An investigation has been conducted by the NACA to determine the design-performance characteristics of the NACA eight-stage axial-flow compressor and the effect of altitude on the performance. The compressor was tested at simulated altitudes of 50,000; 36,000; and 27,000 feet at rotor speeds corresponding to compressor Mach numbers of 0.80, 0.85, 0.90, and 0.95 wit varying air flow at each speed.

The NACA has conducted an investigation to determine the performance that can be obtained from a multistage axial-flow compressor based on airfoil research. A theory was developed; an eight-stage axial-flow compressor was designed, constructed, and tested.