- Restrictions on Access:
- Unclassified, Unlimited, Publicly available.
- The input parameters are presented for a computer program which performs calculations for inviscid isentropic transonic flow over three dimensional airfoils with straight leading edges. The free stream Mach number is restricted only by the isentropic assumption. Weak shock waves are automatically located where they occur in the flow. The finite difference form of the full equation for the velocity potential is solved by the method of relaxation, after the flow exterior to the airfoil is mapped to the upper half plane.
- Document ID: 19740011527.
Accession ID: 74N19640.
- No Copyright.
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