In this paper,a series of low-Reynolds number airfoils were explored in application to the Long-Endurance Mars Exploration Flying Vehicle(LEMFEV)project.The end goal of the study was twofold:–to identify the most eff...In this paper,a series of low-Reynolds number airfoils were explored in application to the Long-Endurance Mars Exploration Flying Vehicle(LEMFEV)project.The end goal of the study was twofold:–to identify the most effective airfoil or airfoil-boundary layer trip combination for the given aircraft in cruise and unveil the underlying physical mechanism for this effectiveness;–to determine if the operating range of angles of attack for the selected airfoil could be expanded by placing the boundary layer trips in a relatively aft position such that they affected the boundary layer at a higher angle of attack.The paper presented two sample specifications for the LEMFEV project;discussed the effect of turbulence on the performance of airfoils under the given conditions;justified the selection of an amplification factor for simulations;developed and justified the measure of merit for airfoil selection and optimization;as well as considered boundary layer trips as a means of enhancing the performance of the selected airfoil.For design and analysis,MATLAB and X-FOIL were used.The analysis showed that for the given design conditions,both considered sample mission profiles were performed better by an airplane with the SD7037-092-88 airfoil.Furthermore,for this airfoil and design conditions,boundary layer trips would only increase drag at lift coefficients where they forced transition,and the boundary layer trips didn’t expand the airfoil’s operating range of angles of attack.In other words,eliminating the bubble had a detrimental effect on the lift-to-drag ratio of the airfoil.The friction drag increase due to early transition by far outweighed the pressure drag produced by the laminar bubble.展开更多
In this study,a rocket-based UAV and a solar wing-tail Martian UAV were designed and assessed against a set of criteria established using a house of quality chart.For the design,analysis,trade studies,and optimization...In this study,a rocket-based UAV and a solar wing-tail Martian UAV were designed and assessed against a set of criteria established using a house of quality chart.For the design,analysis,trade studies,and optimization,MATLAB and XFLR5 were used.The optimized versions of the two configurations feature the same wing and tail airfoils,the same wing and tail planforms,different dimensions,weight,and performance.Therefore,distinct types of scientific missions are suitable for these aircraft.The results of the study extend our understanding of the capabilities of a Martian fixed-wing airplane in terms of payload mass,hence its scientific value,as well as in terms of its planform geometry and airfoil shapes.展开更多
基金funded by the Russian Science Foundation,Grant number 22-49-02047.
文摘In this paper,a series of low-Reynolds number airfoils were explored in application to the Long-Endurance Mars Exploration Flying Vehicle(LEMFEV)project.The end goal of the study was twofold:–to identify the most effective airfoil or airfoil-boundary layer trip combination for the given aircraft in cruise and unveil the underlying physical mechanism for this effectiveness;–to determine if the operating range of angles of attack for the selected airfoil could be expanded by placing the boundary layer trips in a relatively aft position such that they affected the boundary layer at a higher angle of attack.The paper presented two sample specifications for the LEMFEV project;discussed the effect of turbulence on the performance of airfoils under the given conditions;justified the selection of an amplification factor for simulations;developed and justified the measure of merit for airfoil selection and optimization;as well as considered boundary layer trips as a means of enhancing the performance of the selected airfoil.For design and analysis,MATLAB and X-FOIL were used.The analysis showed that for the given design conditions,both considered sample mission profiles were performed better by an airplane with the SD7037-092-88 airfoil.Furthermore,for this airfoil and design conditions,boundary layer trips would only increase drag at lift coefficients where they forced transition,and the boundary layer trips didn’t expand the airfoil’s operating range of angles of attack.In other words,eliminating the bubble had a detrimental effect on the lift-to-drag ratio of the airfoil.The friction drag increase due to early transition by far outweighed the pressure drag produced by the laminar bubble.
文摘In this study,a rocket-based UAV and a solar wing-tail Martian UAV were designed and assessed against a set of criteria established using a house of quality chart.For the design,analysis,trade studies,and optimization,MATLAB and XFLR5 were used.The optimized versions of the two configurations feature the same wing and tail airfoils,the same wing and tail planforms,different dimensions,weight,and performance.Therefore,distinct types of scientific missions are suitable for these aircraft.The results of the study extend our understanding of the capabilities of a Martian fixed-wing airplane in terms of payload mass,hence its scientific value,as well as in terms of its planform geometry and airfoil shapes.
