Publication Date:
2019-07-12
Description:
The stator-blade angles in the first four stages of a 16-stage axial-flow compressor were increased in order to decrease the angles of attack of these stages, and thereby to improve part-speed performance. The performance of this modified compressor was compared with that of the same compressor with original blade angles.
Keywords:
Aircraft Design, Testing and Performance
Type:
NACA-RM-E52B15
Format:
application/pdf