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FX 63-120 AIRFOIL (fx63120-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: FX 63-120 AIRFOIL (fx63120-il)
Reynolds number: 200,000
Max Cl/Cd: 93.66 at α=5.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx63120-il-200000.txt
Download as CSV file: xf-fx63120-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 63-120 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
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.3114   0.11579   0.11225  -0.0432   1.0000   0.0493
 -10.000  -0.3274   0.11381   0.11036  -0.0437   1.0000   0.0497
  -9.750  -0.3449   0.11223   0.10888  -0.0425   1.0000   0.0498
  -9.500  -0.3384   0.10878   0.10546  -0.0386   1.0000   0.0506
  -9.250  -0.3391   0.10759   0.10432  -0.0350   1.0000   0.0512
  -9.000  -0.3232   0.10502   0.10174  -0.0359   0.9982   0.0528
  -8.750  -0.3043   0.10112   0.09784  -0.0408   0.9949   0.0557
  -8.500  -0.3042   0.09437   0.09112  -0.0582   0.9855   0.0595
  -8.250  -0.2846   0.08939   0.08613  -0.0583   0.9839   0.0609
  -8.000  -0.2627   0.08691   0.08364  -0.0585   0.9793   0.0624
  -7.750  -0.2418   0.08352   0.08024  -0.0624   0.9749   0.0652
  -7.500  -0.2323   0.07907   0.07580  -0.0689   0.9655   0.0688
  -7.250  -0.2280   0.06555   0.06227  -0.0944   0.9502   0.0725
  -7.000  -0.2033   0.06640   0.06313  -0.0875   0.9489   0.0741
  -6.750  -0.1839   0.06429   0.06102  -0.0886   0.9420   0.0775
  -6.500  -0.1470   0.04848   0.04480  -0.1222   0.9340   0.0873
  -6.250  -0.1286   0.04726   0.04366  -0.1207   0.9261   0.0904
  -6.000  -0.0615   0.03012   0.02461  -0.1448   0.9227   0.0585
  -5.750  -0.0154   0.02652   0.02053  -0.1503   0.9213   0.0583
  -5.500   0.0311   0.02342   0.01702  -0.1550   0.9201   0.0576
  -5.250   0.0706   0.02165   0.01490  -0.1577   0.9161   0.0584
  -5.000   0.1078   0.02038   0.01334  -0.1597   0.9111   0.0600
  -4.750   0.1478   0.01850   0.01136  -0.1623   0.9082   0.0615
  -4.500   0.1891   0.01732   0.01015  -0.1650   0.9057   0.0638
  -4.250   0.2267   0.01656   0.00935  -0.1668   0.9013   0.0675
  -4.000   0.2592   0.01594   0.00866  -0.1676   0.8944   0.0702
  -3.750   0.2994   0.01490   0.00764  -0.1701   0.8902   0.0741
  -3.500   0.3350   0.01433   0.00708  -0.1717   0.8837   0.0810
  -3.250   0.3712   0.01367   0.00644  -0.1735   0.8761   0.0921
  -3.000   0.4211   0.01196   0.00570  -0.1792   0.8714   0.3523
  -2.750   0.4488   0.01200   0.00581  -0.1790   0.8620   0.4299
  -2.500   0.4823   0.01196   0.00574  -0.1798   0.8559   0.4651
  -2.250   0.5092   0.01205   0.00584  -0.1794   0.8473   0.4917
  -2.000   0.5399   0.01213   0.00590  -0.1796   0.8406   0.5206
  -1.750   0.5665   0.01231   0.00612  -0.1789   0.8327   0.5457
  -1.500   0.5950   0.01243   0.00623  -0.1786   0.8254   0.5672
  -1.250   0.6230   0.01254   0.00632  -0.1783   0.8182   0.5836
  -1.000   0.6509   0.01258   0.00635  -0.1780   0.8104   0.5959
  -0.750   0.6809   0.01261   0.00631  -0.1782   0.8038   0.6080
  -0.500   0.7077   0.01267   0.00638  -0.1778   0.7954   0.6203
  -0.250   0.7380   0.01267   0.00634  -0.1780   0.7893   0.6316
   0.000   0.7639   0.01272   0.00642  -0.1775   0.7802   0.6434
   0.250   0.7943   0.01272   0.00637  -0.1777   0.7737   0.6570
   0.500   0.8204   0.01280   0.00649  -0.1772   0.7647   0.6718
   0.750   0.8495   0.01280   0.00647  -0.1771   0.7577   0.6865
   1.000   0.8748   0.01287   0.00660  -0.1764   0.7484   0.7015
   1.250   0.9036   0.01288   0.00659  -0.1763   0.7412   0.7176
   1.500   0.9286   0.01295   0.00672  -0.1755   0.7313   0.7337
   1.750   0.9566   0.01298   0.00673  -0.1752   0.7234   0.7502
   2.000   0.9816   0.01301   0.00681  -0.1743   0.7128   0.7661
   2.250   1.0072   0.01302   0.00685  -0.1735   0.7017   0.7816
   2.500   1.0336   0.01300   0.00680  -0.1728   0.6910   0.7971
