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FX 63-158 AIRFOIL (fx63158-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: FX 63-158 AIRFOIL (fx63158-il)
Reynolds number: 500,000
Max Cl/Cd: 76.92 at α=2.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx63158-il-500000.txt
Download as CSV file: xf-fx63158-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 63-158 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.1866   0.09893   0.09686  -0.0606   0.9902   0.0174
 -10.750  -0.1867   0.09237   0.09031  -0.0648   0.9876   0.0178
 -10.500  -0.3018   0.10308   0.10094  -0.0490   0.9985   0.0161
 -10.250  -0.1988   0.07488   0.07284  -0.0757   0.9802   0.0180
 -10.000  -0.2119   0.06618   0.06409  -0.0812   0.9756   0.0180
  -9.750  -0.2283   0.05909   0.05693  -0.0859   0.9613   0.0180
  -9.500  -0.2444   0.05275   0.05048  -0.0906   0.9491   0.0180
  -9.250  -0.2561   0.04682   0.04440  -0.0962   0.9368   0.0180
  -9.000  -0.2661   0.04080   0.03809  -0.1043   0.9202   0.0180
  -8.750  -0.3000   0.05407   0.05161  -0.0973   0.9327   0.0175
  -8.500  -0.3014   0.04622   0.04297  -0.1107   0.9096   0.0180
  -8.250  -0.2313   0.03782   0.03417  -0.1281   0.8751   0.0185
  -8.000  -0.2027   0.03523   0.03114  -0.1319   0.8056   0.0188
  -7.750  -0.1923   0.03352   0.02912  -0.1309   0.7695   0.0191
  -7.500  -0.1820   0.03174   0.02703  -0.1295   0.7373   0.0196
  -7.250  -0.1689   0.02992   0.02488  -0.1284   0.7159   0.0204
  -6.500  -0.1123   0.01242   0.00672  -0.1208   0.6550   0.0235
  -6.250  -0.0911   0.01117   0.00508  -0.1206   0.6459   0.0264
  -6.000  -0.0681   0.01017   0.00403  -0.1205   0.6361   0.0276
  -5.750  -0.0444   0.00934   0.00297  -0.1206   0.6277   0.0314
  -5.500  -0.0189   0.00874   0.00205  -0.1207   0.6195   0.0358
  -5.250   0.0060   0.01676   0.00950  -0.1214   0.6200   0.0142
  -5.000   0.0290   0.01574   0.00842  -0.1203   0.6131   0.0137
  -4.750   0.0531   0.01493   0.00755  -0.1195   0.6061   0.0136
  -4.500   0.0775   0.01431   0.00684  -0.1190   0.5987   0.0138
  -4.250   0.1037   0.01379   0.00625  -0.1189   0.5898   0.0142
  -4.000   0.1301   0.01336   0.00572  -0.1189   0.5790   0.0148
  -3.750   0.1583   0.01270   0.00505  -0.1196   0.5678   0.0156
  -3.500   0.1872   0.01234   0.00463  -0.1203   0.5594   0.0169
  -3.250   0.2170   0.01200   0.00421  -0.1211   0.5522   0.0185
  -3.000   0.2471   0.01166   0.00378  -0.1220   0.5455   0.0199
  -2.750   0.2779   0.01142   0.00346  -0.1228   0.5397   0.0219
  -2.500   0.3084   0.01122   0.00326  -0.1235   0.5331   0.0387
  -2.250   0.3401   0.01091   0.00302  -0.1247   0.5272   0.0931
  -2.000   0.3701   0.01081   0.00291  -0.1254   0.5203   0.1078
  -1.750   0.4005   0.01067   0.00281  -0.1263   0.5128   0.1437
  -1.500   0.4345   0.01027   0.00265  -0.1282   0.5045   0.2458
  -1.250   0.4686   0.00989   0.00251  -0.1303   0.4946   0.3363
  -1.000   0.5098   0.00917   0.00249  -0.1343   0.4846   0.5746
  -0.750   0.5378   0.00934   0.00267  -0.1343   0.4769   0.6142
  -0.500   0.5665   0.00943   0.00272  -0.1346   0.4695   0.6232
  -0.250   0.5947   0.00957   0.00279  -0.1347   0.4619   0.6337
   0.000   0.6227   0.00970   0.00291  -0.1347   0.4553   0.6429
   0.250   0.6510   0.00987   0.00302  -0.1348   0.4448   0.6536
   0.500   0.6778   0.01003   0.00316  -0.1346   0.4324   0.6587
   0.750   0.7047   0.01021   0.00326  -0.1345   0.4210   0.6625
   1.000   0.7318   0.01039   0.00335  -0.1344   0.4115   0.6664
   1.250   0.7600   0.01054   0.00344  -0.1346   0.4032   0.6706
   1.500   0.7866   0.01071   0.00359  -0.1344   0.3950   0.6738
   1.750   0.8135   0.01085   0.00374  -0.1343   0.3856   0.6775
   2.000   0.8395   0.01109   0.00390  -0.1340   0.3664   0.6813
   2.250   0.8646   0.01144   0.00410  -0.1337   0.3474   0.6852
   2.500   0.8910   0.01165   0.00428  -0.1335   0.3362   0.6896
