Multi-objective Optimization of Airfoil for Mars Exploration Aircraft Using Genetic Algorithm

Sasaki, Gaku; Tatsukawa, Tomoaki; Nonomura, Taku; Oyama, Akira; Matsumoto, Takaaki; Yonemoto, Koichi

doi:10.2322/tastj.12.pk_59

Cited by 4 publications

(2 citation statements)

References 5 publications

(5 reference statements)

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“…8 In addition, some researches have been conducted to obtain the optimum airfoil shape by using optimization method. Sasaki et al 9 have used genetic algorithm and obtained the optimized airfoil shape, which shows the characteristics of the low-Reynolds number airfoil as mentioned above. Whereas these sophisticated airfoils can achieve high aerodynamic performance, there are several problems associated with the structural strength and the load capacity due to its thin airfoil shape.…”

Section: Introductionmentioning

confidence: 98%

Control of Airfoil Flow at Cruise Condition by DBD Plasma Actuator - Sophisticated Airfoil vs. Simple Airfoil with Flow Control -

Asano

Sato

Nonomura

et al. 2016

8th AIAA Flow Control Conference

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We have conducted large-eddy simulations of the airfoil flow at a cruise condition controlled by a DBD plasma actuator. The NACA0015 is used as the airfoil. The Reynolds number and angle of attack are set to be 63000 and 4 deg., respectively. In this condition, the flow is almost attached, except for the separation bubble region, over the airfoil. The lift-to-drag ratio is improved by the flow control with the burst mode actuation. The most effective burst frequency becomes F + ≃ 6 and the normal mode actuation is not effective. The delay of the turbulent transition is one of the key mechanism for the effective flow control at the cruise condition, differently from the separation control case. The flow feature and aerodynamic performance are compared between the controlled flow and "Ishii airfoil" flow, which is developed as a low-Reynolds-number airfoil. The lift-to-drag ratio attained by the flow control is comparable to that of the Ishii airfoil. Moreover, it can be said that the flow control by the plasma actuator on the simple shape airfoil has the capability to emulate the flow feature of the sophisticated airfoil.

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Section: Introductionmentioning

confidence: 98%

Control of Airfoil Flow at Cruise Condition by DBD Plasma Actuator - Sophisticated Airfoil vs. Simple Airfoil with Flow Control -

Asano

Sato

Nonomura

et al. 2016

8th AIAA Flow Control Conference

Self Cite

View full text Add to dashboard Cite

show abstract

“…Therefore, it is very important to observe the phenomenon of separation bubbles and consider them. Sasaki et al have studied multi-objective airfoil shape optimization using Genetic Algorithm (GA) associated with Computational Fluid Dynamics (CFD) 5) . Their research found possible types of airfoils numerically, but require further investigation using wind tunnel testing.…”

Section: Introductionmentioning

confidence: 99%

Variable-Pressure Wind Tunnel Test of Airfoils at Low Reynolds Numbers Designed for Mars Exploration Aircraft

Tsukamoto

Yonemoto

Makizono

et al. 2016

AEROSPACE TECHNOLOGY JAPAN

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Recently, aerial Mars exploration systems have been actively researched. Because the atmospheric density of Mars is almost one-hundredth to that of Earth's, the flight Reynolds number becomes low (Re = 10 4 ~ 10 5 ). In low Reynolds numbers, the flow around a wing tends to separate and conventional airfoils cannot satisfy the given performance requirements for Mars exploration aircraft. In recent years, Sasaki et al. researched new airfoils that have high lift-to-drag ratio at low Reynolds number using evolutionary multi-objective optimization and computational fluid dynamics. In this research, two-dimensional wind tunnel test of three airfoils proposed by Sasaki et al. is conducted to investigate their actual aerodynamic characteristics at Reynolds number 2.0 × 10 4 . The Ishii airfoil with good performance at low Reynolds number is used as the benchmark. The result of the wind tunnel test showed that the lift curve of the three airfoils is linear, and their maximum lift coefficient and stall angle are larger than those of Ishii. Particularly, the three airfoils' lift-to-drag ratio is superior to the Ishii airfoil by more than 30%. NomenclatureRe : Reynolds number L : lift

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Design Exploration of Airfoil Geometry for Martian Airplane

Kanazaki

2015

IEEJ Trans.EIS

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To design airfoils for novel airplanes, new knowledge of aerodynamics is required. Modified Parametric SECtion (modified PARSEC) airfoil representation is one of the promising methods for automated airfoil/wing design. In this paper, this method is applied to airfoil design exploration by means of a Kriging model based genetic algorithm (GA) to obtain an optimal airfoil for consideration in the development of a Martian airplane. In this study, an airfoil that can obtain a sufficient glide ratio is considered. The objective function is to maximize the maximum lift-to-drag ratio. To extract the knowledge from solutions, the self-organizing map map (SOM) is also applied. According to the exploration result, several solutions which carry out high aerodynamic performances could be found out. In addition, design knowledges on the low Reynolds number airfoil could be extracted efficiently by SOM. SOM's results suggest that the airfoil with and higher camber at the trailing edge is more suitable for a Martian airplane.

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Multi-objective Optimization of Airfoil for Mars Exploration Aircraft Using Genetic Algorithm

Cited by 4 publications

References 5 publications

Control of Airfoil Flow at Cruise Condition by DBD Plasma Actuator - Sophisticated Airfoil vs. Simple Airfoil with Flow Control -

Control of Airfoil Flow at Cruise Condition by DBD Plasma Actuator - Sophisticated Airfoil vs. Simple Airfoil with Flow Control -

Variable-Pressure Wind Tunnel Test of Airfoils at Low Reynolds Numbers Designed for Mars Exploration Aircraft

Design Exploration of Airfoil Geometry for Martian Airplane

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