| 摘要 |
PURPOSE: To provide a high load and high efficiency in a relatively high Mach number by forming a blade having a pair of aerofoil cross sections to have a specific thickness ratio and camber relating to plural cross-sections in its longitudinal direction. CONSTITUTION: This aerofoil blade 100 is identified by a code comprising two numbers with respective cross sections equal to 1000 times of thickness ratio (thickness/length), for example, the uppermost end aerofoil part 20 is characterized by 0.02 of thickness ratio, and the second aerofoil part 30 has 0.030 of thickness ratio. The third, fourth, and fifth aerofoil parts 40, 60, 75 have 0.040, 0.060, and 0.075 of thickness ratios respectively. A cross section of the aerofoil part 20 is cut off substantially at the tip of the blade, and a cross section of the aerofoil part 30 is cut off in a position of about 0.75 of length in a longitudinal axis of the blade from a root part of the blade. Cross sections of the aerofoil parts 40, 75 are cut off in positions of about 0.045 and 0.35 in their lengths.
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