Hongqiang Lu's Homepage

Hongqiang Lu

Email: hongqiang.lu@nuaa.edu.cn

College of Aerospace Engineering

Nanjing University of Aeronautics and Astronautics

Nanjing, China, 210016

College of Aerospace Engineering, Nanjing University of Aeronautics and Astronautics, China. Msc.

School of Computing, University of Leeds, UK. PhD.



Research Interests:

Discontinuous Galerkin Methods; EHL Problems; Euler Euqaitons; N-S Equations; Multigrid Methods

Recent Publications:


  1. Hongqiang Lu, Yizhao Wu, Chunhua Zhou, Shuling Tian. High Resolution of Subsonic Flows on Coarse Grids (In Chinese), Chinese Journal of Aeronautics, To appear.

  2. Lu, H, Berzins, M, Goodyer, C E & Jimack, P K, High Order Discontinuous Galerkin Method for Elastohydrodynamic Lubrication Line Contact Problems. Comm. Num. Meth. Engrg, vol.21, pp.643-650, 2005.

  3. Lu, H, Berzins, M, Goodyer, C E, Jimack, P K & Walkley, M A, Adaptive High-order Finite Element Solution of Transient Elastohydrodynamic Lubrication Problems. Proc. IMechE Part J: J. Engrg. Tribology, vol.220, pp.215-225, 2006.

  4. Lu, H, Berzins, M & Jimack, P K, Application of the Adaptive Discontinuous Galerkin Method to Problems in Elastohydrodynamic Lubrication. (Proceedings of the Fifth International Conference on Engineering Computational Technology, Las Palmas de Gran Canaria, Spain, September 2006.

  5. Hongqiang Lu, Yizhao Wu, Songcan Chen. A New Method to Generate Coarse Meshes for Overlapping Unstructured Multigrid Algorithm Based on SOM Network. Applied Mathematics and Computation, Vol 140(2-3), 353-360, 2003.



Talks:

  1. BIENNIAL CONFERENCES ON NUMERICAL ANALYSIS, Dundee, Tuesday 28 June - Friday July 1, 2005. http://www.maths.dundee.ac.uk/naconf/

  2. 32th LEEDS-LYON SYMPOSIUM ON TRIBOLOGY, Lyon, France, Tuesday 6th -Friday 9th September 2005. http://leeds-lyon.insa-lyon.fr/

  3. INTERNATIONAL CONFERENCE ON SPECTRAL AND HIGH ORDER METHODS, Beijing, China, 2007. http://lsec.cc.ac.cn/~icosahom/



Numerical Results:



  1. DG for EHL Problems


1d steady-state result


1d transient result






















    2d steady-state result

  1. DG for Inviscid Flows (Euler Equations)

(1) Subsonic Flow Around a Cylinder (Ma=0.38)

Global Mesh Mesh around the Solid Wall

Ma Contours (p=1) Ma Contours (p=2) Ma Contours (p=3) Ma Contours (p=4) Comparison of the Cp Disctributions

(2) Subsonic Flow around the NACA0012 Airfoil (Ma=0.63, Attack Angle=2.0)

Global Mesh Mesh around the Solid Wall

Ma Contours (p=1) Ma Contours (p=4) Comparison of the Cp distributions

(3) Transonic and Supersonic Flows around NACA0012 Airfoil







Ma Profile (Ma=0.8, Attack Angle=1.5) Ma Profile (Ma=1.5, Attack Angle=0.0)



  1. DG for Viscous Flows (N-S Equations)



Mesh for Viscous Flows



















Ma Contours when p=1,2,3,4 (Ma=0.5, Attack Angle=0.0, Re=2000)