Drag Divergence is a phenomenon in transonic aerodynamics characterized by a rapid increase in aerodynamic drag coefficient occurring as an airfoil or aircraft approaches and transitions through the speed of sound, distinguished from other drag effects by its onset at a critical Mach number where local flow reaches supersonic speeds and shock waves begin to form.
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Citations
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Authors
27
Institutions
Publications per year
2017–2026
6
Parents
Publications
25
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Authors
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1–5 of 53
Institutions
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Langley Research Center
Hampton, United States
6 h-index
8 publications
312 citations
Tsinghua University
Beijing, China
2 h-index
6 publications
123 citations
Concordia University
Montreal, Canada
2 h-index
4 publications
94 citations
Stanford University
Stanford, United States
2 h-index
5 publications
213 citations
University of Alabama at Birmingham
Birmingham, United States
1 h-index
1 publications
62 citations
Indian Institute of Technology Madras
Chennai, India
1 h-index
2 publications
36 citations
Northwestern Polytechnical University
Xi'an, China
1 h-index
3 publications
57 citations
Ames Research Center
Mountain View, United States
1 h-index
1 publications
15 citations
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Venues
- NASA Technical Reports Server (NASA)
Repository · 3 publications · 45 citations
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- Journal of Aircraft
2 publications · 46 citations
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- NASA STI Repository (National Aeronautics and Space Administration)
Repository · 2 publications · 29 citations
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- Chinese Journal of Aeronautics
CJA · 1 publications · 23 citations
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- IEEE Transactions on Aerospace and Electronic Systems
1 publications · 20 citations
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