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In the present study, an effort has been made to sequester automobile exhaust gases from a petroleum based engine using microalgae Scenedesmus quadricauda. The automobile selected for the present study was a two wheeler motorcycle. S. quadricauda was subjected to un-suspended/attached non-enclosure cultivation onto a silicone matrix coated stainless steel pipe, protracted to the motorcycle silencer outlet through which, the exhaust gases passed out. The automobile exhaust gases initially contained 13% of carbon dioxide, 2.4% of carbon monoxide, 0.2% of nitric oxide, 0.08% of nitrogen dioxide, 0.1% of sulfur dioxide and 0.05% of sulfur trioxide concentrations, which were removed up to 62, 57, 65, 66, 64 and 65% respectively by S. quadricauda from the attached growth experiment. The present study results showed that the exhaust gases played a crucial role in inducing biomass and lipid yields up to ≥2 and ≥ 0.6 g L − 1 respectively. The tolerance of S. quadricauda to the exhaust gas components' toxicity and its efficiency in treating them followed by the biomass and lipid productivities were better than anticipated in the present study.

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This article has been retracted. Please see the Retraction Notice for more detail: https://doi.org/10.1186/s42834-020-0046-z

Micro Vortex generators are very small components deployed on the wings to control airflow over the upper surface of the wing to affect the boundary layer over it. These are employed onto a Micro aerial vehicle (MAV) of fixed wing type with an S5010 which is a low Reynolds number airfoil. This airfoil provides good aerodynamic results as compared to many low Reynolds number airfoils. Micro vortex generators are used to enhance the performance through controlling airflow at different speeds and angle of attack. The comparison of a half part of the MAV wing which is designed in CATIA, with and without the vortex generators on its leading edge at 10% of its chord length is done to show how the vortex generators improve the performance and control authority at different speeds and angle of attacks. These are shown with the velocity and pressure distribution around the wing by considering laminar flow in the simulation.