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FX 63-137 13.7% smoothed (fx63137sm-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: FX 63-137 13.7% smoothed (fx63137sm-il)
Reynolds number: 1,000,000
Max Cl/Cd: 151.46 at α=3°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx63137sm-il-1000000.txt
Download as CSV file: xf-fx63137sm-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 63-137 13.7% smoothed                        
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.1068   0.09242   0.09066  -0.0925   0.9755   0.0163
 -10.000   0.0271   0.07137   0.06961  -0.1103   0.9310   0.0171
  -9.750  -0.2458   0.02958   0.02692  -0.1594   0.9218   0.0130
  -9.500  -0.1911   0.02282   0.01947  -0.1810   0.9044   0.0132
  -9.250  -0.1574   0.02078   0.01707  -0.1863   0.8888   0.0134
  -9.000  -0.1339   0.01761   0.01347  -0.1898   0.8737   0.0136
  -8.750  -0.1083   0.01636   0.01205  -0.1909   0.8623   0.0139
  -8.500  -0.0810   0.01564   0.01122  -0.1918   0.8526   0.0141
  -8.250  -0.0536   0.01493   0.01038  -0.1925   0.8432   0.0144
  -8.000  -0.0258   0.01428   0.00961  -0.1932   0.8352   0.0147
  -7.750   0.0021   0.01367   0.00889  -0.1937   0.8271   0.0150
  -7.500   0.0306   0.01310   0.00821  -0.1943   0.8198   0.0154
  -7.250   0.0592   0.01264   0.00765  -0.1948   0.8124   0.0159
  -7.000   0.0880   0.01240   0.00729  -0.1952   0.8054   0.0163
  -6.750   0.1177   0.01148   0.00629  -0.1963   0.7989   0.0168
  -6.500   0.1476   0.01098   0.00574  -0.1970   0.7922   0.0173
  -6.250   0.1774   0.01064   0.00534  -0.1977   0.7860   0.0178
  -6.000   0.2075   0.01031   0.00497  -0.1984   0.7796   0.0183
  -5.750   0.2377   0.01003   0.00461  -0.1990   0.7732   0.0189
  -5.500   0.2681   0.00976   0.00429  -0.1996   0.7673   0.0195
  -5.250   0.2997   0.00936   0.00383  -0.2006   0.7610   0.0203
  -5.000   0.3304   0.00911   0.00353  -0.2014   0.7548   0.0214
  -4.750   0.3609   0.00893   0.00333  -0.2020   0.7490   0.0228
  -4.500   0.3918   0.00870   0.00304  -0.2027   0.7427   0.0243
  -4.250   0.4222   0.00854   0.00283  -0.2033   0.7366   0.0265
  -4.000   0.4533   0.00833   0.00262  -0.2040   0.7307   0.0296
  -3.750   0.4839   0.00817   0.00243  -0.2046   0.7244   0.0350
  -3.500   0.5150   0.00800   0.00228  -0.2053   0.7185   0.0491
  -3.250   0.5471   0.00773   0.00215  -0.2064   0.7123   0.0883
  -3.000   0.5787   0.00751   0.00204  -0.2074   0.7060   0.1369
  -2.750   0.6119   0.00719   0.00194  -0.2088   0.7000   0.2213
  -2.500   0.6446   0.00691   0.00189  -0.2101   0.6936   0.3150
  -2.250   0.6747   0.00685   0.00189  -0.2106   0.6870   0.3637
  -2.000   0.7046   0.00682   0.00190  -0.2110   0.6809   0.3908
  -1.750   0.7337   0.00683   0.00192  -0.2112   0.6741   0.4142
  -1.500   0.7626   0.00687   0.00195  -0.2113   0.6677   0.4354
  -1.250   0.7917   0.00688   0.00197  -0.2115   0.6609   0.4480
  -1.000   0.8201   0.00695   0.00199  -0.2115   0.6540   0.4584
  -0.750   0.8490   0.00698   0.00202  -0.2117   0.6474   0.4692
  -0.500   0.8776   0.00703   0.00207  -0.2117   0.6401   0.4834
  -0.250   0.9059   0.00710   0.00212  -0.2117   0.6331   0.4958
   0.000   0.9344   0.00715   0.00216  -0.2118   0.6256   0.5045
   0.250   0.9623   0.00725   0.00221  -0.2117   0.6181   0.5123
   0.500   0.9909   0.00729   0.00227  -0.2118   0.6105   0.5206
   1.000   1.0470   0.00745   0.00240  -0.2118   0.5948   0.5363
   1.250   1.0743   0.00758   0.00247  -0.2116   0.5864   0.5443
   1.500   1.1026   0.00764   0.00255  -0.2117   0.5785   0.5523
   1.750   1.1298   0.00777   0.00264  -0.2115   0.5698   0.5609
   2.000   1.1578   0.00784   0.00273  -0.2115   0.5615   0.5689
   2.500   1.2126   0.00807   0.00294  -0.2113   0.5440   0.5859
   2.750   1.2392   0.00823   0.00306  -0.2110   0.5346   0.5950
   3.000   1.2662   0.00836   0.00318  -0.2109   0.5228   0.6033
   3.250   1.2924   0.00854   0.00333  -0.2105   0.5088   0.6127
