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Investigation of the Boundary Condition at a Wind Tunnel Test Section Wall for a Lifting Wing-Body Model at Low Supersonic Speed

出版	Defense Technical Information Center, 1979
URL	http://books.google.com.hk/books?id=7oi6tgAACAAJ&hl=&source=gbs_api

註釋The purpose of the investigation is to study theoretically and experimentally at low supersonic speed the interference-free flow field around a lifting wing-body wind tunnel model at locations where the tunnel walls are normally situated. The undisturbed flow properties are used to establish criteria for cross flow characteristics of wave-attenuating ventilated wind tunnel walls. The flow field has been calculated theoretically by a relaxation method based on the transonic small perturbation (TSP) equation and for one sample case for the body alone with a method based on the solution of the full gas dynamic equations (the Euler equations) in a time-dependent finite volume formulation. A survey of the flow has been made experimentally with a probe in wind tunnel tests. Pressure and flow deflection in the flow field near a delta-wing-body configuration have been calculated at free stream Mach number 1.2 and at angles of attack of 0 deg and 5 deg. The same properties have been determined in wind tunnel tests at Mach number 1.15, 1.20 and 1.30 and at nominal angles of attack 0 deg, 5 deg, 15 deg and 25 deg. The theoretical results obtained using the TSP method show only qualitative agreement with experimental data and the shocks are smeared out. Theoretical results obtained by the time-dependent finite volume method for the body alone show promising agreement with experiments.