Transonic Fan/Compressor Rotor Design Study. Volume 2
Abstract
Volumes I through VI of this report describes the aerodynamic design of a series of five transonic rotors all parametrically related to a baseline design documented in Technical Report AFAPL-TR-79-2078. Each of the five designs deviate from the baseline, in so far as practical, by a variation of one parameter only. The parametric variations are specified at the rotor tip. This volume describes the aerodynamic design details of the Phase I Rotor. The Phase I rotor has the tip airfoil maximum thickness located at 40% of meanline length as compared with 70% for the baseline rotor. The location of maximum thickness varied linearly with radius to 56% of the meanline length at the hub, which is the same as the baseline rotor.
Document Details
- Document Type
- Technical Report
- Publication Date
- Feb 01, 1982
- Accession Number
- ADB069402
Entities
People
- D. E. Parker
- M. R. Simonson
Organizations
- General Electric