   3.500   1.3184   0.00873   0.00348  -0.2102   0.4942   0.6218
   3.750   1.3441   0.00894   0.00364  -0.2098   0.4801   0.6315
   4.000   1.3694   0.00916   0.00383  -0.2093   0.4642   0.6407
   4.250   1.3945   0.00941   0.00402  -0.2088   0.4481   0.6507
   4.500   1.4197   0.00965   0.00423  -0.2084   0.4345   0.6610
   4.750   1.4448   0.00989   0.00444  -0.2079   0.4215   0.6714
   5.000   1.4699   0.01012   0.00466  -0.2074   0.4081   0.6821
   5.250   1.4943   0.01039   0.00490  -0.2069   0.3933   0.6930
   5.500   1.5182   0.01070   0.00517  -0.2062   0.3776   0.7046
   5.750   1.5418   0.01101   0.00545  -0.2055   0.3626   0.7166
   6.000   1.5650   0.01134   0.00574  -0.2047   0.3475   0.7283
   6.250   1.5877   0.01170   0.00606  -0.2038   0.3319   0.7411
   6.500   1.6096   0.01208   0.00640  -0.2028   0.3151   0.7546
   6.750   1.6306   0.01251   0.00677  -0.2017   0.2971   0.7686
   7.000   1.6507   0.01298   0.00718  -0.2004   0.2787   0.7831
   7.250   1.6699   0.01347   0.00762  -0.1989   0.2611   0.7990
   7.500   1.6876   0.01399   0.00808  -0.1972   0.2437   0.8161
   7.750   1.7031   0.01452   0.00857  -0.1950   0.2264   0.8352
   8.000   1.7171   0.01508   0.00910  -0.1926   0.2088   0.8590
   8.250   1.7282   0.01566   0.00967  -0.1896   0.1905   0.8959
   8.500   1.7333   0.01626   0.01025  -0.1855   0.1721   1.0000
   8.750   1.7428   0.01720   0.01105  -0.1826   0.1512   1.0000
   9.000   1.7519   0.01817   0.01191  -0.1797   0.1323   1.0000
   9.250   1.7616   0.01913   0.01280  -0.1769   0.1181   1.0000
   9.500   1.7722   0.02006   0.01368  -0.1744   0.1078   1.0000
   9.750   1.7821   0.02106   0.01465  -0.1719   0.0993   1.0000
  10.000   1.7947   0.02192   0.01552  -0.1699   0.0945   1.0000
  10.250   1.8045   0.02299   0.01657  -0.1676   0.0893   1.0000
  10.500   1.8168   0.02392   0.01753  -0.1657   0.0860   1.0000
  10.750   1.8288   0.02490   0.01855  -0.1638   0.0833   1.0000
  11.000   1.8386   0.02608   0.01974  -0.1618   0.0802   1.0000
  11.250   1.8462   0.02747   0.02115  -0.1597   0.0769   1.0000
  11.500   1.8575   0.02862   0.02236  -0.1580   0.0754   1.0000
  11.750   1.8692   0.02977   0.02357  -0.1565   0.0741   1.0000
  12.000   1.8794   0.03108   0.02493  -0.1549   0.0726   1.0000
  12.250   1.8882   0.03255   0.02644  -0.1533   0.0709   1.0000
  12.500   1.8954   0.03421   0.02814  -0.1517   0.0692   1.0000
  12.750   1.8995   0.03622   0.03019  -0.1499   0.0670   1.0000
  13.000   1.9054   0.03812   0.03216  -0.1484   0.0656   1.0000
  13.250   1.9161   0.03959   0.03370  -0.1473   0.0648   1.0000
  13.500   1.9255   0.04123   0.03540  -0.1463   0.0636   1.0000
  13.750   1.9332   0.04308   0.03731  -0.1452   0.0622   1.0000
  14.000   1.9396   0.04511   0.03938  -0.1441   0.0607   1.0000
  14.250   1.9437   0.04745   0.04176  -0.1430   0.0590   1.0000
  14.500   1.9439   0.05030   0.04468  -0.1419   0.0573   1.0000
  14.750   1.9481   0.05278   0.04724  -0.1410   0.0563   1.0000
  15.000   1.9562   0.05481   0.04935  -0.1404   0.0556   1.0000
  15.250   1.9642   0.05689   0.05150  -0.1399   0.0544   1.0000
  15.500   1.9695   0.05936   0.05402  -0.1393   0.0530   1.0000
  15.750   1.9726   0.06215   0.05686  -0.1388   0.0518   1.0000
  16.000   1.9741   0.06521   0.05997  -0.1384   0.0505   1.0000
  16.250   1.9723   0.06880   0.06363  -0.1381   0.0491   1.0000
  16.500   1.9726   0.07218   0.06710  -0.1379   0.0483   1.0000
  16.750   1.9776   0.07492   0.06993  -0.1378   0.0476   1.0000
  17.000   1.9811   0.07789   0.07299  -0.1378   0.0468   1.0000
  17.250   1.9829   0.08115   0.07633  -0.1379   0.0458   1.0000
  17.500   1.9835   0.08464   0.07989  -0.1381   0.0448   1.0000
  17.750   1.9825   0.08841   0.08373  -0.1385   0.0437   1.0000
  18.000   1.9797   0.09251   0.08789  -0.1390   0.0425   1.0000
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