Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

WHITCOMB INTEGRAL SUPERCRITICAL AIRFOIL (whitcomb-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: WHITCOMB INTEGRAL SUPERCRITICAL AIRFOIL (whitcomb-il)
Reynolds number: 500,000
Max Cl/Cd: 59.59 at α=6.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-whitcomb-il-500000-n5.txt
Download as CSV file: xf-whitcomb-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: WHITCOMB INTEGRAL SUPERCRITICAL AIRFOIL         
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -17.500  -1.0234   0.09783   0.09406  -0.0455   1.0000   0.0193
 -17.250  -1.0514   0.08879   0.08485  -0.0505   1.0000   0.0193
 -17.000  -1.0738   0.08103   0.07695  -0.0547   1.0000   0.0193
 -16.750  -1.0917   0.07432   0.07009  -0.0583   1.0000   0.0194
 -16.500  -1.1063   0.06847   0.06410  -0.0612   1.0000   0.0194
 -16.250  -1.1180   0.06339   0.05889  -0.0635   1.0000   0.0195
 -16.000  -1.1274   0.05898   0.05436  -0.0653   1.0000   0.0195
 -15.750  -1.1348   0.05515   0.05042  -0.0664   1.0000   0.0196
 -15.500  -1.1407   0.05180   0.04696  -0.0670   1.0000   0.0197
 -15.250  -1.1455   0.04884   0.04390  -0.0671   1.0000   0.0198
 -15.000  -1.1492   0.04623   0.04119  -0.0669   1.0000   0.0199
 -14.750  -1.1522   0.04392   0.03879  -0.0662   1.0000   0.0200
 -14.500  -1.1545   0.04183   0.03662  -0.0652   1.0000   0.0201
 -14.250  -1.1560   0.03995   0.03465  -0.0640   1.0000   0.0203
 -14.000  -1.1566   0.03823   0.03285  -0.0626   1.0000   0.0204
 -13.750  -1.1570   0.03665   0.03118  -0.0609   1.0000   0.0205
 -13.500  -1.1566   0.03521   0.02966  -0.0590   1.0000   0.0207
 -13.250  -1.1559   0.03388   0.02826  -0.0570   1.0000   0.0209
 -13.000  -1.1551   0.03266   0.02697  -0.0548   1.0000   0.0211
 -12.750  -1.1549   0.03153   0.02577  -0.0522   1.0000   0.0213
 -12.500  -1.1427   0.03034   0.02449  -0.0519   0.9990   0.0215
 -12.250  -1.1289   0.02922   0.02327  -0.0518   0.9976   0.0218
 -12.000  -1.1142   0.02818   0.02214  -0.0517   0.9961   0.0220
 -11.750  -1.0962   0.02695   0.02086  -0.0524   0.9947   0.0223
 -11.500  -1.0751   0.02585   0.01972  -0.0533   0.9937   0.0226
 -11.250  -1.0554   0.02488   0.01871  -0.0537   0.9919   0.0230
 -11.000  -1.0335   0.02401   0.01779  -0.0543   0.9903   0.0234
 -10.750  -1.0099   0.02319   0.01692  -0.0550   0.9889   0.0238
 -10.500  -0.9843   0.02240   0.01609  -0.0561   0.9877   0.0243
 -10.250  -0.9573   0.02166   0.01529  -0.0574   0.9866   0.0249
 -10.000  -0.9299   0.02097   0.01453  -0.0586   0.9858   0.0255
  -9.750  -0.9019   0.02027   0.01379  -0.0599   0.9851   0.0261
  -9.500  -0.8732   0.01960   0.01311  -0.0613   0.9845   0.0269
  -9.250  -0.8437   0.01905   0.01254  -0.0627   0.9840   0.0277
  -9.000  -0.8166   0.01852   0.01198  -0.0635   0.9832   0.0287
  -8.750  -0.7920   0.01801   0.01143  -0.0637   0.9818   0.0296
  -8.500  -0.7646   0.01748   0.01088  -0.0645   0.9806   0.0307
  -8.250  -0.7357   0.01700   0.01041  -0.0656   0.9794   0.0320
  -8.000  -0.7062   0.01659   0.00997  -0.0666   0.9785   0.0335