   2.750   0.9154   0.01190   0.00454  -0.1329   0.3233   0.6943
   3.000   0.9381   0.01237   0.00488  -0.1320   0.2949   0.7000
   3.250   0.9637   0.01271   0.00513  -0.1317   0.2855   0.7049
   3.500   0.9888   0.01287   0.00533  -0.1313   0.2778   0.7078
   3.750   1.0117   0.01326   0.00564  -0.1306   0.2477   0.7100
   4.000   1.0334   0.01374   0.00599  -0.1297   0.2299   0.7126
   4.250   1.0579   0.01402   0.00626  -0.1292   0.2209   0.7153
   4.500   1.0823   0.01432   0.00653  -0.1289   0.1964   0.7177
   4.750   1.1042   0.01481   0.00689  -0.1281   0.1817   0.7196
   5.000   1.1289   0.01508   0.00715  -0.1278   0.1775   0.7215
   5.250   1.1531   0.01534   0.00741  -0.1274   0.1738   0.7234
   5.500   1.1768   0.01554   0.00767  -0.1268   0.1712   0.7256
   5.750   1.2006   0.01574   0.00793  -0.1262   0.1686   0.7282
   6.000   1.2239   0.01599   0.00823  -0.1256   0.1635   0.7311
   6.250   1.2470   0.01625   0.00854  -0.1249   0.1477   0.7343
   6.500   1.2647   0.01686   0.00904  -0.1235   0.1360   0.7369
   6.750   1.2854   0.01727   0.00943  -0.1225   0.1321   0.7390
   7.000   1.3037   0.01765   0.00983  -0.1211   0.1280   0.7410
   7.250   1.3225   0.01794   0.01019  -0.1197   0.1248   0.7430
   7.500   1.3411   0.01826   0.01058  -0.1183   0.1197   0.7449
   7.750   1.3590   0.01864   0.01102  -0.1168   0.1148   0.7468
   8.000   1.3718   0.01931   0.01163  -0.1147   0.0965   0.7485
   8.250   1.3842   0.02000   0.01229  -0.1125   0.0925   0.7501
   8.500   1.3970   0.02069   0.01300  -0.1105   0.0884   0.7515
   8.750   1.4122   0.02126   0.01365  -0.1089   0.0850   0.7528
   9.000   1.4232   0.02207   0.01451  -0.1068   0.0813   0.7540
   9.250   1.4390   0.02264   0.01515  -0.1054   0.0780   0.7552
   9.500   1.4517   0.02341   0.01591  -0.1037   0.0643   0.7562
   9.750   1.4582   0.02453   0.01699  -0.1014   0.0618   0.7576
  10.000   1.4649   0.02570   0.01820  -0.0993   0.0595   0.7589
  10.250   1.4717   0.02695   0.01952  -0.0974   0.0576   0.7602
  10.500   1.4772   0.02837   0.02106  -0.0955   0.0562   0.7617
  10.750   1.4793   0.03016   0.02297  -0.0937   0.0545   0.7633
  11.000   1.4775   0.03242   0.02532  -0.0918   0.0528   0.7650
  11.250   1.4734   0.03509   0.02808  -0.0902   0.0510   0.7669
  11.500   1.4889   0.03610   0.02920  -0.0899   0.0491   0.7687
  11.750   1.4988   0.03769   0.03089  -0.0894   0.0463   0.7703
  12.000   1.5053   0.03967   0.03293  -0.0888   0.0436   0.7717
  12.250   1.5216   0.04072   0.03408  -0.0887   0.0390   0.7732
  12.500   1.5288   0.04269   0.03606  -0.0884   0.0347   0.7747
  12.750   1.5319   0.04514   0.03850  -0.0880   0.0318   0.7763
  13.000   1.5344   0.04772   0.04115  -0.0877   0.0297   0.7778
  13.250   1.5362   0.05044   0.04397  -0.0875   0.0282   0.7794
  13.500   1.5366   0.05340   0.04701  -0.0874   0.0267   0.7810
  13.750   1.5362   0.05653   0.05023  -0.0873   0.0253   0.7827
  14.000   1.5353   0.05981   0.05359  -0.0874   0.0239   0.7844
  14.250   1.5393   0.06256   0.05644  -0.0877   0.0231   0.7863
  14.500   1.5432   0.06537   0.05934  -0.0880   0.0215   0.7883
  14.750   1.5446   0.06859   0.06264  -0.0884   0.0194   0.7902
  15.000   1.5447   0.07203   0.06614  -0.0889   0.0174   0.7921
  15.250   1.5450   0.07548   0.06966  -0.0895   0.0154   0.7941
  15.500   1.5433   0.07931   0.07354  -0.0902   0.0135   0.7959
  15.750   1.5431   0.08300   0.07732  -0.0911   0.0120   0.7979
  16.000   1.5414   0.08697   0.08136  -0.0920   0.0104   0.7999
  16.250   1.5413   0.09080   0.08529  -0.0930   0.0092   0.8020
  16.500   1.5390   0.09498   0.08955  -0.0942   0.0067   0.8041
  16.750   1.5340   0.09968   0.09431  -0.0956   0.0049   0.8061
  17.000   1.5306   0.10421   0.09892  -0.0971   0.0046   0.8081
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