Design of adaptive transonic laminar airfoils using the<mml:math xmlns:mml="http://www.w3.org/1998/Math/MathML" altimg="si1.gif" overflow="scroll"><mml:mi>γ</mml:mi><mml:mtext>-</mml:mtext><mml:msub><mml:mrow><mml:mover accent="true"><mml:mrow><mml:mi mathvariant="italic">Re</mml:mi></mml:mrow><mml:mrow><mml:mo stretchy="false">˜</mml:mo></mml:mrow></mml:mover></mml:mrow><mml:mrow><mml:mi>θ</mml:mi><mml:mi>t</mml:mi></mml:mrow></mml:msub></mml:math>transition model

Robitaille, Martin; Mosahebi, Ali; Laurendeau, Éric

doi:10.1016/j.ast.2015.06.027

Cited by 25 publications

(3 citation statements)

References 17 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…If the numerical transition is outside the experimental transition region then an error is calculated between the numerical value and the closest boundary value. If the calculated error is less than 6%, the error is considered as acceptable 30 . Figure 12 presents an example where the numerical transition matches the experimental transition region and an example where the numerical transition does not match and the error is computed for the this case.…”

Section: Optimization Results Versus Experimental Resultsmentioning

confidence: 99%

A Genetic Algorithm Optimization Method for a Morphing Wing Tip Demonstrator Validated Using Infra Red Experimental Data

Koreanschi

Gabor

Acotto

et al. 2016

34th AIAA Applied Aerodynamics Conference

View full text Add to dashboard Cite

Section: Optimization Results Versus Experimental Resultsmentioning

confidence: 99%

A Genetic Algorithm Optimization Method for a Morphing Wing Tip Demonstrator Validated Using Infra Red Experimental Data

Koreanschi

Gabor

Acotto

et al. 2016

34th AIAA Applied Aerodynamics Conference

View full text Add to dashboard Cite

“…Robitaille et al 38 examines the design of adaptive laminar airfoils in transonic flow using -Re˜θ t transition model as a transition prediction method. Huan et al 39 developed an effective robust design optimization (RDO) which is based on an adjusted polynomial chaos expansion (PCE) method for designing high performance transonic high lift natural laminar flow (NLF) airfoil for operating at low Reynolds numbers.…”

Section: Other Approachesmentioning

confidence: 99%

Mathematical Modeling, Design, and Optimization of Airfoils and Aircrafts Operating at Specific Reynolds Number

Kakade¹,

Seeni²

2022

ECS Trans.

View full text Add to dashboard Cite

Although there are several airfoil designs available to choose from, for the application of aircraft design, the problem of finding the optimal design based on mathematical and physical modeling has not been attempted before. For that purpose, research on existing literature has been done to find the most efficient and optimal airfoil design and optimization technique to be further used for designing and optimizing airfoils. Both physical and mathematical modeling along with other computational algorithms will be used to generate optimal new airfoil designs for high lift and low drag for specific operational conditions.

show abstract

“…3. Calculate C D at C L 2 with a Proportional Integral Derivative controller [30] over the angle of attack for an accurate evaluation of…”

Section: Calculatementioning

confidence: 99%

Combined high-speed and high-lift wing aerodynamic optimization using a coupled VLM-2.5D RANS approach

Parenteau

Laurendeau

Carrier

2018

Aerospace Science and Technology

View full text Add to dashboard Cite

The paper presents a numerical framework for the aerodynamic analysis of aircraft wings in transonic cruise and take-off/landing compatible with preliminary and conceptual design phase requirements based on the Non-Linear Vortex Lattice Method (NL-VLM). The purpose of this work is to demonstrate the applicability of the VLM-2.5D RANS approach for aircraft design optimization. The algorithm captures wing sweep effects, important in the transonic regime and near C Lmax conditions, by a stripwise viscous-inviscid coupling strategy with an infinite-swept wing (2.5D) Reynolds-Averaged Navier-Stokes (RANS) solver. Aerodynamic forces are evaluated through spanwise integration of the 2.5D RANS solutions and a trefftz-plane analysis of the VLM solver. The framework allows calculations of single and multi-element configurations without modifying the VLM mesh. A novel C Lmax criteria is proposed based on recently observed stall-cells patterns that captures C Lmax , α max and the spanwise location of the stall, which represent important design parameters. The applicability of the framework to aircraft design is demonstrated by embedding the analysis tools into a gradient-free Covariance Matrix Adaptation Evolution Strategy. After a verification phase, validation is performed on high-speed, high-lift and combined high-speed/high-lift optimisations cases. In particular, the capability of the numerical algorithms towards multi-topology optimisation is demonstrated.

show abstract

Design of adaptive transonic laminar airfoils using theγ-Re˜θttransition model

Cited by 25 publications

References 17 publications

A Genetic Algorithm Optimization Method for a Morphing Wing Tip Demonstrator Validated Using Infra Red Experimental Data

A Genetic Algorithm Optimization Method for a Morphing Wing Tip Demonstrator Validated Using Infra Red Experimental Data

Mathematical Modeling, Design, and Optimization of Airfoils and Aircrafts Operating at Specific Reynolds Number

Combined high-speed and high-lift wing aerodynamic optimization using a coupled VLM-2.5D RANS approach

Contact Info

Product

Resources

About