THE AERODYNAMIC CALIBRATION OF THE AEDC PWT 16-FOOT SUPERSONIC TUNNEL COMPRESSOR
Abstract
The aerodynamic performance of the Propulsion Wind Tunnel Facility's 16-Ft Supersonic Tunnel compressor was investigated at an inlet temperature of approximately 100 F and a tunnel stagnation pressure of 500 psf at the design speed of 600 rpm. The over-all performance of the four cylinder configuration was considerably improved when the fourth cylinder stator blades were changed from -14 to -5 degrees. This change increased the maximum four cylinder pressure ratio from approximately 6.30 to 7.45 and increased the inlet volume flow approximately five %. The maximum pressure ratio available is 2.80 at 160,000 cfs, 4.08 at 152,000 cfs, and 7.45 at 164,000 cfs for two, three, and four cylinders, respectively. The peak pressure ratio performance of the prototype for the two and three cylinder configurations is greater than that predicted by Westinghouse. In the four cylinder configuration this peak pressure ratio is approximately 1.5 below the theoretical estimate. It was also noted that the prototype results exhibit a 12,000 to 15,000 cfs loss in maximum inlet volume flow when compared to the estimate. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- May 01, 1962
- Accession Number
- AD0275743
Entities
People
- C.l. Jr. Garner
- W.e. White
Organizations
- Arnold Engineering Development Complex