Effect of surface roughness on aerodynamic performance of the wing with NACA 4412 airfoil at Reynolds number 1.7 × 105

Dwivedi, Yagya Dutta; Wahab, Abdul; Pallay, Aditi Deekshita; Shesham, Akhil

doi:10.1016/j.matpr.2022.02.153

Cited by 11 publications

(4 citation statements)

References 8 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…First, lift (CL) and drag (CD) coefficients were used as global quantities to assess any discrepancies between the adopted models and DNS results. In table 1, such a comparison is reported by also considering previous experimental investigations on NACA 4412 profiles [17,18]. Notice that the present test case considers a rather atypical combination of angle of attack, Reynolds number and turbulent intensity.…”

Section: Flow Dynamicsmentioning

confidence: 90%

See 1 more Smart Citation

RANS representation of transition and separation over a low-Re number blade section at high angle of attack

Pagliarini,

Corsini,

Stalio

et al. 2024

J. Phys.: Conf. Ser.

View full text Add to dashboard Cite

Systems based on wind energy harvesting can successfully meet part of the increasing green energy demand worldwide. However, wind turbines operation might be undermined by varying atmospheric conditions, which could result in an increase of angle of attack and consequent onset of flow separation phenomena, especially at low Reynolds numbers. Such conditions are strongly influenced by blades geometry, and they negatively affect structural integrity and power output of wind turbines. For this reason, it is crucial to define a tool capable of swiftly allowing numerical investigations on different geometrical configurations to delay and mitigate flow separation occurrence. The present work aims at modelling laminar-turbulent transition and turbulent flow separation over a wind turbine blade section operating at angle of attack = 15°, Re = 66000 and Pr = 0.71 by means of a steady RANS approach. Turbulence is treated by means of the Transition SST k-ω and the Transition k-kL-ω models. The main aerodynamic and thermal coefficients are evaluated and compared against a high-order accurate DNS database for validation. The results highlight, for the present test case, a better capability of the Transition SST k-ω of perceiving the main thermo-fluid dynamic features of the separated flow over the blade section.

show abstract

Section: Flow Dynamicsmentioning

confidence: 90%

“…Lift and drag coefficients for different numerical approaches and comparison with similar experimental cases[17,18].…”

mentioning

confidence: 99%

RANS representation of transition and separation over a low-Re number blade section at high angle of attack

Pagliarini,

Corsini,

Stalio

et al. 2024

J. Phys.: Conf. Ser.

View full text Add to dashboard Cite

show abstract

“…Furthermore, Y.D. Dwivedi, Abdul Wahab, et al [10] found that the roughness of the wing surface also affects the lift, drag and stall performance of the aircraft. Additional factors such as wing geometry, surface roughness, and aerodynamic configurations can also exert considerable influence on the lift-drag ratio, necessitating a comprehensive understanding of the complex interplay between various aerodynamic parameters.…”

Section: Replenishmentmentioning

confidence: 99%

Exploring the Influence of Wing Shape on the Aerodynamics of Gliders

Cao

2024

HSET

View full text Add to dashboard Cite

The lift-to-drag ratio and the aerodynamic characteristics of the wing shape play an important role in the performance of the glider. Lift-drag ratio, as a key index of aircraft performance evaluation, is directly related to aircraft glide performance, fuel efficiency, and flight range. The selection and optimization of wing shape is also considered to be one of the main factors affecting the performance of gliders. However, despite the extensive research in the field of glider design, there are still some gaps in the understanding of the relationship between lift-drag ratio and wing shape. The traditional research is carried out in a specific situation, and the aerodynamic characteristics of different wing shapes are relatively short of systematic comparison and in-depth theoretical analysis. Therefore, this research focuses on the design and performance optimization of gliders, focusing on the lift-drag ratio and aerodynamic characteristics of wing shape. The tracker is used to collect the data of glider models with different wing shapes in the air, compare the performance of various shapes, discuss their advantages and disadvantages, and make a comprehensive analysis. Important findings from this study not only provide practical guidance for glider design but also provide insight into the relationship between lift-drag ratio and wing shape research, this research encourages further exploration and expansion of this area to advance the development of glider technology. This research provides useful references for scientists, engineers, and designers in the field of aviation, leading to more advanced and efficient glider design and manufacture.

show abstract

“…Surface roughness can have an effect on the flow around the airfoil, even if it is a reduced thin NACA 64A-204 airfoil with a relatively small chord and width [10 cm × 5 × m]. Here's why, Dwivedi et al (2022), :…”

Section: Surface Roughness and Effects On Experimentationmentioning

confidence: 99%

Investigation of viscous supersonic laminar flows around F-16 airfoil: experimental, numerical, and analytical approaches

Eddegdag,

Naamane,

Radouani

2023

Phys. Scr.

View full text Add to dashboard Cite

This research paper primarily focuses on the behavior of viscous supersonic laminar flows around the F-16’s NACA 64A-204 airfoil, while also extending its scope to Shock-Wave/Boundary-Layer Interactions. The aim is to evaluate and compare methodologies for accurately characterizing these crucial aerodynamic phenomena. A unique experimental setup was developed, featuring mock-ups of F-16 airfoil equipped with pressure taps, and tested in the Supersonic Burst Wind Tunnel AF300. Computational Fluid Dynamics simulations were conducted using Ansys Fluent 2022 R2 and were supplemented by our previously established analytical model was adapted to our specific airfoil case, following calculations of the wing section equation. Key aerodynamic parameters such as lift coefficient, drag coefficient, Local Mach numbers, and the characteristics of the shock waves formed around the airfoil were examined. The study validates the NACA 64A-204 mock-up, with average errors for key parameters and 1st and 2nd Pressure Taps between the three adopted approaches remaining below 2.5%. The findings contribute valuable insights into the fundamental physics of viscous supersonic laminar flows, offering immediate applications to the design of high-speed aircraft and other advanced aerospace technologies. Additionally, the validated mock-up enhances the research capabilities of the Supersonic Burst Wind Tunnel AF300. Ultimately, this study serves as a foundational reference for optimizing aerodynamic surfaces, thereby facilitating advancements in key vehicle performance metrics such as manoeuvrability and fuel efficiency.

show abstract

Effect of surface roughness on aerodynamic performance of the wing with NACA 4412 airfoil at Reynolds number 1.7 × 105

Cited by 11 publications

References 8 publications

RANS representation of transition and separation over a low-Re number blade section at high angle of attack

RANS representation of transition and separation over a low-Re number blade section at high angle of attack

Exploring the Influence of Wing Shape on the Aerodynamics of Gliders

Investigation of viscous supersonic laminar flows around F-16 airfoil: experimental, numerical, and analytical approaches

Contact Info

Product

Resources

About