in this paper a method is outlined to compute wall-interferenee in closedlow speed wind tunnel for 3D high lift test using wall pressure at optimum points andthe influence function (WPIF method for short). The experim...in this paper a method is outlined to compute wall-interferenee in closedlow speed wind tunnel for 3D high lift test using wall pressure at optimum points andthe influence function (WPIF method for short). The experimental results of a high liftmodel in small wind tunnel are corrected by applying the WPIF method. The correctedresults are compared with the wall interference-free data of this high lift model in largewind tunnel. It is shown that the WPIF method is desirable for the correction of lift,drag and pitch moment.展开更多
The effect of the size of a delta wing relative to that of the test section on the vortex breakdown location over a delta wing oscillating in pitch to very high angles of attack was ...The effect of the size of a delta wing relative to that of the test section on the vortex breakdown location over a delta wing oscillating in pitch to very high angles of attack was investigated experimentally using flow visualization. The unsteady wall pressure characteristics such as delay, frequency were analyzed. An unsteady tunnel wall correction, applying influence functions in steady wall pressure correction method and unsteady wall pressure at the optimum points, was presented. Experimental examinations prove that the unsteady tunnel wall correction is desirable.展开更多
The correction method uses the static pressures measured near the tunnelwalls during model tests as boundary conditions. It is required that the flow near thewalls is subsonic and the freestream Mach number is less th...The correction method uses the static pressures measured near the tunnelwalls during model tests as boundary conditions. It is required that the flow near thewalls is subsonic and the freestream Mach number is less than 1. It is still valid whenthere are shock waves and supersonic pockets near the model as long as shock waves donot extend to walls, and the method is applicable to various ventilated wall or solid walltest sections. Corrections for three models tested abroad are in quite good agreementwith NASA's results, which are obtained by a nonhnear correction method. Thepresnet method has been apphed to B737 inodel tcsted in CARDC 1.2 m wind tunnel.The results show that this method is suitable for transonic wall interference correctionfor high aspect ratio airplane tests.展开更多
文摘in this paper a method is outlined to compute wall-interferenee in closedlow speed wind tunnel for 3D high lift test using wall pressure at optimum points andthe influence function (WPIF method for short). The experimental results of a high liftmodel in small wind tunnel are corrected by applying the WPIF method. The correctedresults are compared with the wall interference-free data of this high lift model in largewind tunnel. It is shown that the WPIF method is desirable for the correction of lift,drag and pitch moment.
文摘The effect of the size of a delta wing relative to that of the test section on the vortex breakdown location over a delta wing oscillating in pitch to very high angles of attack was investigated experimentally using flow visualization. The unsteady wall pressure characteristics such as delay, frequency were analyzed. An unsteady tunnel wall correction, applying influence functions in steady wall pressure correction method and unsteady wall pressure at the optimum points, was presented. Experimental examinations prove that the unsteady tunnel wall correction is desirable.
文摘The correction method uses the static pressures measured near the tunnelwalls during model tests as boundary conditions. It is required that the flow near thewalls is subsonic and the freestream Mach number is less than 1. It is still valid whenthere are shock waves and supersonic pockets near the model as long as shock waves donot extend to walls, and the method is applicable to various ventilated wall or solid walltest sections. Corrections for three models tested abroad are in quite good agreementwith NASA's results, which are obtained by a nonhnear correction method. Thepresnet method has been apphed to B737 inodel tcsted in CARDC 1.2 m wind tunnel.The results show that this method is suitable for transonic wall interference correctionfor high aspect ratio airplane tests.
