High-performance airfoil with low reynolds-number dependence on aerodynamic characteristics

Anyoji, Masayuki; Hamada, Daiki

doi:10.15406/fmrij.2019.03.00055

Cited by 15 publications

(3 citation statements)

References 11 publications

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“…Here, subscripts A, B, and C indicate the markers of the ends of the inner and outer wings in figure 10, respectively. The maximum ΔΓ inner and ΔΓ outer according to equations (10) and (11) were approximately 0.10°and 0.16°, respectively. Moreover, as the joint between the inner and outer wings (Y=± 440) had relatively low rigidity, ΔΓ outer was generally larger than ΔΓ inner .…”

Section: Deformation Of the Main Wingmentioning

confidence: 90%

“…Further, to achieve a Martian atmospheric flight, the airfoil needs to have an excellent performance with high L/D at low Reynolds numbers. Anyoji et al revealed that among the existing airfoils with low Reynolds number, the Ishii airfoil originally designed for a hand-launched glider wing meets the requirement [10,11]. Additionally, they have proposed design guidelines for the required high-performance low-Reynolds-number airfoils based on their physical features.…”

Section: Introductionmentioning

confidence: 99%

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Aeroelastic deformation measurement of Martian airplane for high-altitude flight experiment using stereophotogrammetry

Hiramatsu¹,

Anyoji²,

Fujita³

et al. 2021

Eng. Res. Express

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A fixed-wing aircraft called Mars Airplane Balloon Experiment −2 (MABE2) developed by the authors was the subject of high-altitude flight demonstration test in this paper, which can simulate the near-actual environment of a Martian atmospheric flight. Although the flight condition is in the low-Reynolds-number region due to low density at high altitude, the wing suffers from aeroelastic deformation given the relatively high dynamic pressure load in the pull-up phase. Stereophotogrammetry was applied in the 6.5 m × 5.5 m low-speed wind tunnel at the Japan Aerospace Exploration Agency (JAXA), aiming to optically measure MABE2’s aeroelastic deformation under dynamic pressure loads equivalent to high-altitude flight test, with the MABE2’s reinforced structural strength. The results of the accuracy test indicated that stereophotogrammetry measures aeroelastic deformation at high accuracy of ±0.1 mm around the image center and ±0.3 mm around the edge. A slight deflection of up to 4 mm was observed on the main wing, whereas both the main and tail wings were hardly twisted. Compared with flight-simulation-assumed errors, these deformations are extremely small and have a negligible effect on the high-altitude flight test. The study results confirmed the practicality and efficiency of this optical measurement technique in aeroelastic deformation measurement for a real light aircraft.

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Section: Deformation Of the Main Wingmentioning

confidence: 90%

Section: Introductionmentioning

confidence: 99%

Aeroelastic deformation measurement of Martian airplane for high-altitude flight experiment using stereophotogrammetry

Hiramatsu¹,

Anyoji²,

Fujita³

et al. 2021

Eng. Res. Express

Self Cite

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show abstract

“…For the Martian conditions, an optimized airfoil is likely to be similar to an Ishii airfoil [16], with C l |L/D max ≈ 0.7 at α ≈ 5 • and C l,max ≈ 0.8 at α ≈ 9 • (Re ≈ 23,000, M ≈ 0.2), where the definitions are as follows: C l |L/D max is the lift coefficient corresponding to the maximum lift-to-drag ratio; C l,max is the maximum lift coefficient; α is the angle of attack, degrees; Re is the Reynolds number; M is the Mach number.…”

Section: Aerodynamicsmentioning

confidence: 99%

Long-Endurance Mars Exploration Flying Vehicle: A Project Brief

Karpovich,

Kombaev,

Gueraiche

et al. 2023

Aerospace

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The paper presents specifications for the Long-Endurance Mars Exploration Flying Vehicle (LEMFEV), which will be used as future design input data. The specifications are based on the analysis of previous Mars missions and scientific data collected by the operating Martian probes. The design specifications include the requirements related to the airplane’s delivery to the Martian surface; the requirements related to the Martian conditions (atmosphere and climate); and the requirements related to the scientific payload parameters and the mission flight profile.

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Design and Simulation of Hybrid Airfoils for Wind Turbine

Singh,

Navrose

2024

Lecture Notes in Mechanical Engineering

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High-performance airfoil with low reynolds-number dependence on aerodynamic characteristics

Cited by 15 publications

References 11 publications

Aeroelastic deformation measurement of Martian airplane for high-altitude flight experiment using stereophotogrammetry

Aeroelastic deformation measurement of Martian airplane for high-altitude flight experiment using stereophotogrammetry

Long-Endurance Mars Exploration Flying Vehicle: A Project Brief

Design and Simulation of Hybrid Airfoils for Wind Turbine

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