   2.750   1.0580   0.01301   0.00685  -0.1719   0.6790   0.8128
   3.000   1.0823   0.01304   0.00694  -0.1709   0.6677   0.8290
   3.250   1.1070   0.01307   0.00698  -0.1700   0.6571   0.8465
   3.500   1.1293   0.01307   0.00701  -0.1685   0.6456   0.8656
   3.750   1.1496   0.01308   0.00710  -0.1667   0.6334   0.8895
   4.000   1.1673   0.01300   0.00708  -0.1643   0.6218   0.9298
   4.250   1.1953   0.01307   0.00712  -0.1643   0.6092   1.0000
   4.500   1.2256   0.01327   0.00726  -0.1649   0.5957   1.0000
   4.750   1.2536   0.01348   0.00745  -0.1650   0.5801   1.0000
   5.000   1.2803   0.01370   0.00762  -0.1648   0.5630   1.0000
   5.250   1.3056   0.01394   0.00783  -0.1644   0.5444   1.0000
   5.500   1.3303   0.01421   0.00808  -0.1638   0.5253   1.0000
   5.750   1.3546   0.01452   0.00835  -0.1631   0.5070   1.0000
   6.000   1.3786   0.01488   0.00866  -0.1624   0.4896   1.0000
   6.250   1.4020   0.01527   0.00902  -0.1616   0.4720   1.0000
   6.500   1.4240   0.01573   0.00940  -0.1606   0.4526   1.0000
   6.750   1.4448   0.01619   0.00983  -0.1593   0.4303   1.0000
   7.000   1.4644   0.01673   0.01029  -0.1579   0.4074   1.0000
   7.250   1.4833   0.01729   0.01081  -0.1564   0.3837   1.0000
   7.500   1.5011   0.01789   0.01136  -0.1548   0.3596   1.0000
   7.750   1.5178   0.01855   0.01196  -0.1530   0.3341   1.0000
   8.000   1.5322   0.01932   0.01264  -0.1508   0.3079   1.0000
   8.250   1.5449   0.02017   0.01341  -0.1485   0.2813   1.0000
   8.500   1.5547   0.02111   0.01425  -0.1456   0.2560   1.0000
   8.750   1.5609   0.02221   0.01523  -0.1424   0.2324   1.0000
   9.000   1.5677   0.02336   0.01630  -0.1393   0.2083   1.0000
   9.250   1.5719   0.02472   0.01755  -0.1360   0.1857   1.0000
   9.500   1.5764   0.02616   0.01892  -0.1330   0.1632   1.0000
   9.750   1.5786   0.02783   0.02048  -0.1299   0.1449   1.0000
  10.000   1.5808   0.02961   0.02219  -0.1271   0.1299   1.0000
  10.250   1.5833   0.03147   0.02402  -0.1245   0.1175   1.0000
  10.500   1.5872   0.03334   0.02590  -0.1223   0.1072   1.0000
  10.750   1.5893   0.03545   0.02803  -0.1200   0.0991   1.0000
  11.000   1.5899   0.03779   0.03035  -0.1179   0.0924   1.0000
  11.250   1.5939   0.03994   0.03259  -0.1162   0.0863   1.0000
  11.500   1.5965   0.04228   0.03495  -0.1146   0.0813   1.0000
  11.750   1.5985   0.04481   0.03751  -0.1130   0.0770   1.0000
  12.000   1.6043   0.04696   0.03979  -0.1118   0.0729   1.0000
  12.250   1.6071   0.04947   0.04232  -0.1106   0.0694   1.0000
  12.500   1.6109   0.05207   0.04497  -0.1093   0.0661   1.0000
  12.750   1.6163   0.05440   0.04746  -0.1084   0.0630   1.0000
  13.000   1.6204   0.05692   0.05006  -0.1077   0.0602   1.0000
  13.250   1.6244   0.05968   0.05275  -0.1066   0.0572   1.0000
  13.500   1.6282   0.06236   0.05565  -0.1061   0.0550   1.0000
  13.750   1.6315   0.06516   0.05859  -0.1056   0.0525   1.0000
  14.000   1.6341   0.06806   0.06156  -0.1053   0.0503   1.0000
  14.250   1.6396   0.07087   0.06433  -0.1045   0.0477   1.0000
  14.500   1.6398   0.07423   0.06795  -0.1045   0.0460   1.0000
  14.750   1.6409   0.07757   0.07145  -0.1045   0.0441   1.0000
  15.000   1.6424   0.08085   0.07482  -0.1046   0.0424   1.0000
  15.250   1.6468   0.08381   0.07774  -0.1044   0.0405   1.0000
  15.500   1.6459   0.08766   0.08180  -0.1045   0.0390   1.0000
  15.750   1.6431   0.09181   0.08617  -0.1052   0.0376   1.0000
  16.000   1.6412   0.09583   0.09036  -0.1060   0.0363   1.0000
  16.250   1.6411   0.09960   0.09423  -0.1068   0.0351   1.0000
  16.500   1.6450   0.10270   0.09734  -0.1072   0.0339   1.0000
  16.750   1.6441   0.10683   0.10163  -0.1077   0.0329   1.0000
  17.000   1.6344   0.11238   0.10746  -0.1099   0.0322   1.0000
  17.250   1.6260   0.11790   0.11323  -0.1121   0.0316   1.0000
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