  -7.750  -0.6764   0.01623   0.00957  -0.0676   0.9778   0.0349
  -7.500  -0.6459   0.01576   0.00913  -0.0689   0.9771   0.0367
  -7.250  -0.6152   0.01540   0.00876  -0.0700   0.9765   0.0385
  -7.000  -0.5841   0.01508   0.00842  -0.0712   0.9760   0.0402
  -6.750  -0.5526   0.01471   0.00807  -0.0725   0.9755   0.0423
  -6.500  -0.5209   0.01439   0.00776  -0.0738   0.9751   0.0448
  -6.250  -0.4889   0.01411   0.00748  -0.0751   0.9746   0.0475
  -6.000  -0.4566   0.01381   0.00722  -0.0765   0.9743   0.0512
  -5.750  -0.4240   0.01354   0.00697  -0.0778   0.9739   0.0557
  -5.500  -0.3911   0.01328   0.00675  -0.0793   0.9736   0.0616
  -5.250  -0.3575   0.01301   0.00655  -0.0809   0.9733   0.0695
  -5.000  -0.3236   0.01275   0.00635  -0.0825   0.9730   0.0786
  -4.750  -0.2896   0.01251   0.00617  -0.0841   0.9727   0.0890
  -4.500  -0.2557   0.01228   0.00601  -0.0858   0.9725   0.1008
  -4.250  -0.2253   0.01205   0.00585  -0.0866   0.9716   0.1142
  -4.000  -0.1937   0.01181   0.00572  -0.0878   0.9708   0.1335
  -3.750  -0.1608   0.01157   0.00558  -0.0892   0.9701   0.1553
  -3.500  -0.1260   0.01130   0.00546  -0.0911   0.9696   0.1844
  -3.250  -0.0904   0.01103   0.00534  -0.0932   0.9692   0.2174
  -2.750  -0.0035   0.01007   0.00498  -0.1013   0.9709   0.3567
  -2.500   0.0587   0.00906   0.00490  -0.1099   0.9728   0.5767
  -2.250   0.0790   0.00936   0.00535  -0.1076   0.9679   0.6126
  -2.000   0.1144   0.00932   0.00530  -0.1088   0.9637   0.6273
  -1.750   0.1584   0.00897   0.00491  -0.1117   0.9574   0.6393
  -1.500   0.1930   0.00883   0.00478  -0.1124   0.9494   0.6472
  -1.250   0.2261   0.00867   0.00459  -0.1130   0.9413   0.6546
  -0.250   0.3590   0.01007   0.00433  -0.1143   0.5082   0.6725
   0.000   0.3776   0.01089   0.00470  -0.1121   0.3946   0.6749
   0.250   0.4013   0.01141   0.00491  -0.1112   0.3192   0.6769
   0.500   0.4272   0.01181   0.00505  -0.1107   0.2572   0.6787
   0.750   0.4540   0.01217   0.00516  -0.1105   0.2054   0.6806
   1.000   0.4822   0.01244   0.00525  -0.1106   0.1678   0.6823
   1.250   0.5110   0.01266   0.00531  -0.1109   0.1388   0.6835
   1.500   0.5398   0.01290   0.00539  -0.1111   0.1139   0.6846
   1.750   0.5691   0.01310   0.00548  -0.1114   0.0974   0.6857
   2.000   0.5967   0.01329   0.00560  -0.1113   0.0841   0.6863
   2.250   0.6243   0.01349   0.00573  -0.1111   0.0728   0.6868
   2.500   0.6519   0.01370   0.00588  -0.1110   0.0644   0.6872
   2.750   0.6794   0.01391   0.00605  -0.1108   0.0580   0.6877
   3.000   0.7069   0.01412   0.00624  -0.1106   0.0535   0.6883
   3.250   0.7340   0.01437   0.00645  -0.1103   0.0493   0.6889
   3.500   0.7616   0.01457   0.00666  -0.1101   0.0464   0.6894
   3.750   0.7889   0.01482   0.00688  -0.1099   0.0436   0.6899
   4.000   0.8163   0.01506   0.00712  -0.1097   0.0415   0.6904
   4.250   0.8437   0.01530   0.00736  -0.1095   0.0395   0.6909
   4.500   0.8708   0.01559   0.00763  -0.1093   0.0377   0.6914
   4.750   0.8978   0.01588   0.00792  -0.1090   0.0361   0.6919
