seiten, 15 Bilder, 1 Tabelle, 21 Quellen
Conference paper
English
AERODYNAMIK , MACH-ZAHL , STROEMUNGSGLEICHUNG , TURBULENTE STROEMUNG , GRENZSCHICHTSTROEMUNG , STROEMUNGSGESCHWINDIGKEIT , DREIDIMENSIONALE STROEMUNG , STOSSWELLE , STOSSBELASTUNG , TEMPERATURBEREICH , DRUCKAENDERUNG , STROEMUNGSVORGANG , TRAGFLUEGELUMSTROEMUNG , FLUGZEUGZELLE , FLUGZEUGBAU , MATHEMATISCHES VERFAHREN