THE AERODYNAMIC CALIBRATION OF THE AEDC 16-FOOT SUPERSONIC TUNNEL COMPRESSOR WITH THE FIRST CYLINDER REMOVED,
Abstract
The aerodynamic performance of the supersonic wind tunnel compressor with the first cylinder of the compressor removed was investigated at an inlet temperature of approximately 55F and compressor exit pressure levels of 300 and 1200 psfa at the design speed of 600 rpm. The overall performance of the three-cylinder configuration was considerably improved when the first and second cylinder stator blade settings were mismatched 6 degrees. This change increased the maximum three-cylinder configuration pressure ratio from 4.59 to 5.00. The maximum pressure ratios available are 1.57 at 108,800 cfs, 2.58 at 113,500 cfs, and 5.00 at 109,000 cfs for the one-, two-, and three-cylinder configurations, respectively. Increasing the stagnation pressure from 300 to 1200 psfa produced up to a 10% increase in volume flow for the two-cylinder configuration and up to an 11% increase in volume flow for the threecylinder configuration. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Feb 01, 1964
- Accession Number
- AD0428813
Entities
People
- C. L. Garner Jr.
Organizations
- Arnold Engineering Development Complex