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WORTMANN FX 62-K-131 AIRFOIL (fx62k131-il) Xfoil prediction polar at RE=200,000 Ncrit=0


Details Polar file
Airfoil: WORTMANN FX 62-K-131 AIRFOIL (fx62k131-il)
Reynolds number: 200,000
Max Cl/Cd: 83.65 at α=6.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx62k131-il-200000.txt
Download as CSV file: xf-fx62k131-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: WORTMANN FX 62-K-131 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
  ------ -------- --------- --------- -------- -------- --------
 -11.750  -0.1813   0.11879   0.11558  -0.0704   0.9776   0.0276
 -11.500  -0.1691   0.11519   0.11197  -0.0721   0.9761   0.0287
 -11.250  -0.1598   0.11148   0.10825  -0.0744   0.9749   0.0299
 -11.000  -0.1508   0.10751   0.10427  -0.0771   0.9738   0.0311
 -10.750  -0.1481   0.10420   0.10097  -0.0783   0.9693   0.0325
 -10.500  -0.1429   0.10022   0.09699  -0.0808   0.9668   0.0342
 -10.250  -0.1408   0.09586   0.09264  -0.0849   0.9647   0.0364
  -9.250  -0.1242   0.07777   0.07460  -0.0945   0.9551   0.0406
  -9.000  -0.1148   0.07379   0.07061  -0.0966   0.9528   0.0424
  -8.750  -0.1079   0.06909   0.06591  -0.0999   0.9511   0.0442
  -8.500  -0.1023   0.06374   0.06056  -0.1046   0.9495   0.0462
  -8.250  -0.1046   0.05861   0.05545  -0.1088   0.9458   0.0477
  -7.500  -0.1423   0.04467   0.04138  -0.1207   0.9255   0.0489
  -7.250  -0.1562   0.04203   0.03841  -0.1237   0.9175   0.0500
  -6.500  -0.1716   0.04686   0.04250  -0.1313   0.9128   0.0525
  -6.250  -0.1468   0.04376   0.03940  -0.1335   0.9107   0.0559
  -6.000  -0.1151   0.04028   0.03528  -0.1384   0.9085   0.0659
  -5.750  -0.1086   0.03843   0.03352  -0.1361   0.9021   0.0684
  -5.500  -0.0808   0.03603   0.03072  -0.1386   0.8986   0.0803
  -5.250  -0.0465   0.03338   0.02788  -0.1420   0.8969   0.0948
  -5.000   0.0042   0.02722   0.02063  -0.1419   0.8959   0.0354
  -4.750   0.0427   0.02394   0.01692  -0.1436   0.8947   0.0306
  -4.500   0.0798   0.02227   0.01502  -0.1451   0.8935   0.0322
  -4.250   0.0896   0.02203   0.01470  -0.1420   0.8861   0.0345
  -4.000   0.1220   0.02067   0.01321  -0.1425   0.8838   0.0352
  -3.750   0.1577   0.01954   0.01201  -0.1439   0.8820   0.0372
  -3.500   0.1997   0.01815   0.01065  -0.1474   0.8806   0.0467
  -3.250   0.2719   0.01477   0.00960  -0.1593   0.8810   0.6335
  -3.000   0.2874   0.01557   0.01040  -0.1559   0.8758   0.6896
  -2.750   0.2987   0.01649   0.01129  -0.1512   0.8705   0.7184
  -2.500   0.3076   0.01754   0.01232  -0.1449   0.8670   0.7455
  -2.250   0.3070   0.01856   0.01336  -0.1380   0.8601   0.7605
  -2.000   0.3222   0.01903   0.01376  -0.1345   0.8558   0.7741
  -1.750   0.3438   0.01908   0.01372  -0.1323   0.8532   0.7794
  -1.500   0.3829   0.01895   0.01343  -0.1348   0.8516   0.7881
  -1.250   0.3863   0.01948   0.01396  -0.1302   0.8431   0.7928
  -1.000   0.4214   0.01936   0.01374  -0.1318   0.8406   0.8001
  -0.750   0.4504   0.01920   0.01351  -0.1316   0.8384   0.8051
  -0.500   0.4641   0.01962   0.01390  -0.1294   0.8309   0.8118
  -0.250   0.4954   0.01951   0.01373  -0.1302   0.8276   0.8175
   0.000   0.5243   0.01932   0.01349  -0.1300   0.8251   0.8222
   0.250   0.5625   0.01918   0.01329  -0.1323   0.8229   0.8287
   0.500   0.5708   0.01952   0.01366  -0.1288   0.8143   0.8337
   0.750   0.6032   0.01931   0.01341  -0.1296   0.8117   0.8389
   1.000   0.6431   0.01907   0.01313  -0.1322   0.8097   0.8438
   1.250   0.6524   0.01938   0.01349  -0.1289   0.8009   0.8482
   1.500   0.6863   0.01911   0.01321  -0.1300   0.7979   0.8526
   1.750   0.7283   0.01882   0.01288  -0.1330   0.7957   0.8570
