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Cambered plate C=6% T=5% R=2.11 (cp-060-050-gn)

Cambered plate C=6% T=5% R=2.11 - HAWT pipe blade with coordinates based on top surface. Camber=6% Wall thickness=5% Radius=2.113


Airfoil cp-060-050-gn
Details Dat file Parser  
(cp-060-050-gn) Cambered plate C=6% T=5% R=2.11
HAWT pipe blade with coordinates based on top surface. Camber=6% Wall thickness=5% Radius=2.113
Max thickness 10.8% at 6.3% chord.
Max camber 2.7% at 52.1% chord
Source Generated
Source dat file
The dat file is in Selig format
Cambered plate C=6% T=5% R=2.11
  1.000000  0.000000
  0.978618  0.005089
  0.957184  0.009955
  0.935701  0.014599
  0.914170  0.019018
  0.892595  0.023214
  0.870977  0.027184
  0.849319  0.030930
  0.827624  0.034450
  0.805893  0.037745
  0.784128  0.040813
  0.762334  0.043655
  0.740510  0.046270
  0.718661  0.048657
  0.696788  0.050818
  0.674894  0.052751
  0.652981  0.054456
  0.631051  0.055933
  0.609107  0.057182
  0.587151  0.058202
  0.565186  0.058994
  0.543214  0.059558
  0.521237  0.059893
  0.499258  0.060000
  0.477279  0.059878
  0.455302  0.059527
  0.433331  0.058948
  0.411366  0.058141
  0.389411  0.057105
  0.367468  0.055840
  0.345540  0.054348
  0.323628  0.052627
  0.301735  0.050679
  0.279863  0.048503
  0.258016  0.046100
  0.236194  0.043470
  0.214401  0.040613
  0.192639  0.037529
  0.170911  0.034220
  0.149217  0.030684
  0.127562  0.026923
  0.105947  0.022937
  0.084375  0.018727
  0.062848  0.014292
  0.041368  0.009634
  0.035859  0.008092
  0.030549  0.005963
  0.025500  0.003273
  0.020772  0.000053
  0.016420 -0.003660
  0.012494 -0.007821
  0.009042 -0.012383
  0.006103 -0.017291
  0.003711 -0.022488
  0.001896 -0.027913
  0.000678 -0.033502
  0.000072 -0.039191
  0.000084 -0.044911
  0.000714 -0.050597
  0.001956 -0.056181
  0.003794 -0.061599
  0.006206 -0.066786
  0.009166 -0.071681
  0.012638 -0.076228
  0.016580 -0.080373
  0.020948 -0.084067
  0.025690 -0.087268
  0.030750 -0.089937
  0.036069 -0.092043
  0.041584 -0.093562
  0.047231 -0.094476
  0.052944 -0.094773
  0.058656 -0.094452
  0.064299 -0.093514
  0.087202 -0.088563
  0.110161 -0.083879
  0.133174 -0.079463
  0.156236 -0.075316
  0.179345 -0.071439
  0.202498 -0.067831
  0.225691 -0.064494
  0.248922 -0.061428
  0.272186 -0.058634
  0.295482 -0.056111
  0.318806 -0.053860
  0.342155 -0.051881
  0.415248 -0.046117
  0.488342 -0.040352
  0.561436 -0.034588
  0.634530 -0.028823
  0.707624 -0.023058
  0.780718 -0.017294
  0.853812 -0.011529
  0.926906 -0.005765
  1.000000  0.000000
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Polars for Cambered plate C=6% T=5% R=2.11 (cp-060-050-gn)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   cp-060-050-gn50,000919.6 at α=7.5°Mach=0 Ncrit=9Xfoil predictionDetails
   cp-060-050-gn50,000520.1 at α=8.75°Mach=0 Ncrit=5Xfoil predictionDetails
   cp-060-050-gn50,000121.2 at α=11°Mach=0 Ncrit=1Xfoil predictionDetails
   cp-060-050-gn100,000922.4 at α=7.75°Mach=0 Ncrit=9Xfoil predictionDetails
   cp-060-050-gn100,000525 at α=8.75°Mach=0 Ncrit=5Xfoil predictionDetails
   cp-060-050-gn100,000128 at α=10°Mach=0 Ncrit=1Xfoil predictionDetails
   cp-060-050-gn200,000926.1 at α=7.5°Mach=0 Ncrit=9Xfoil predictionDetails
   cp-060-050-gn200,000531.4 at α=9.75°Mach=0 Ncrit=5Xfoil predictionDetails
   cp-060-050-gn200,000135.7 at α=10.5°Mach=0 Ncrit=1Xfoil predictionDetails
   cp-060-050-gn500,000935.9 at α=8.75°Mach=0 Ncrit=9Xfoil predictionDetails
   cp-060-050-gn500,000545.2 at α=12.5°Mach=0 Ncrit=5Xfoil predictionDetails
   cp-060-050-gn500,000150 at α=11°Mach=0 Ncrit=1Xfoil predictionDetails
   cp-060-050-gn1,000,000951.4 at α=12°Mach=0 Ncrit=9Xfoil predictionDetails
   cp-060-050-gn1,000,000560.1 at α=13°Mach=0 Ncrit=5Xfoil predictionDetails
   cp-060-050-gn1,000,000164.2 at α=11.5°Mach=0 Ncrit=1Xfoil predictionDetails
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