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Cambered plate C=14% T=5% R=0.96 (cp-140-050-gn)

Cambered plate C=14% T=5% R=0.96 - HAWT pipe blade with coordinates based on top surface. Camber=14% Wall thickness=5% Radius=0.963


Airfoil cp-140-050-gn
Details Dat file Parser  
(cp-140-050-gn) Cambered plate C=14% T=5% R=0.96
HAWT pipe blade with coordinates based on top surface. Camber=14% Wall thickness=5% Radius=0.963
Max thickness 5.5% at 3.6% chord.
Max camber 12.2% at 47.7% chord
Source Generated
Source dat file
The dat file is in Selig format
Cambered plate C=14% T=5% R=0.96
  1.000000  0.000000
  0.979698  0.011998
  0.959109  0.023496
  0.938244  0.034486
  0.917116  0.044961
  0.895738  0.054916
  0.874122  0.064344
  0.852282  0.073241
  0.830231  0.081599
  0.807982  0.089415
  0.785548  0.096684
  0.762942  0.103402
  0.740179  0.109563
  0.717272  0.115166
  0.694235  0.120205
  0.671081  0.124679
  0.647824  0.128585
  0.624479  0.131920
  0.601059  0.134682
  0.577578  0.136870
  0.554051  0.138482
  0.530492  0.139517
  0.506914  0.139975
  0.483332  0.139856
  0.459760  0.139159
  0.436212  0.137885
  0.412702  0.136034
  0.389245  0.133609
  0.365854  0.130610
  0.342544  0.127038
  0.319328  0.122897
  0.296221  0.118189
  0.273236  0.112916
  0.250386  0.107082
  0.227687  0.100690
  0.205151  0.093744
  0.182791  0.086248
  0.160622  0.078207
  0.138657  0.069625
  0.116908  0.060508
  0.095390  0.050862
  0.074113  0.040690
  0.053093  0.030001
  0.032340  0.018801
  0.011868  0.007095
  0.009696  0.005654
  0.007693  0.003987
  0.005882  0.002113
  0.004284  0.000054
  0.002918 -0.002166
  0.001800 -0.004521
  0.000943 -0.006982
  0.000357 -0.009522
  0.000050 -0.012110
  0.000023 -0.014716
  0.000279 -0.017310
  0.000814 -0.019861
  0.001622 -0.022339
  0.002692 -0.024716
  0.004014 -0.026962
  0.005570 -0.029053
  0.007344 -0.030963
  0.009313 -0.032670
  0.011456 -0.034154
  0.013746 -0.035398
  0.016158 -0.036387
  0.018662 -0.037109
  0.021230 -0.037557
  0.023831 -0.037724
  0.026435 -0.037609
  0.029011 -0.037213
  0.031529 -0.036541
  0.033960 -0.035600
  0.036275 -0.034402
  0.056399 -0.022907
  0.076807 -0.011926
  0.097488 -0.001464
  0.118426  0.008469
  0.139610  0.017869
  0.161025  0.026730
  0.182657  0.035045
  0.204494  0.042809
  0.226520  0.050018
  0.248721  0.056666
  0.271084  0.062750
  0.293594  0.068265
  0.316236  0.073208
  0.338996  0.077576
  0.361860  0.081366
  0.384812  0.084576
  0.407839  0.087202
  0.430924  0.089245
  0.454054  0.090702
  0.477213  0.091573
  0.500387  0.091857
  0.523560  0.091554
  0.546719  0.090663
  0.569847  0.089186
  0.592931  0.087124
  0.615955  0.084478
  0.638905  0.081249
  0.661765  0.077440
  0.684522  0.073052
  0.707160  0.068090
  0.739698  0.060525
  0.772235  0.052959
  0.804773  0.045393
  0.837311  0.037828
  0.869849  0.030262
  0.902387  0.022697
  0.934924  0.015131
  0.967462  0.007566
  1.000000  0.000000
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Polars for Cambered plate C=14% T=5% R=0.96 (cp-140-050-gn)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   cp-140-050-gn50,000921.8 at α=13.25°Mach=0 Ncrit=9Xfoil predictionDetails
   cp-140-050-gn50,000517 at α=14.75°Mach=0 Ncrit=5Xfoil predictionDetails
   cp-140-050-gn50,000115.6 at α=7.75°Mach=0 Ncrit=1Xfoil predictionDetails
   cp-140-050-gn100,000924.8 at α=13°Mach=0 Ncrit=9Xfoil predictionDetails
   cp-140-050-gn100,000528 at α=6.75°Mach=0 Ncrit=5Xfoil predictionDetails
   cp-140-050-gn100,000125.2 at α=5.25°Mach=0 Ncrit=1Xfoil predictionDetails
   cp-140-050-gn200,000952.3 at α=5.5°Mach=0 Ncrit=9Xfoil predictionDetails
   cp-140-050-gn200,000542.5 at α=4.5°Mach=0 Ncrit=5Xfoil predictionDetails
   cp-140-050-gn200,000134.6 at α=3°Mach=0 Ncrit=1Xfoil predictionDetails
   cp-140-050-gn500,000953.9 at α=2.75°Mach=0 Ncrit=9Xfoil predictionDetails
   cp-140-050-gn500,000547.9 at α=2.75°Mach=0 Ncrit=5Xfoil predictionDetails
   cp-140-050-gn500,000137.1 at α=6.5°Mach=0 Ncrit=1Xfoil predictionDetails
   cp-140-050-gn1,000,000947.7 at α=2.75°Mach=0 Ncrit=9Xfoil predictionDetails
   cp-140-050-gn1,000,000545 at α=2°Mach=0 Ncrit=5Xfoil predictionDetails
   cp-140-050-gn1,000,000146.3 at α=5.25°Mach=0 Ncrit=1Xfoil predictionDetails
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