Avigit Aerospace

Avigit Aerospace For the purpose of improving the competitiveness and quality of its equipment and services, Gamesa has several R+D centres woroldwide. In these technologic

27/06/2016

Energy -XS Vertical axis wind turbine - This is a moving mesh calculation for a high solidity vertical axis wind turbine. The solution was computed using OpenFOAM's pimpleDyMFoam solver. The computational domain consists of a rotating inner zone and a stationary out zone. The rotor solidity is 1.5 and operating at a tip speed ratio of 1.0. The blade cross section is the NACA 0015. Note, this is a 2D calculation.

The mesh was generated automatically using Pointwise and a custom Glyph script and consists of quads and triangles. As mentioned earlier, the solution was computed using the pimpleDyMFoam solver. Visualization was done in ParaView.

I hope you all enjoy the video. If you'd like to learn more about these types of simulations and wind turbine shape optimization, please visit http://www.hindawi.com/journals/isrn.... and check out my journal article. Thank you!

27/06/2016

Ramjet test facility in Chitose is a facility to simulate an actual flight environment (altitude and the Mach number) for next-generation supersonic engines and to evaluate their thermal aerodynamic characteristics etc. on the ground.
Main components of this facility are a compressor, air tanks, a burner, a cooler, a test chamber, a cooler for exhaust gas, ejectors, etc. High-pressure air generated by the compressor is accumulated in the air tanks and fed to an engine to be tested in a form of airflow corresponding to the actual flight speed. A temperature of the airflow can be set according to the actual flight environment by the burner or cooler. In addition, the exhaust gas from the engine can be cooled by the exhaust gas cooler and depressurized by the ejectors so that a pressure in the test chamber can be set according to the actual flight altitude.

27/06/2016

Ramjet test facility in Bangalore is a facility to simulate an actual flight environment (altitude and the Mach number) for next-generation supersonic engines and to evaluate their thermal aerodynamic characteristics etc. on the ground.
Main components of this facility are a compressor, air tanks, a burner, a cooler, a test chamber, a cooler for exhaust gas, ejectors, etc. High-pressure air generated by the compressor is accumulated in the air tanks and fed to an engine to be tested in a form of airflow corresponding to the actual flight speed. A temperature of the airflow can be set according to the actual flight environment by the burner or cooler. In addition, the exhaust gas from the engine can be cooled by the exhaust gas cooler and depressurized by the ejectors so that a pressure in the test chamber can be set according to the actual flight altitude.

27/06/2016
17/05/2016
17/05/2016

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