Performance of NACA eight-stage axial-flow compressor designed on the basis of airfoil theory /

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.Prepared at the Aircraft Engine Research Laboratory, Cleveland, Ohio.Originally issued as NACA as Advance Confidential Report E4H18 (August 1944). Also issued as NACA Technical Report 758.NACA Wartime Report E-1.Includes bibliographical references.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.Mode of access: Internet