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GOE 528 AIRFOIL (goe528-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 528 AIRFOIL (goe528-il)
Reynolds number: 200,000
Max Cl/Cd: 75.49 at α=7.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe528-il-200000.txt
Download as CSV file: xf-goe528-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 528 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.2228   0.11967   0.11622  -0.0408   1.0000   0.0424
 -10.500  -0.2317   0.11852   0.11515  -0.0385   1.0000   0.0433
 -10.250  -0.2433   0.11764   0.11435  -0.0366   0.9991   0.0444
 -10.000  -0.2400   0.11367   0.11039  -0.0495   0.9923   0.0455
  -9.750  -0.2156   0.10836   0.10507  -0.0497   0.9896   0.0461
  -9.500  -0.1897   0.10452   0.10121  -0.0513   0.9863   0.0475
  -9.250  -0.1694   0.10083   0.09752  -0.0555   0.9817   0.0494
  -9.000  -0.1545   0.09687   0.09355  -0.0624   0.9742   0.0521
  -8.750  -0.1515   0.09196   0.08866  -0.0763   0.9621   0.0532
  -8.500  -0.1229   0.08783   0.08451  -0.0738   0.9608   0.0542
  -8.250  -0.0977   0.08438   0.08105  -0.0763   0.9566   0.0556
  -8.000  -0.0771   0.08085   0.07750  -0.0806   0.9487   0.0578
  -7.750  -0.0630   0.07513   0.07172  -0.1007   0.9332   0.0619
  -7.500  -0.0403   0.07040   0.06699  -0.1015   0.9293   0.0631
  -7.250  -0.0172   0.06803   0.06460  -0.1010   0.9212   0.0647
  -7.000   0.0086   0.06458   0.06110  -0.1060   0.9130   0.0673
  -6.750   0.0132   0.05807   0.05416  -0.1245   0.8915   0.0728
  -6.500   0.0301   0.05487   0.05109  -0.1219   0.8832   0.0738
  -6.250   0.0465   0.05319   0.04942  -0.1201   0.8737   0.0751
  -6.000   0.0637   0.05124   0.04741  -0.1202   0.8639   0.0774
  -5.750   0.0738   0.04621   0.04186  -0.1273   0.8502   0.0858
  -5.500   0.0911   0.04396   0.03971  -0.1260   0.8414   0.0872
  -5.250   0.1089   0.04233   0.03806  -0.1251   0.8315   0.0892
  -5.000   0.1268   0.04040   0.03602  -0.1250   0.8212   0.0932
  -4.750   0.1461   0.03679   0.03197  -0.1271   0.8123   0.1014
  -4.500   0.1644   0.03527   0.03046  -0.1261   0.8015   0.1039
  -4.250   0.1862   0.03326   0.02799  -0.1267   0.7925   0.1161
  -4.000   0.2062   0.03158   0.02639  -0.1258   0.7821   0.1192
  -3.750   0.2281   0.03016   0.02463  -0.1256   0.7723   0.1327
  -3.500   0.2556   0.02255   0.01563  -0.1241   0.7645   0.0711
  -3.250   0.2795   0.02092   0.01372  -0.1232   0.7546   0.0696
  -3.000   0.3059   0.01974   0.01222  -0.1226   0.7457   0.0698
  -2.750   0.3305   0.01867   0.01094  -0.1217   0.7349   0.0694
  -2.500   0.3575   0.01775   0.00975  -0.1211   0.7261   0.0692
  -2.250   0.3830   0.01703   0.00886  -0.1203   0.7155   0.0698
  -2.000   0.4093   0.01646   0.00814  -0.1196   0.7058   0.0709
  -1.750   0.4362   0.01606   0.00758  -0.1190   0.6967   0.0729
  -1.500   0.4608   0.01536   0.00692  -0.1183   0.6866   0.0758
  -1.250   0.4879   0.01497   0.00646  -0.1178   0.6786   0.0788
  -1.000   0.5124   0.01468   0.00616  -0.1169   0.6684   0.0825
  -0.750   0.5386   0.01431   0.00574  -0.1164   0.6606   0.0884
  -0.500   0.5633   0.01409   0.00554  -0.1156   0.6512   0.1000
  -0.250   0.5883   0.01351   0.00520  -0.1149   0.6439   0.1630
   0.000   0.6034   0.01226   0.00533  -0.1128   0.6355   0.5700
   0.250   0.6741   0.01155   0.00520  -0.1211   0.6269   1.0000
   0.500   0.6982   0.01169   0.00521  -0.1202   0.6184   1.0000
   0.750   0.7242   0.01186   0.00520  -0.1197   0.6117   1.0000
   1.000   0.7480   0.01201   0.00527  -0.1188   0.6035   1.0000
   1.250   0.7746   0.01220   0.00527  -0.1184   0.5970   1.0000
   1.500   0.7980   0.01237   0.00541  -0.1174   0.5890   1.0000
   1.750   0.8239   0.01256   0.00545  -0.1169   0.5823   1.0000
   2.000   0.8483   0.01276   0.00560  -0.1162   0.5751   1.0000
   2.250   0.8734   0.01295   0.00570  -0.1156   0.5680   1.0000
