"NASA Technical Reports Server (NTRS) 20030063996: Altitude-Wind-Tunnel Investigation Of Performance Of Several Propellers On YP-47M Airplane At High Blade Loading. 2; Curtiss 838-1C2-18R1 Four-Blade Propeller" - Information and Links:

NASA Technical Reports Server (NTRS) 20030063996: Altitude-Wind-Tunnel Investigation Of Performance Of Several Propellers On YP-47M Airplane At High Blade Loading. 2; Curtiss 838-1C2-18R1 Four-Blade Propeller - Info and Reading Options

"NASA Technical Reports Server (NTRS) 20030063996: Altitude-Wind-Tunnel Investigation Of Performance Of Several Propellers On YP-47M Airplane At High Blade Loading. 2; Curtiss 838-1C2-18R1 Four-Blade Propeller" and the language of the book is English.


“NASA Technical Reports Server (NTRS) 20030063996: Altitude-Wind-Tunnel Investigation Of Performance Of Several Propellers On YP-47M Airplane At High Blade Loading. 2; Curtiss 838-1C2-18R1 Four-Blade Propeller” Metadata:

  • Title: ➤  NASA Technical Reports Server (NTRS) 20030063996: Altitude-Wind-Tunnel Investigation Of Performance Of Several Propellers On YP-47M Airplane At High Blade Loading. 2; Curtiss 838-1C2-18R1 Four-Blade Propeller
  • Author: ➤  
  • Language: English

Edition Identifiers:

  • Internet Archive ID: NASA_NTRS_Archive_20030063996

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"NASA Technical Reports Server (NTRS) 20030063996: Altitude-Wind-Tunnel Investigation Of Performance Of Several Propellers On YP-47M Airplane At High Blade Loading. 2; Curtiss 838-1C2-18R1 Four-Blade Propeller" Description:

The Internet Archive:

An investigation was conducted in the Cleveland altitude wind tunnel to determine the performance of a Curtiss propeller with four 838-lC2-lSRl blades on a YP-47M airplane at high blade loadings and engine powers. The study was made for a range of power coefficients between 0.30 and 1.00 at free-stream Mach numbers of 0.40 and 0.50. The results of the force measurements indicate primarily the trend of propeller efficiency for changes in power coefficient or advance-diameter ratio, inasmuch as corrections for the effects of tunnel-wall constriction on the installation have not been applied. Slip-stream pressure surveys across the propeller disk are presented to illustrate blade thrust load distribution for several operating conditions. At a free-stream Mach number of 0.40, nearly constant peak efficiencies were obtained at power coefficients from 0.30 to 0.70. A change in power coefficient from 0.70 to 0.90 reduced the peak efficiency about 5 percent. Blade stall at the tip sections became evident for a power coefficient of 0.91 when the advance-diameter ratio was reduced to 1.87. At a free-stream Mach number of 0.50, the highest propeller efficiencies were obtained for power coefficients from 0.80 to 1.00 at advance-diameter ratios above 2.90. At advance-diameter ratios below 2.90, the highest efficiencies were obtained for power coefficients of 0.60 and 0.70. The envelope of the efficiency curves decreased about 12 percent between advance-diameter ratios of 2.60 and 4.20. Local compressibility effects became evident for a power coefficient of 0.40 when the advance-diameter ratio was decreased to 1.75.

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