A Theory of Unstaggered Airfoil Cascades in Compressible Flow
Abstract
By use of the methods of thin airfoil theory, which include effects of compressibility, relations are developed, which permit the rapid determination of the pressure distribution over an unstaggered cascade of airfoil of a given profile, and the determination of the profile shape necessary to yield a given pressure distribution for small chord/gap ratios. For incompressible flow, the results of the theory are compared with available examples obtained by the more exact method of conformal transformation. Although the theory is developed for small chord/gap ratios, these comparisons show that it may be extended to chord/gap ratios of order unity, at least for low speed flows. Choking of cascades, a phenomenon of particular importance in compressor design, is considered.
Document Details
- Document Type
- Technical Report
- Publication Date
- Sep 01, 1947
- Accession Number
- ADA801244
Entities
People
- H. J. Allen
- Robert A. Spurr
Organizations
- National Aeronautics and Space Administration