   2.000   0.7397   0.01897   0.01310  -0.1300   0.7866   0.8609
   2.250   0.7735   0.01857   0.01271  -0.1309   0.7833   0.8647
   2.500   0.8018   0.01860   0.01278  -0.1315   0.7764   0.8691
   2.750   0.8325   0.01834   0.01254  -0.1320   0.7713   0.8724
   3.000   0.8645   0.01794   0.01215  -0.1325   0.7682   0.8757
   3.250   0.8852   0.01807   0.01239  -0.1316   0.7596   0.8801
   3.500   0.9235   0.01775   0.01209  -0.1337   0.7556   0.8834
   3.750   0.9448   0.01770   0.01213  -0.1326   0.7479   0.8871
   4.000   0.9744   0.01736   0.01187  -0.1327   0.7425   0.8906
   4.250   1.0023   0.01726   0.01186  -0.1329   0.7353   0.8942
   4.500   1.0371   0.01703   0.01170  -0.1344   0.7289   0.8977
   4.750   1.0588   0.01685   0.01162  -0.1332   0.7207   0.9013
   5.000   1.0894   0.01643   0.01129  -0.1335   0.7137   0.9046
   5.250   1.1164   0.01603   0.01098  -0.1331   0.7011   0.9084
   5.500   1.1460   0.01554   0.01053  -0.1332   0.6862   0.9119
   5.750   1.1669   0.01523   0.01031  -0.1316   0.6721   0.9155
   6.000   1.1912   0.01504   0.01020  -0.1308   0.6572   0.9191
   6.250   1.2134   0.01501   0.01030  -0.1298   0.6369   0.9232
   6.500   1.2332   0.01489   0.01018  -0.1281   0.6098   0.9270
   6.750   1.2498   0.01494   0.01019  -0.1258   0.5790   0.9310
   7.000   1.2660   0.01525   0.01038  -0.1237   0.5410   0.9350
   7.250   1.2758   0.01578   0.01074  -0.1206   0.4955   0.9394
   7.500   1.2781   0.01645   0.01122  -0.1162   0.4476   0.9447
   7.750   1.2823   0.01749   0.01205  -0.1127   0.3940   0.9497
   8.000   1.2791   0.01873   0.01303  -0.1082   0.3400   0.9554
   8.250   1.2724   0.02048   0.01441  -0.1038   0.2742   0.9619
   8.500   1.2627   0.02246   0.01598  -0.0993   0.2048   0.9690
   8.750   1.2550   0.02468   0.01778  -0.0956   0.1424   0.9773
   9.000   1.2498   0.02684   0.01965  -0.0924   0.0920   0.9998
   9.250   1.2484   0.02959   0.02204  -0.0904   0.0461   0.9999
   9.500   1.2432   0.03283   0.02516  -0.0877   0.0240   0.9999
   9.750   1.2431   0.03567   0.02814  -0.0858   0.0194   0.9999
  10.000   1.2486   0.03803   0.03065  -0.0844   0.0171   0.9999
  10.250   1.2536   0.04044   0.03318  -0.0832   0.0158   0.9999
  10.500   1.2575   0.04298   0.03581  -0.0818   0.0149   0.9999
  10.750   1.2604   0.04571   0.03863  -0.0800   0.0142   0.9999
  11.000   1.2699   0.04832   0.04133  -0.0778   0.0136   0.9999
  11.250   1.2910   0.05054   0.04369  -0.0764   0.0133   0.9999
  11.500   1.3118   0.05293   0.04630  -0.0754   0.0132   0.9999
  11.750   1.3239   0.05540   0.04904  -0.0745   0.0129   0.9999
  12.000   1.3313   0.05795   0.05185  -0.0736   0.0123   0.9999
  12.250   1.3367   0.06085   0.05502  -0.0727   0.0118   0.9999
  12.500   1.3385   0.06386   0.05832  -0.0718   0.0110   0.9999
  12.750   1.3374   0.06769   0.06245  -0.0708   0.0109   0.9999
  13.000   1.3313   0.07214   0.06723  -0.0698   0.0110   0.9999
  13.250   1.3212   0.07693   0.07233  -0.0691   0.0111   0.9999
  13.500   1.3082   0.08206   0.07777  -0.0688   0.0113   0.9999
  13.750   1.2926   0.08767   0.08367  -0.0691   0.0114   0.9999
  14.000   1.2759   0.09360   0.08987  -0.0701   0.0115   0.9999
  14.250   1.2581   0.10004   0.09656  -0.0719   0.0117   0.9999
  14.500   1.2405   0.10680   0.10356  -0.0746   0.0118   0.9999
  14.750   1.2226   0.11411   0.11109  -0.0781   0.0119   0.9999
  15.000   1.2043   0.12213   0.11933  -0.0826   0.0121   0.9999
  15.250   1.1867   0.13049   0.12787  -0.0879   0.0123   0.9999
  15.500   1.1692   0.13963   0.13718  -0.0942   0.0124   0.9999
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