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Numerical Analysis of Asymmetric Canard-Wing System in Detroit Flying Cars
ISSN: 0148-7191, e-ISSN: 2688-3627
Published March 19, 2019 by SAE International in United States
This content contains downloadable datasetsAnnotation ability available
Event: AeroTech Americas
A numerical simulation system of airflow around the Detroit Flying Cars-Wild Dream 1 (WD-1) is introduced. It involves the application of FVM, the mesh-independence system, boundary conditions and the verification of the simulation conditions to NACA airfoil data and the discussion of technological treatments corresponding to the evaluation of asymmetric wings.
The present work is investigating the aerodynamic behavior of an asymmetric canard-wing system used on the Detroit Flying Cars-WD 1 model. The work involves the application of Finite Volume Method (FVM), the mesh-independence system, boundary conditions and the verification of simulation conditions to NACA airfoil data using OpenFOAM software. The Reynolds number based on free stream velocity and root chord is 5X106. Based on the Coefficient of Lift and Coefficient of Drag obtained from the analysis, the effect of canards on the wings, the distance between the canard trailing edge and the leading edge of the wings and the sensitivity of the staggered height between the canard-wing configuration on the left and right side of the fuselage is studied.
|Technical Paper||Interdependence of Parameters important to the Design of Subsonic Canard-Configured Aircraft|
|Technical Paper||Interdisciplinary Wing Design – Structural Aspects|
|Technical Paper||Propeller Design by Numerical Optimization|
CitationKocherla, I. and Yu, C., "Numerical Analysis of Asymmetric Canard-Wing System in Detroit Flying Cars," SAE Technical Paper 2019-01-1361, 2019, https://doi.org/10.4271/2019-01-1361.
Data Sets - Support Documents
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- Tu , E.L. Vortex-Wing Interaction of a Close-Coupled Canard Configuration Journal of Aircraft 31 2 314 321 1994
- Holzmann , T. Mathematics, Numerics, Derivations and Open FOAM® 2016 10.13140/RG.2.2.27193.36960
- UIUC Airfoil Data Site http://m-selig.ae.illinois.edu/ads/coord_database.html
- YouTube 2018 https://youtu.be/c3QH60mSGy8