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GOE 195 AIRFOIL (goe195-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 195 AIRFOIL (goe195-il)
Reynolds number: 1,000,000
Max Cl/Cd: 139 at α=4°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe195-il-1000000.txt
Download as CSV file: xf-goe195-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 195 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3619   0.09159   0.08997  -0.0321   1.0000   0.0185
  -8.500  -0.3445   0.08932   0.08770  -0.0343   0.9988   0.0188
  -8.250  -0.3268   0.08674   0.08511  -0.0371   0.9972   0.0192
  -8.000  -0.3095   0.08350   0.08188  -0.0411   0.9952   0.0197
  -7.750  -0.2932   0.07980   0.07817  -0.0457   0.9922   0.0205
  -7.500  -0.2691   0.07096   0.06932  -0.0600   0.9866   0.0223
  -7.250  -0.2457   0.05862   0.05694  -0.0781   0.9823   0.0227
  -7.000  -0.2234   0.05616   0.05447  -0.0819   0.9769   0.0231
  -6.750  -0.1965   0.05348   0.05177  -0.0868   0.9726   0.0235
  -6.500  -0.1698   0.04980   0.04806  -0.0928   0.9661   0.0240
  -6.250  -0.1377   0.04373   0.04191  -0.1027   0.9588   0.0253
  -6.000  -0.0841   0.02093   0.01768  -0.1314   0.9486   0.0286
  -5.750  -0.0578   0.01975   0.01646  -0.1318   0.9427   0.0291
  -5.500  -0.0316   0.01859   0.01519  -0.1321   0.9347   0.0298
  -5.250  -0.0046   0.01747   0.01391  -0.1324   0.9273   0.0307
  -5.000   0.0229   0.01638   0.01263  -0.1326   0.9184   0.0318
  -4.750   0.0508   0.01583   0.01188  -0.1326   0.9093   0.0331
  -4.500   0.0786   0.01448   0.01029  -0.1327   0.8986   0.0331
  -4.250   0.1070   0.01162   0.00699  -0.1331   0.8872   0.0296
  -4.000   0.1349   0.01074   0.00591  -0.1329   0.8744   0.0289
  -3.750   0.1626   0.01016   0.00520  -0.1327   0.8596   0.0289
  -3.500   0.1901   0.00965   0.00459  -0.1325   0.8432   0.0290
  -3.250   0.2177   0.00925   0.00408  -0.1323   0.8254   0.0294
  -3.000   0.2451   0.00897   0.00371  -0.1320   0.8067   0.0301
  -2.750   0.2727   0.00868   0.00332  -0.1318   0.7886   0.0305
  -2.500   0.3005   0.00844   0.00299  -0.1317   0.7721   0.0309
  -2.250   0.3284   0.00824   0.00270  -0.1315   0.7578   0.0314
  -1.750   0.3845   0.00792   0.00223  -0.1313   0.7317   0.0322
  -1.500   0.4127   0.00779   0.00203  -0.1312   0.7193   0.0326
  -1.250   0.4408   0.00769   0.00187  -0.1311   0.7065   0.0330
  -1.000   0.4689   0.00762   0.00173  -0.1310   0.6922   0.0335
  -0.750   0.4968   0.00758   0.00163  -0.1308   0.6746   0.0341
  -0.500   0.5244   0.00750   0.00141  -0.1306   0.6483   0.0357
   0.000   0.5776   0.00773   0.00128  -0.1299   0.5682   0.0394
   0.250   0.6050   0.00782   0.00127  -0.1297   0.5506   0.0416
   0.500   0.6330   0.00755   0.00126  -0.1298   0.5403   0.1584
   0.750   0.6609   0.00745   0.00138  -0.1298   0.5322   0.2491
   1.000   0.6886   0.00752   0.00146  -0.1297   0.5241   0.2717
   1.250   0.7164   0.00759   0.00152  -0.1296   0.5162   0.2858
   1.500   0.7441   0.00766   0.00160  -0.1295   0.5093   0.2974
   1.750   0.7721   0.00769   0.00166  -0.1294   0.5026   0.3099
   2.000   0.7997   0.00777   0.00173  -0.1292   0.4962   0.3206
   2.250   0.8278   0.00778   0.00180  -0.1292   0.4911   0.3366
   2.500   0.8556   0.00777   0.00188  -0.1291   0.4845   0.3683
   2.750   0.8832   0.00763   0.00204  -0.1292   0.4756   0.5057
   3.000   0.9106   0.00755   0.00218  -0.1291   0.4657   0.6150
   3.250   0.9343   0.00689   0.00227  -0.1281   0.4586   1.0000
   3.500   0.9617   0.00702   0.00235  -0.1279   0.4486   1.0000
   3.750   0.9892   0.00714   0.00243  -0.1277   0.4349   1.0000
   4.000   1.0161   0.00731   0.00253  -0.1275   0.4172   1.0000
   4.250   1.0428   0.00751   0.00264  -0.1272   0.3937   1.0000
   4.500   1.0684   0.00783   0.00281  -0.1268   0.3617   1.0000
   4.750   1.0929   0.00827   0.00306  -0.1262   0.3224   1.0000
