The Numerical Solution of Compressible Fluid Flow Problems
Abstract
Numerical methods have been developed for obtaining steady, adiabatic flow field of friction less, perfect gas about arbitrary two-dimensional bodies. Solutions include subsonic and supersonic velocity regions and transition compression shocks. Rotational motion and entropy changes following shocks are taken into account. Extensive use is made of relaxation method. Methods can be applied directly to wind-tunnel and free air tests of arbitrary airfoil shapes at subsonic speeds.
Document Details
- Document Type
- Technical Report
- Publication Date
- May 01, 1944
- Accession Number
- ADB814416
Entities
People
- Howard W. Emmons
Organizations
- Harvard University