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FX 62-K-153/20 AIRFOIL (fx62k153-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: FX 62-K-153/20 AIRFOIL (fx62k153-il)
Reynolds number: 200,000
Max Cl/Cd: 79.86 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx62k153-il-200000-n5.txt
Download as CSV file: xf-fx62k153-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 62-K-153/20 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.1808   0.08800   0.08399  -0.1129   0.9005   0.0107
 -10.750  -0.1837   0.08209   0.07808  -0.1165   0.8949   0.0106
 -10.500  -0.1901   0.07499   0.07097  -0.1212   0.8902   0.0105
 -10.250  -0.2081   0.06373   0.05969  -0.1299   0.8844   0.0102
 -10.000  -0.2354   0.05415   0.04991  -0.1374   0.8781   0.0099
  -9.750  -0.2582   0.04761   0.04311  -0.1412   0.8720   0.0097
  -9.500  -0.2758   0.04270   0.03792  -0.1427   0.8657   0.0097
  -9.250  -0.2827   0.03836   0.03318  -0.1446   0.8612   0.0099
  -9.000  -0.2807   0.03474   0.02917  -0.1452   0.8572   0.0103
  -8.750  -0.2731   0.03127   0.02518  -0.1454   0.8534   0.0112
  -8.500  -0.2589   0.02851   0.02192  -0.1455   0.8503   0.0122
  -8.250  -0.2370   0.02761   0.02091  -0.1461   0.8478   0.0130
  -8.000  -0.2149   0.02615   0.01919  -0.1464   0.8456   0.0139
  -7.750  -0.1951   0.02450   0.01723  -0.1458   0.8427   0.0150
  -7.500  -0.1734   0.02314   0.01557  -0.1453   0.8400   0.0163
  -7.250  -0.1501   0.02245   0.01488  -0.1455   0.8374   0.0178
  -7.000  -0.1253   0.02170   0.01399  -0.1456   0.8351   0.0196
  -6.750  -0.0997   0.02089   0.01298  -0.1455   0.8331   0.0213
  -6.500  -0.0750   0.01998   0.01205  -0.1456   0.8314   0.0233
  -6.250  -0.0526   0.01937   0.01140  -0.1452   0.8288   0.0247
  -6.000  -0.0297   0.01876   0.01074  -0.1448   0.8260   0.0263
  -5.750  -0.0048   0.01827   0.01016  -0.1448   0.8234   0.0284
  -5.500   0.0208   0.01757   0.00945  -0.1453   0.8212   0.0312
  -5.250   0.0487   0.01706   0.00888  -0.1460   0.8193   0.0341
  -5.000   0.0782   0.01660   0.00830  -0.1470   0.8175   0.0379
  -4.750   0.1070   0.01612   0.00781  -0.1480   0.8155   0.0464
  -4.500   0.1335   0.01575   0.00748  -0.1486   0.8128   0.0602
  -4.250   0.1621   0.01532   0.00714  -0.1496   0.8102   0.0894
  -4.000   0.1955   0.01438   0.00671  -0.1525   0.8080   0.2095
  -3.750   0.2351   0.01306   0.00669  -0.1571   0.8062   0.5304
  -3.500   0.2625   0.01329   0.00700  -0.1567   0.8043   0.5896
  -3.250   0.2916   0.01354   0.00718  -0.1567   0.8026   0.6192
  -3.000   0.3183   0.01397   0.00755  -0.1562   0.8003   0.6456
  -2.750   0.3381   0.01458   0.00819  -0.1539   0.7970   0.6628
  -2.500   0.3645   0.01482   0.00836  -0.1536   0.7942   0.6722
  -2.250   0.3932   0.01487   0.00832  -0.1540   0.7918   0.6761
  -2.000   0.4211   0.01495   0.00832  -0.1541   0.7897   0.6790
  -1.750   0.4514   0.01497   0.00826  -0.1547   0.7879   0.6827
  -1.500   0.4823   0.01499   0.00819  -0.1558   0.7856   0.6876
  -1.250   0.5076   0.01510   0.00829  -0.1557   0.7820   0.6907
  -1.000   0.5336   0.01520   0.00836  -0.1555   0.7790   0.6930
  -0.750   0.5619   0.01524   0.00837  -0.1557   0.7764   0.6957
  -0.500   0.5925   0.01524   0.00832  -0.1565   0.7742   0.6990
  -0.250   0.6264   0.01519   0.00819  -0.1582   0.7723   0.7032
   0.000   0.6501   0.01534   0.00836  -0.1577   0.7680   0.7057
   0.250   0.6755   0.01542   0.00847  -0.1574   0.7643   0.7078
   0.500   0.7038   0.01544   0.00849  -0.1577   0.7614   0.7101
   0.750   0.7346   0.01542   0.00844  -0.1585   0.7589   0.7127
   1.000   0.7641   0.01544   0.00846  -0.1592   0.7558   0.7158
   1.250   0.7909   0.01554   0.00858  -0.1595   0.7507   0.7195
   1.500   0.8182   0.01551   0.00858  -0.1595   0.7468   0.7211
   1.750   0.8485   0.01544   0.00850  -0.1600   0.7438   0.7229
   2.000   0.8724   0.01557   0.00871  -0.1596   0.7392   0.7252
   2.250   0.8981   0.01566   0.00886  -0.1595   0.7348   0.7278
