Abstract
Experimental testing of the crossflow fan was performed and modified for transonic flow. The fan selected for the study was composed of an ABS plastic material with 32 blades, which were reinforced at the center-span location by a structural ring. The outer diameter of the fan was 3.42 in. The fan was cut to fit the 5 in. width of the test section, and aluminum end caps were attached to the ends of the fan to provide structural reinforcement. A diffusing ramp of 7.5 deg was incorporated into the tunnel wall leading up to the fan inlet arc to allow the flow to enter the fan radially across the first stage. The fan rear-wall housing was also built into the aluminum test section, leaving room under the fan to allow the flow to exit the second stage tangent to the blades.
| Original language | English (US) |
|---|---|
| Pages (from-to) | 1216-1219 |
| Number of pages | 4 |
| Journal | Journal of Aircraft |
| Volume | 54 |
| Issue number | 3 |
| DOIs | |
| State | Published - 2017 |
| Externally published | Yes |
ASJC Scopus subject areas
- Aerospace Engineering