F322 航技研小型超音速実験機の推進系付き形態風洞試験

概要

論文の詳細を見る
Wind tunnel test of the Powered National Supersonic Transport was conducted in the transonic flow regime to investigate the engine/airframe interaction of an SST configuration with a propulsion system, and the mass flow rate of the airflow going through the flow-through nacelle was controlled by the plug system located behind the nacelle exit. In addition to the conventional force and pressure measurements, the pressure sensitive paint (PSP) technique was also applied to increase the data productivity of the experiment. The test results showed increase in the nacelle drag with the decrease in the mass flow of the flow-thorough nacelle, and the PSP measurements showed it was due to the strong compression region formed in front of the nacelle. The test results will be used in the development of the experimental transport and the validation of the CFD analysis.
日本流体力学会の論文
2001-07-31