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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


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