The flow in wind tunnel past OAT15A profile has been computed with WJ-H, Sm95 and Sm97 turbulence models. In the computations made with Sm95 model, a too aft shock position was obtained on the profile at symmetry plane. The shock location was correctly predicted by Sm97, while the ...
1) airfoil wind tunnel 翼型风洞1. The measurement and control of the model attitude angle in airfoil wind tunnel test; 翼型风洞实验模型姿态角的测量与控制更多例句>> 2) airfoil wind tunnel test 翼型风洞试验3) rotor model wind tunnel test 旋翼模型风洞试验...
Wind tunnel investigation of supersonic wing-tail flutter A flutter model, consisting of a wing, horizontal tail, and splitter plate/fuselage mechanism, was tested in a 4-foot transonic tunnel in the Mach number range 1.1 to 1.3. Two types of flutter were encountered during the testing: a wi...
and Junqiang B., 2009, "A high-speed nature laminar flow airfoil and its experimental study in wind tunnel with nonintrusive measurement technique", Chinese Journal of Aeronautics, No. 22, pp. 225-229.Jun Z., Zhenghong, G., Hao, Z., Junqiang, B., A High-speed Nature Laminar ...
That is the reason to carry out wind tunnel tests on a NACA 633-418 airfoil with 18% relative thickness in the Stuttgart Laminar Wind Tunnel. The airfoil was tested in clean condition, but also with leading edge roughness and different heights and different positions of the vortex generators....
3) wind-tunnel tests/wraparound-fin 风洞试验/卷弧翼4) airfoil wind tunnel 翼型风洞 1. The measurement and control of the model attitude angle in airfoil wind tunnel test; 翼型风洞实验模型姿态角的测量与控制 更多例句>> 5) wind tunnel test 模型风洞试验 1. The wind pressure distribution...
Wind tunnel tests of the Ris-A1-18, Ris-A1-21 and Ris-A1-24 airfoils This report contains 2D measurements of the Ris-A1-18, Ris-A1-21 and Ris-A1-24 airfoils. The aerodynamic properties were derived from pressure measurements on the airfoil surface and in the wake. The VELUX open jet...
This report presents the results of the experimental investigation on a NAL-114-36-00 symmetric supercritical airfoil developed at NAL and tested in O.3m wind tunnel over a free stream Mach number range of 0.53 to 0.85 and angle of incidence range of 0° to 4°. Model surface pressures wer...
We present an experimental study which shows that the mechanism known as transient growth of energy, can cause flutter instability of a nonlinearly flexible airfoil at a wind velocity below the linear critical flutter velocity. A flap mounted upstream a flexible airfoil in a wind tunnel generates ...
A design of double-element airfoil is proposed for its use in the vertical axis wind turbine. The double-element airfoil system consists of a main airfoil ... PD Chougule,L Rosendahl,Soren R.K. Nielsen - 《Ships & Offshore Structures》 被引量: 1发表: 2015年 Wind Tunnel Testing of Multi...