   2.500   0.8990   0.01318   0.00584  -0.1151   0.5616   1.0000
   2.750   0.9230   0.01338   0.00600  -0.1143   0.5541   1.0000
   3.000   0.9500   0.01363   0.00611  -0.1140   0.5480   1.0000
   3.250   0.9726   0.01383   0.00634  -0.1130   0.5404   1.0000
   3.500   0.9982   0.01405   0.00648  -0.1125   0.5338   1.0000
   3.750   1.0222   0.01430   0.00671  -0.1118   0.5268   1.0000
   4.000   1.0465   0.01452   0.00689  -0.1111   0.5196   1.0000
   4.250   1.0722   0.01479   0.00709  -0.1107   0.5133   1.0000
   4.500   1.0946   0.01500   0.00734  -0.1097   0.5056   1.0000
   4.750   1.1207   0.01525   0.00749  -0.1093   0.4993   1.0000
   5.000   1.1424   0.01550   0.00780  -0.1082   0.4918   1.0000
   5.250   1.1668   0.01572   0.00799  -0.1076   0.4851   1.0000
   5.500   1.1904   0.01601   0.00828  -0.1069   0.4784   1.0000
   5.750   1.2129   0.01624   0.00853  -0.1059   0.4711   1.0000
   6.000   1.2382   0.01652   0.00875  -0.1055   0.4649   1.0000
   6.250   1.2583   0.01676   0.00909  -0.1042   0.4571   1.0000
   6.500   1.2828   0.01702   0.00929  -0.1036   0.4508   1.0000
   6.750   1.3034   0.01731   0.00968  -0.1024   0.4435   1.0000
   7.000   1.3258   0.01757   0.00993  -0.1015   0.4366   1.0000
   7.250   1.3474   0.01788   0.01027  -0.1005   0.4295   1.0000
   7.500   1.3672   0.01811   0.01054  -0.0991   0.4213   1.0000
   7.750   1.3870   0.01840   0.01085  -0.0978   0.4133   1.0000
   8.000   1.4057   0.01864   0.01111  -0.0962   0.4049   1.0000
   8.250   1.4242   0.01897   0.01148  -0.0947   0.3968   1.0000
   8.500   1.4427   0.01928   0.01182  -0.0932   0.3891   1.0000
   8.750   1.4605   0.01967   0.01225  -0.0917   0.3814   1.0000
   9.000   1.4767   0.02000   0.01260  -0.0898   0.3732   1.0000
   9.250   1.4919   0.02041   0.01306  -0.0878   0.3651   1.0000
   9.500   1.5067   0.02080   0.01347  -0.0858   0.3575   1.0000
   9.750   1.5194   0.02126   0.01399  -0.0834   0.3500   1.0000
  10.000   1.5315   0.02171   0.01448  -0.0810   0.3427   1.0000
  10.250   1.5440   0.02224   0.01505  -0.0787   0.3355   1.0000
  10.500   1.5542   0.02278   0.01565  -0.0761   0.3281   1.0000
  10.750   1.5658   0.02338   0.01627  -0.0739   0.3209   1.0000
  11.000   1.5744   0.02402   0.01700  -0.0714   0.3137   1.0000
  11.250   1.5872   0.02469   0.01766  -0.0695   0.3073   1.0000
  11.500   1.5928   0.02547   0.01860  -0.0669   0.2999   1.0000
  11.750   1.6032   0.02624   0.01933  -0.0649   0.2929   1.0000
  12.000   1.6066   0.02722   0.02048  -0.0623   0.2856   1.0000
  12.250   1.6141   0.02816   0.02137  -0.0602   0.2782   1.0000
  12.500   1.6141   0.02941   0.02281  -0.0576   0.2697   1.0000
  12.750   1.6158   0.03074   0.02415  -0.0554   0.2611   1.0000
  13.000   1.6157   0.03226   0.02577  -0.0533   0.2520   1.0000
  13.250   1.6163   0.03390   0.02749  -0.0515   0.2433   1.0000
  13.500   1.6156   0.03572   0.02933  -0.0497   0.2349   1.0000
  13.750   1.6154   0.03766   0.03141  -0.0483   0.2259   1.0000
  14.000   1.6121   0.03993   0.03372  -0.0468   0.2167   1.0000
  14.250   1.6069   0.04251   0.03636  -0.0456   0.2066   1.0000
  14.500   1.6015   0.04530   0.03926  -0.0446   0.1955   1.0000
  14.750   1.5926   0.04860   0.04261  -0.0438   0.1828   1.0000
  15.000   1.5812   0.05238   0.04642  -0.0433   0.1691   1.0000
  15.250   1.5672   0.05667   0.05071  -0.0431   0.1541   1.0000
  15.500   1.5503   0.06151   0.05553  -0.0432   0.1383   1.0000
  15.750   1.5324   0.06670   0.06069  -0.0436   0.1231   1.0000
  16.000   1.5139   0.07216   0.06611  -0.0443   0.1115   1.0000
  16.250   1.4963   0.07764   0.07158  -0.0451   0.1032   1.0000
  16.500   1.4808   0.08297   0.07693  -0.0460   0.0969   1.0000
  16.750   1.4653   0.08840   0.08235  -0.0472   0.0920   1.0000
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