   5.000   0.9249   0.01614   0.00820  -0.1087   0.0345   0.6924
   5.250   0.9516   0.01643   0.00849  -0.1084   0.0331   0.6931
   5.500   0.9779   0.01681   0.00885  -0.1080   0.0318   0.6938
   5.750   1.0045   0.01712   0.00920  -0.1077   0.0308   0.6944
   6.000   1.0310   0.01745   0.00955  -0.1073   0.0298   0.6950
   6.250   1.0573   0.01779   0.00991  -0.1070   0.0288   0.6955
   6.500   1.0833   0.01818   0.01031  -0.1065   0.0280   0.6960
   6.750   1.1086   0.01866   0.01079  -0.1060   0.0272   0.6965
   7.000   1.1342   0.01907   0.01125  -0.1055   0.0267   0.6970
   7.250   1.1595   0.01950   0.01173  -0.1049   0.0260   0.6975
   7.500   1.1845   0.01996   0.01223  -0.1044   0.0254   0.6979
   7.750   1.2093   0.02043   0.01273  -0.1037   0.0249   0.6984
   8.000   1.2337   0.02091   0.01325  -0.1031   0.0244   0.6988
   8.250   1.2577   0.02144   0.01381  -0.1023   0.0240   0.6993
   8.500   1.2806   0.02209   0.01448  -0.1014   0.0235   0.6998
   8.750   1.3036   0.02270   0.01516  -0.1005   0.0231   0.7004
   9.000   1.3267   0.02328   0.01582  -0.0996   0.0227   0.7009
   9.250   1.3491   0.02391   0.01653  -0.0986   0.0223   0.7012
   9.500   1.3709   0.02458   0.01727  -0.0975   0.0220   0.7015
   9.750   1.3922   0.02528   0.01806  -0.0964   0.0217   0.7018
  10.000   1.4130   0.02597   0.01883  -0.0952   0.0214   0.7022
  10.250   1.4332   0.02669   0.01964  -0.0939   0.0211   0.7025
  10.500   1.4526   0.02744   0.02046  -0.0925   0.0209   0.7029
  10.750   1.4713   0.02822   0.02133  -0.0910   0.0207   0.7032
  11.000   1.4888   0.02905   0.02225  -0.0893   0.0205   0.7036
  11.250   1.5052   0.02994   0.02322  -0.0875   0.0203   0.7039
  11.500   1.5198   0.03094   0.02430  -0.0855   0.0201   0.7043
  11.750   1.5320   0.03210   0.02556  -0.0831   0.0199   0.7046
  12.000   1.5419   0.03333   0.02691  -0.0804   0.0197   0.7050
  12.250   1.5485   0.03442   0.02814  -0.0771   0.0196   0.7053
  12.500   1.5553   0.03565   0.02952  -0.0740   0.0195   0.7057
  12.750   1.5608   0.03699   0.03102  -0.0709   0.0194   0.7062
  13.000   1.5646   0.03848   0.03268  -0.0678   0.0193   0.7067
  13.250   1.5664   0.04014   0.03450  -0.0646   0.0192   0.7072
  13.500   1.5662   0.04199   0.03652  -0.0614   0.0191   0.7076
  13.750   1.5643   0.04404   0.03874  -0.0584   0.0190   0.7079
  14.000   1.5601   0.04637   0.04125  -0.0557   0.0189   0.7082
  14.250   1.5538   0.04903   0.04409  -0.0532   0.0188   0.7085
  14.500   1.5445   0.05217   0.04741  -0.0512   0.0188   0.7088
  14.750   1.5324   0.05591   0.05135  -0.0500   0.0187   0.7091
  15.000   1.5173   0.06049   0.05613  -0.0500   0.0187   0.7093
  15.250   1.4971   0.06656   0.06242  -0.0519   0.0186   0.7095
  15.500   1.4717   0.07489   0.07100  -0.0567   0.0186   0.7096
  15.750   1.4320   0.08815   0.08457  -0.0665   0.0187   0.7097
  16.000   1.3455   0.11295   0.10977  -0.0837   0.0189   0.7093
<< Back to WHITCOMB INTEGRAL SUPERCRITICAL AIRFOIL (whitcomb-il)

Polar data table (+)

Polar graphs


<< Back to WHITCOMB INTEGRAL SUPERCRITICAL AIRFOIL (whitcomb-il)