Transonic Fan/Compressor Rotor Design Study. Volume 3
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 base line, in so far as practical, by a variation of one parameter only. The parametric variations are specified at the rotor tip. The original hub characteristics were preserved to the maximum extent practical. The varied parameter was adjusted along the span. This volume describes the aerodynamic design details of the Phase II rotor. The Phase II rotor has the tip airfoil maximum thickness located at 55% of meanline length as compared with 70% for the baseline rotor. The location of maximum thickness varied linearly with stream function to 56% of 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
- ADB069403
Entities
People
- D. E. Parker
- M. R. Simonson
Organizations
- General Electric