The Theory and Practice of Two-Dimensional Supersonic Pressure Calculations
JOHNS HOPKINS UNIV LAUREL MD APPLIED PHYSICS LAB
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It has been demonstrated that an arbitrary curve intersecting once and only once each of the straight-line patching or characteristic curves in an expansive supersonic flow can be treated as if it were a characteristic curve. This fact leads to the formulas for calculating pressure distributions over airfoils immersed in two-dimensional supersonic flows, and hence to lift, drag, and moment computations. The Analysis Group has calculated also extensive tables for facilitating oblique shock front computations. The Bumblebee report includes these computation tables and the discussion of the principles of two-dimensional supersonic flow.
- Fluid Mechanics