Publication Date:
2019-06-28
Description:
Algebraic procedures are described for the automatic generation of structured, single-block flow computation grids for relatively simple configurations (wing, fuselage, and fin). For supersonic flows, a quasi two-dimensional grid for Euler-marching codes is developed, and some sample results in graphical form are included. A type of grid for subsonic flow calculation is also described. The techniques are algebraic and are based on a generalization of the method of transfinite interpolation.
Keywords:
AERODYNAMICS
Type:
NASA-TM-4573
,
L-17364
,
NAS 1.15:4573
Format:
application/pdf
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