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WORTMANN FX 62-K-131 AIRFOIL (fx62k131-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: WORTMANN FX 62-K-131 AIRFOIL (fx62k131-il)
Reynolds number: 200,000
Max Cl/Cd: 84.07 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx62k131-il-200000-n5.txt
Download as CSV file: xf-fx62k131-il-200000-n5.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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.0965   0.08876   0.08524  -0.0945   0.9293   0.0223
 -10.250  -0.0943   0.08423   0.08070  -0.0981   0.9250   0.0248
 -10.000  -0.0914   0.07974   0.07620  -0.1023   0.9210   0.0257
  -9.500  -0.1924   0.08886   0.08527  -0.0934   0.9375   0.0189
  -9.250  -0.1799   0.08534   0.08172  -0.0968   0.9318   0.0207
  -9.000  -0.1701   0.08087   0.07724  -0.1013   0.9248   0.0223
  -8.000  -0.1623   0.05525   0.05134  -0.1275   0.8930   0.0155
  -7.750  -0.1626   0.05097   0.04693  -0.1317   0.8852   0.0148
  -7.500  -0.1569   0.04639   0.04209  -0.1354   0.8798   0.0140
  -7.250  -0.1497   0.04188   0.03731  -0.1375   0.8741   0.0130
  -7.000  -0.1386   0.03496   0.02972  -0.1394   0.8690   0.0112
  -6.750  -0.1157   0.03165   0.02592  -0.1406   0.8658   0.0108
  -6.500  -0.0941   0.02918   0.02309  -0.1412   0.8617   0.0107
  -6.250  -0.0703   0.02672   0.02024  -0.1420   0.8581   0.0106
  -6.000  -0.0445   0.02418   0.01729  -0.1428   0.8551   0.0107
  -5.750  -0.0174   0.02188   0.01465  -0.1434   0.8526   0.0110
  -5.500   0.0084   0.02033   0.01286  -0.1436   0.8496   0.0115
  -5.250   0.0334   0.01922   0.01163  -0.1434   0.8462   0.0121
  -5.000   0.0601   0.01849   0.01079  -0.1436   0.8431   0.0138
  -4.750   0.0881   0.01785   0.01002  -0.1438   0.8404   0.0159
  -4.500   0.1164   0.01698   0.00903  -0.1441   0.8381   0.0167
  -4.250   0.1434   0.01581   0.00783  -0.1447   0.8350   0.0183
  -4.000   0.1725   0.01519   0.00713  -0.1456   0.8316   0.0209
  -3.750   0.2030   0.01481   0.00665  -0.1466   0.8285   0.0259
  -3.500   0.2368   0.01419   0.00594  -0.1484   0.8259   0.0357
  -3.250   0.2773   0.01299   0.00535  -0.1527   0.8238   0.1950
  -3.000   0.3200   0.01165   0.00553  -0.1576   0.8209   0.5969
  -2.750   0.3410   0.01207   0.00609  -0.1555   0.8167   0.6753
  -2.500   0.3654   0.01245   0.00640  -0.1542   0.8131   0.7024
  -2.250   0.3909   0.01263   0.00648  -0.1533   0.8103   0.7105
  -2.000   0.4206   0.01270   0.00642  -0.1540   0.8068   0.7179
  -1.750   0.4455   0.01282   0.00649  -0.1534   0.8029   0.7221
  -1.500   0.4749   0.01289   0.00646  -0.1539   0.7997   0.7281
  -1.250   0.5043   0.01294   0.00643  -0.1543   0.7969   0.7334
  -1.000   0.5305   0.01305   0.00648  -0.1540   0.7937   0.7376
  -0.750   0.5591   0.01313   0.00652  -0.1545   0.7895   0.7434
  -0.500   0.5866   0.01320   0.00656  -0.1545   0.7859   0.7476
  -0.250   0.6141   0.01327   0.00658  -0.1544   0.7829   0.7515
   0.000   0.6429   0.01334   0.00663  -0.1548   0.7792   0.7567
   0.250   0.6708   0.01341   0.00670  -0.1552   0.7746   0.7609
   0.500   0.6973   0.01346   0.00674  -0.1549   0.7708   0.7637
   0.750   0.7266   0.01348   0.00674  -0.1553   0.7678   0.7671
   1.000   0.7541   0.01357   0.00686  -0.1556   0.7625   0.7714
   1.250   0.7830   0.01360   0.00690  -0.1561   0.7580   0.7749
   1.500   0.8109   0.01360   0.00690  -0.1561   0.7544   0.7772
   1.750   0.8356   0.01369   0.00707  -0.1557   0.7482   0.7801
   2.000   0.8644   0.01368   0.00707  -0.1561   0.7426   0.7836
   2.250   0.8950   0.01369   0.00709  -0.1570   0.7362   0.7876
   2.500   0.9203   0.01370   0.00716  -0.1565   0.7294   0.7897
   2.750   0.9464   0.01372   0.00726  -0.1563   0.7233   0.7923
   3.000   0.9725   0.01377   0.00738  -0.1561   0.7162   0.7952