   5.000   1.1162   0.00886   0.00338  -0.1255   0.2733   1.0000
   5.250   1.1402   0.00937   0.00370  -0.1248   0.2379   1.0000
   5.500   1.1644   0.00983   0.00401  -0.1242   0.2077   1.0000
   5.750   1.1878   0.01038   0.00436  -0.1235   0.1692   1.0000
   6.000   1.2092   0.01116   0.00484  -0.1226   0.1211   1.0000
   6.250   1.2325   0.01169   0.00525  -0.1218   0.0990   1.0000
   6.500   1.2560   0.01218   0.00563  -0.1211   0.0791   1.0000
   6.750   1.2758   0.01308   0.00625  -0.1198   0.0396   1.0000
   7.000   1.2990   0.01357   0.00672  -0.1190   0.0334   1.0000
   7.250   1.3230   0.01394   0.00712  -0.1183   0.0316   1.0000
   7.500   1.3460   0.01441   0.00761  -0.1175   0.0294   1.0000
   7.750   1.3674   0.01504   0.00828  -0.1164   0.0268   1.0000
   8.000   1.3912   0.01538   0.00864  -0.1157   0.0259   1.0000
   8.250   1.4141   0.01578   0.00907  -0.1149   0.0246   1.0000
   8.500   1.4361   0.01626   0.00958  -0.1140   0.0232   1.0000
   8.750   1.4550   0.01702   0.01038  -0.1125   0.0215   1.0000
   9.000   1.4760   0.01753   0.01094  -0.1114   0.0207   1.0000
   9.250   1.4977   0.01794   0.01139  -0.1105   0.0198   1.0000
   9.500   1.5188   0.01839   0.01186  -0.1094   0.0188   1.0000
   9.750   1.5386   0.01891   0.01239  -0.1082   0.0178   1.0000
  10.000   1.5512   0.02000   0.01355  -0.1058   0.0166   1.0000
  10.250   1.5711   0.02043   0.01402  -0.1046   0.0162   1.0000
  10.500   1.5890   0.02096   0.01461  -0.1031   0.0156   1.0000
  10.750   1.6044   0.02154   0.01524  -0.1012   0.0150   1.0000
  11.000   1.6183   0.02216   0.01589  -0.0990   0.0145   1.0000
  11.250   1.6309   0.02287   0.01663  -0.0967   0.0139   1.0000
  11.500   1.6374   0.02399   0.01781  -0.0937   0.0133   1.0000
  11.750   1.6426   0.02524   0.01915  -0.0907   0.0129   1.0000
  12.000   1.6554   0.02601   0.01999  -0.0888   0.0125   1.0000
  12.250   1.6657   0.02699   0.02104  -0.0867   0.0122   1.0000
  12.500   1.6748   0.02810   0.02223  -0.0846   0.0118   1.0000
  12.750   1.6833   0.02930   0.02349  -0.0827   0.0115   1.0000
  13.000   1.6912   0.03059   0.02485  -0.0808   0.0112   1.0000
  13.250   1.6979   0.03205   0.02637  -0.0790   0.0109   1.0000
  13.500   1.7015   0.03385   0.02825  -0.0771   0.0106   1.0000
  13.750   1.6994   0.03629   0.03078  -0.0752   0.0103   1.0000
  14.000   1.6886   0.03976   0.03440  -0.0732   0.0101   1.0000
  14.250   1.6891   0.04227   0.03702  -0.0721   0.0099   1.0000
  14.500   1.6917   0.04466   0.03951  -0.0713   0.0098   1.0000
  14.750   1.6928   0.04728   0.04223  -0.0706   0.0097   1.0000
  15.000   1.6917   0.05023   0.04529  -0.0701   0.0095   1.0000
  15.250   1.6902   0.05333   0.04850  -0.0698   0.0094   1.0000
  15.500   1.6874   0.05669   0.05197  -0.0696   0.0092   1.0000
  15.750   1.6839   0.06027   0.05565  -0.0698   0.0090   1.0000
  16.000   1.6799   0.06407   0.05955  -0.0701   0.0089   1.0000
  16.250   1.6758   0.06801   0.06360  -0.0707   0.0087   1.0000
  16.500   1.6703   0.07220   0.06790  -0.0715   0.0086   1.0000
  16.750   1.6633   0.07672   0.07252  -0.0724   0.0085   1.0000
  17.000   1.6555   0.08141   0.07731  -0.0735   0.0084   1.0000
  17.250   1.6465   0.08634   0.08234  -0.0748   0.0083   1.0000
  17.500   1.6353   0.09164   0.08775  -0.0762   0.0082   1.0000
  17.750   1.6231   0.09723   0.09345  -0.0779   0.0081   1.0000
  18.000   1.6101   0.10304   0.09936  -0.0798   0.0081   1.0000
  18.250   1.5967   0.10900   0.10543  -0.0818   0.0080   1.0000
  18.500   1.5819   0.11531   0.11185  -0.0842   0.0079   1.0000
  18.750   1.5673   0.12172   0.11838  -0.0868   0.0078   1.0000
  19.000   1.5520   0.12838   0.12515  -0.0897   0.0077   1.0000
  19.250   1.5368   0.13513   0.13202  -0.0928   0.0077   1.0000
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