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• Performance of NACA eight-stage axial-flow compressor designed on the basis of airfoil theory
• The Effect of Increased Cooling Surface on Performance of Aircraft-Engine Cylinders as Shown by Tests of the NACA Cylinder
• The Effect of Increased Cooling Surface on Performance of Aircraft-Engine Cylinders as Shown by Tests of the NACA Cylinder
• Comparative Cooling of Cylinders of Nonuniform Fin Width With Tight-Fitting Baffles and With Baffles That Provide Constant Flow-Path Areas