Add to ORKGA numerical method of assessing the interference due to tunnel walls on flow past an airfoil in a wind tunnel from measurements on a control surface using the full potential equation, has been tried out on a few airfoils in this study. The interference corrections are compared with those by the other methods and the agreement is very good. The calculation is quite rapid and can be used in a routine manner to correct the data from the wind tunnel.13; 13
Tests were conducted on three NASA 0012 airfoil models. A range of Mach numbers from 0.6 to 0.9 and ...
The lift interference was calculated for a porous wall wind tunnel by a modified method of block cyc...
Tests have been made recent ly at ONERA on the interference effects arising from the presence of the...
A numerical method of assessing the interference due to tunnel walls on flow past an airfoil in a wi...
A code has been developed, based on the pressure measurements on the airfoil surface and the transon...
Wall interference problems in wind tunnel testing were discussed by many people. These are enough to...
Wall interference problems in wind tunnel testing were discussed by many people. These are enough to...
The wall interference is obtained for a wind tunnel of elliptic section for the two cases of closed ...
Abstract—Because support interference corrections are not prop-erly understood, engineers mostly rel...
Abstract: In the current research, the results of some wind tunnel experiments on a moving airfoil w...
Because support interference corrections are not properly understood, engineers mostly rely on expen...
Because support interference corrections are not properly understood, engineers mostly rely on expen...
A general solution is presented for determination of wind tunnel boundary-induced interference in tw...
This report outlines the development of a general theory for the calculation of the effect of the bo...
A method for analyzing wall interference is described which avoids the assumption of linear superpos...
Tests were conducted on three NASA 0012 airfoil models. A range of Mach numbers from 0.6 to 0.9 and ...
The lift interference was calculated for a porous wall wind tunnel by a modified method of block cyc...
Tests have been made recent ly at ONERA on the interference effects arising from the presence of the...
A numerical method of assessing the interference due to tunnel walls on flow past an airfoil in a wi...
A code has been developed, based on the pressure measurements on the airfoil surface and the transon...
Wall interference problems in wind tunnel testing were discussed by many people. These are enough to...
Wall interference problems in wind tunnel testing were discussed by many people. These are enough to...
The wall interference is obtained for a wind tunnel of elliptic section for the two cases of closed ...
Abstract—Because support interference corrections are not prop-erly understood, engineers mostly rel...
Abstract: In the current research, the results of some wind tunnel experiments on a moving airfoil w...
Because support interference corrections are not properly understood, engineers mostly rely on expen...
Because support interference corrections are not properly understood, engineers mostly rely on expen...
A general solution is presented for determination of wind tunnel boundary-induced interference in tw...
This report outlines the development of a general theory for the calculation of the effect of the bo...
A method for analyzing wall interference is described which avoids the assumption of linear superpos...
Tests were conducted on three NASA 0012 airfoil models. A range of Mach numbers from 0.6 to 0.9 and ...
The lift interference was calculated for a porous wall wind tunnel by a modified method of block cyc...
Tests have been made recent ly at ONERA on the interference effects arising from the presence of the...