IMPROVEMENT IN AERODYNAMIC PERFORMANCE OF AIRFOILS USING AERODYNAMIC SHAPE OPTIMIZATION

This study demonstrates the application of the discrete adjoint method for aerodynamic shape optimization of the NACA2412 airfoil used in Cessna 172R at moderate Reynolds numbers and low Mach numbers . The open-source CFD solver OpenFOAM is coupled with DAFoam-discrete adjoint with OpenFOAM to effic...

Full description

Saved in:
Bibliographic Details
Published inJP Journal of Heat and Mass Transfer pp. 427 - 445
Main Authors Vuong, Thi-Hong-Nhi, Long, Gia-Hung, Le, Thi-Hong-Hieu, Le, Thanh-Long
Format Journal Article
LanguageEnglish
Published 09.06.2025
Online AccessGet full text
ISSN0973-5763
3049-2556
DOI10.17654/0973576325021

Cover

More Information
Summary:This study demonstrates the application of the discrete adjoint method for aerodynamic shape optimization of the NACA2412 airfoil used in Cessna 172R at moderate Reynolds numbers and low Mach numbers . The open-source CFD solver OpenFOAM is coupled with DAFoam-discrete adjoint with OpenFOAM to efficiently compute the sensitivities of the drag coefficient concerning shape design variables. The SST (Shear Stress Transport) turbulence model is employed for its superior performance in predicting flow separation over airfoils. The airfoil geometry is parameterized using B-spline curves with control points as design variables. A discrete adjoint method for a multidisciplinary optimization algorithm minimizes the drag coefficient subject to lift constraints by automatically adjusting the control point positions. The optimized airfoil exhibits significantly reduced drag compared to the baseline NACA2412. Optimizing the airfoil shape reduced drag coefficient by , increased lift coefficients, and increased lift-todrag ratios at different angles of attack over the original design.
ISSN:0973-5763
3049-2556
DOI:10.17654/0973576325021