   2.500   0.9280   0.01565   0.00887  -0.1601   0.7314   0.7305
   2.750   0.9612   0.01558   0.00882  -0.1615   0.7287   0.7334
   3.000   0.9826   0.01579   0.00913  -0.1606   0.7228   0.7355
   3.250   1.0083   0.01584   0.00926  -0.1604   0.7185   0.7374
   3.500   1.0383   0.01577   0.00923  -0.1609   0.7150   0.7394
   3.750   1.0597   0.01586   0.00943  -0.1599   0.7067   0.7417
   4.000   1.0897   0.01561   0.00920  -0.1603   0.6989   0.7443
   4.250   1.1126   0.01565   0.00931  -0.1596   0.6885   0.7472
   4.500   1.1383   0.01568   0.00943  -0.1594   0.6807   0.7496
   4.750   1.1635   0.01567   0.00951  -0.1590   0.6728   0.7512
   5.000   1.1854   0.01574   0.00967  -0.1580   0.6621   0.7531
   5.250   1.2082   0.01572   0.00970  -0.1570   0.6479   0.7554
   5.500   1.2316   0.01570   0.00969  -0.1562   0.6302   0.7580
   5.750   1.2531   0.01577   0.00973  -0.1550   0.6066   0.7606
   6.000   1.2738   0.01595   0.00981  -0.1537   0.5792   0.7631
   6.250   1.2890   0.01625   0.01003  -0.1514   0.5513   0.7649
   6.500   1.3008   0.01669   0.01041  -0.1485   0.5232   0.7670
   6.750   1.3117   0.01730   0.01093  -0.1457   0.4937   0.7694
   7.000   1.3211   0.01804   0.01158  -0.1427   0.4642   0.7720
   7.250   1.3277   0.01897   0.01240  -0.1395   0.4316   0.7746
   7.500   1.3299   0.02018   0.01344  -0.1359   0.3944   0.7772
   7.750   1.3292   0.02160   0.01469  -0.1320   0.3522   0.7793
   8.000   1.3247   0.02334   0.01621  -0.1279   0.3080   0.7815
   8.250   1.3230   0.02509   0.01781  -0.1244   0.2701   0.7839
   8.500   1.3228   0.02689   0.01943  -0.1214   0.2334   0.7863
   8.750   1.3249   0.02865   0.02104  -0.1188   0.2013   0.7888
   9.000   1.3290   0.03034   0.02260  -0.1166   0.1691   0.7911
   9.250   1.3324   0.03211   0.02424  -0.1143   0.1441   0.7932
   9.500   1.3384   0.03366   0.02576  -0.1123   0.1245   0.7952
   9.750   1.3447   0.03522   0.02731  -0.1104   0.1091   0.7975
  10.000   1.3516   0.03678   0.02887  -0.1087   0.0959   0.8000
  10.250   1.3585   0.03839   0.03050  -0.1070   0.0837   0.8026
  10.500   1.3655   0.04003   0.03215  -0.1055   0.0729   0.8050
  11.000   1.3788   0.04342   0.03557  -0.1024   0.0562   0.8094
  11.250   1.3863   0.04506   0.03729  -0.1010   0.0497   0.8117
  11.500   1.3921   0.04689   0.03915  -0.0996   0.0443   0.8143
  11.750   1.4000   0.04859   0.04096  -0.0984   0.0402   0.8172
  12.000   1.4067   0.05045   0.04289  -0.0972   0.0359   0.8202
  12.250   1.4128   0.05238   0.04491  -0.0960   0.0319   0.8229
  12.500   1.4187   0.05429   0.04688  -0.0948   0.0275   0.8254
  12.750   1.4237   0.05636   0.04902  -0.0937   0.0240   0.8281
  13.000   1.4291   0.05843   0.05119  -0.0927   0.0211   0.8311
  13.250   1.4321   0.06082   0.05363  -0.0917   0.0184   0.8342
  13.500   1.4371   0.06303   0.05599  -0.0908   0.0159   0.8373
  13.750   1.4380   0.06567   0.05870  -0.0897   0.0135   0.8405
  14.000   1.4406   0.06820   0.06140  -0.0888   0.0115   0.8443
  14.250   1.4408   0.07107   0.06436  -0.0880   0.0100   0.8482
  14.500   1.4403   0.07410   0.06753  -0.0873   0.0089   0.8521
  14.750   1.4394   0.07719   0.07078  -0.0867   0.0079   0.8563
  15.000   1.4377   0.08047   0.07423  -0.0862   0.0074   0.8609
  15.500   1.4308   0.08762   0.08168  -0.0857   0.0066   0.8714
  15.750   1.4266   0.09138   0.08564  -0.0857   0.0064   0.8781
  16.000   1.4214   0.09527   0.08972  -0.0857   0.0061   0.8865
  16.250   1.4158   0.09917   0.09380  -0.0859   0.0059   0.8993
  16.500   1.4065   0.10285   0.09767  -0.0854   0.0056   0.9460
  16.750   1.4009   0.10709   0.10207  -0.0864   0.0055   0.9999
  17.000   1.3958   0.11166   0.10679  -0.0878   0.0053   0.9999
  17.250   1.3897   0.11649   0.11176  -0.0895   0.0051   0.9999
  17.500   1.3826   0.12159   0.11700  -0.0914   0.0050   0.9999
  17.750   1.3747   0.12696   0.12252  -0.0938   0.0049   0.9999
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