New Test Cases in Low Density Hypersonic Flow

2003 ◽  
Author(s):  
Bruno Chanetz
Keyword(s):  
Hypersonic Flow ◽  
Test Cases ◽  
Low Density

Improved Procedures for Determining Surface Pressures in Low-Density Hypersonic Flow

AIAA Journal ◽  
1972 ◽  
Vol 10 (9) ◽  
pp. 1183-1187 ◽  
Author(s):  
JEROME A. SMITH ◽  
JOHN H. LEWIS
Keyword(s):  
Hypersonic Flow ◽  
Low Density

HaloDPC: An Improved Recognition Method on Halo Node for Density Peak Clustering Algorithm

2019 ◽  
Vol 33 (08) ◽  
pp. 1950012 ◽  
Author(s):  
Jianhua Jiang ◽  
Wei Zhou ◽  
Limin Wang ◽  
Xin Tao ◽  
Keqin Li
Keyword(s):  
Clustering Algorithm ◽  
High Dimensionality ◽  
Test Cases ◽  
Low Density ◽  
Recognition Method ◽  
Density Peak ◽  
Irregular Shapes ◽  
Density Peaks ◽  
Density Peaks Clustering ◽  
Density Peak Clustering

The density peaks clustering (DPC) is known as an excellent approach to detect some complicated-shaped clusters with high-dimensionality. However, it is not able to detect outliers, hub nodes and boundary nodes, or form low-density clusters. Therefore, halo is adopted to improve the performance of DPC in processing low-density nodes. This paper explores the potential reasons for adopting halos instead of low-density nodes, and proposes an improved recognition method on Halo node for Density Peak Clustering algorithm (HaloDPC). The proposed HaloDPC has improved the ability to deal with varying densities, irregular shapes, the number of clusters, outlier and hub node detection. This paper presents the advantages of the HaloDPC algorithm on several test cases.

Modelling Rarefied Hypersonic Reactive Flows Using the Direct Simulation Monte Carlo Method

2015 ◽  
Vol 18 (4) ◽  
pp. 1095-1121 ◽  
Author(s):  
Ming-Chung Lo ◽  
Cheng-Chin Su ◽  
Jong-Shinn Wu ◽  
Kun-Chang Tseng
Keyword(s):  
Monte Carlo ◽  
Hypersonic Flow ◽  
Direct Simulation Monte Carlo ◽  
Test Cases ◽  
Monte Carlo Code ◽  
Direct Simulation ◽  
Reactive Flows ◽  
Flow Past ◽  
Flow Past A Cylinder ◽  
Simulation Monte Carlo

AbstractThis paper presents the implementation, validation and application of TCE (total collision energy) model for simulating hypersonic reactive flows in a parallel direct simulation Monte Carlo code, named PDSC++, using an unstructured grid. A series of benchmarking test cases, which include reproduction of theoretical rate constants in a single cell, 2D hypersonic flow past a cylinder and 2D-axisymmetric hypersonic flow past a sphere, were performed to validate the implementation. Finally, detailed aerothermodynamics of the flown reentry Apollo 6 Command Module at 105 km is simulated to demonstrate the powerful capability of the PDSC++in treating realistic hypersonic reactive flow at high altitude.

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