   3.250   1.0012   0.01379   0.00745  -0.1565   0.7098   0.7984
   3.500   1.0303   0.01384   0.00759  -0.1571   0.7017   0.8019
   3.750   1.0548   0.01389   0.00773  -0.1565   0.6936   0.8040
   4.000   1.0811   0.01391   0.00781  -0.1562   0.6855   0.8064
   4.250   1.1061   0.01400   0.00801  -0.1558   0.6755   0.8093
   4.500   1.1330   0.01407   0.00816  -0.1559   0.6650   0.8125
   4.750   1.1602   0.01412   0.00830  -0.1559   0.6503   0.8157
   5.000   1.1819   0.01416   0.00832  -0.1546   0.6262   0.8177
   5.250   1.2025   0.01431   0.00841  -0.1530   0.5954   0.8202
   5.500   1.2240   0.01456   0.00862  -0.1519   0.5693   0.8231
   5.750   1.2450   0.01493   0.00893  -0.1507   0.5411   0.8262
   6.000   1.2630   0.01550   0.00937  -0.1492   0.5014   0.8292
   6.250   1.2718   0.01623   0.00991  -0.1458   0.4506   0.8316
   6.500   1.2766   0.01715   0.01058  -0.1418   0.3976   0.8345
   6.750   1.2775   0.01821   0.01140  -0.1374   0.3468   0.8378
   7.000   1.2783   0.01964   0.01251  -0.1334   0.2864   0.8412
   7.250   1.2770   0.02129   0.01381  -0.1294   0.2220   0.8442
   7.500   1.2752   0.02299   0.01519  -0.1255   0.1642   0.8469
   7.750   1.2788   0.02453   0.01654  -0.1226   0.1243   0.8497
   8.000   1.2851   0.02602   0.01789  -0.1202   0.0932   0.8526
   8.250   1.2898   0.02775   0.01943  -0.1179   0.0604   0.8555
   8.500   1.2950   0.02939   0.02095  -0.1156   0.0381   0.8581
   8.750   1.2988   0.03110   0.02261  -0.1131   0.0221   0.8606
   9.000   1.3052   0.03270   0.02425  -0.1110   0.0141   0.8631
   9.250   1.3136   0.03423   0.02590  -0.1091   0.0101   0.8658
   9.500   1.3194   0.03606   0.02781  -0.1072   0.0081   0.8686
   9.750   1.3275   0.03773   0.02964  -0.1055   0.0071   0.8712
  10.000   1.3332   0.03946   0.03154  -0.1035   0.0065   0.8736
  10.250   1.3388   0.04129   0.03352  -0.1017   0.0060   0.8760
  10.500   1.3438   0.04323   0.03561  -0.1000   0.0058   0.8787
  10.750   1.3475   0.04537   0.03790  -0.0983   0.0055   0.8815
  11.000   1.3492   0.04780   0.04047  -0.0966   0.0052   0.8841
  11.250   1.3483   0.05036   0.04319  -0.0947   0.0051   0.8864
  11.500   1.3466   0.05308   0.04606  -0.0928   0.0050   0.8887
  11.750   1.3478   0.05563   0.04877  -0.0912   0.0049   0.8911
  12.000   1.3488   0.05828   0.05163  -0.0898   0.0048   0.8938
  12.250   1.3505   0.06099   0.05451  -0.0884   0.0047   0.8966
  12.500   1.3522   0.06367   0.05737  -0.0871   0.0046   0.8992
  12.750   1.3536   0.06635   0.06025  -0.0859   0.0044   0.9018
  13.000   1.3546   0.06919   0.06328  -0.0849   0.0042   0.9046
  13.250   1.3553   0.07218   0.06646  -0.0842   0.0040   0.9075
  13.500   1.3550   0.07542   0.06988  -0.0837   0.0038   0.9105
  13.750   1.3537   0.07865   0.07329  -0.0835   0.0035   0.9139
  14.000   1.3503   0.08219   0.07701  -0.0832   0.0034   0.9176
  14.250   1.3460   0.08610   0.08109  -0.0834   0.0033   0.9215
  14.750   1.3327   0.09480   0.09018  -0.0841   0.0031   0.9298
  15.000   1.3235   0.09979   0.09539  -0.0850   0.0031   0.9346
  15.250   1.3134   0.10491   0.10072  -0.0861   0.0031   0.9408
  15.500   1.3019   0.11035   0.10639  -0.0875   0.0030   0.9500
  15.750   1.2879   0.11590   0.11215  -0.0892   0.0030   0.9996
  16.000   1.2776   0.12255   0.11903  -0.0926   0.0030   0.9999
  16.250   1.2665   0.12952   0.12621  -0.0965   0.0030   0.9999
  16.500   1.2532   0.13729   0.13420  -0.1011   0.0030   0.9999
  16.750   1.2429   0.14479   0.14190  -0.1059   0.0030   0.9999
  17.000   1.2299   0.15352   0.15083  -0.1117   0.0030   0.9999
  17.250   1.2179   0.16244   0.15994  -0.1179   0.0030   0.9999
  17.500   1.2040   0.17297   0.17068  -0.1253   0.0031   0.9999
  17.750   1.1790   0.18889   0.18684  -0.1359   0.0033   0.9999
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