NASA NTRS · 19710013196
Flow fields over sharp edged delta wings with attached shocks
Abstract
Analysis of supersonic and hypersonic flow of inviscid ideal gas over conical wings with sharp leading edges and attached shock waves by three dimensional method of characteristics
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Beeman, E. R., Jr., Powers, S. A.. 1971-04-01. Flow fields over sharp edged delta wings with attached shocks. https://ntrs.nasa.gov/citations/19710013196
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