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FX 62-K-153/20 AIRFOIL (fx62k153-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: FX 62-K-153/20 AIRFOIL (fx62k153-il)
Reynolds number: 50,000
Max Cl/Cd: 23 at α=10.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx62k153-il-50000-n5.txt
Download as CSV file: xf-fx62k153-il-50000-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 =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.750  -0.3725   0.15084   0.14436  -0.0428   0.9985   0.1012
 -11.500  -0.3810   0.14809   0.14168  -0.0486   0.9948   0.1047
 -11.250  -0.3854   0.14470   0.13834  -0.0529   0.9909   0.1052
 -11.000  -0.3598   0.13921   0.13278  -0.0516   0.9891   0.1075
 -10.750  -0.3564   0.13018   0.12369  -0.0582   0.9858   0.0612
 -10.500  -0.3444   0.12626   0.11972  -0.0584   0.9828   0.0571
 -10.250  -0.3627   0.11807   0.11164  -0.0672   0.9775   0.0494
 -10.000  -0.3494   0.11466   0.10821  -0.0672   0.9752   0.0484
  -9.750  -0.3452   0.11076   0.10429  -0.0687   0.9719   0.0475
  -9.500  -0.3453   0.10670   0.10026  -0.0704   0.9678   0.0467
  -9.250  -0.3453   0.10200   0.09558  -0.0733   0.9640   0.0459
  -9.000  -0.3470   0.09665   0.09025  -0.0772   0.9605   0.0452
  -8.750  -0.3587   0.09209   0.08573  -0.0791   0.9549   0.0445
  -8.500  -0.3715   0.08716   0.08083  -0.0821   0.9500   0.0437
  -8.250  -0.3917   0.08329   0.07695  -0.0832   0.9441   0.0431
  -8.000  -0.4103   0.07924   0.07282  -0.0847   0.9377   0.0424
  -7.750  -0.4178   0.07423   0.06762  -0.0884   0.9330   0.0420
  -7.500  -0.4310   0.07099   0.06421  -0.0875   0.9265   0.0419
  -7.250  -0.4297   0.06702   0.05996  -0.0891   0.9221   0.0423
  -7.000  -0.4185   0.06291   0.05548  -0.0918   0.9189   0.0436
  -6.750  -0.4164   0.05995   0.05216  -0.0912   0.9138   0.0445
  -6.500  -0.4018   0.05638   0.04812  -0.0925   0.9100   0.0456
  -6.250  -0.3784   0.05271   0.04389  -0.0946   0.9072   0.0463
  -6.000  -0.3488   0.04935   0.03990  -0.0969   0.9050   0.0474
  -5.750  -0.3265   0.04709   0.03706  -0.0972   0.9016   0.0497
  -5.500  -0.3058   0.04524   0.03513  -0.0973   0.8982   0.0528
  -5.250  -0.2793   0.04358   0.03319  -0.0976   0.8954   0.0555
  -5.000  -0.2509   0.04210   0.03137  -0.0975   0.8929   0.0583
  -4.750  -0.2219   0.04100   0.03000  -0.0972   0.8908   0.0635
  -4.500  -0.2038   0.04028   0.02930  -0.0955   0.8873   0.0684
  -4.250  -0.1863   0.03972   0.02859  -0.0932   0.8833   0.0730
  -4.000  -0.1631   0.03904   0.02788  -0.0925   0.8801   0.0813
  -3.750  -0.1340   0.03828   0.02703  -0.0932   0.8773   0.0937
  -3.500  -0.1004   0.03732   0.02609  -0.0955   0.8749   0.1191
  -3.250  -0.0711   0.03564   0.02513  -0.0988   0.8711   0.1990
  -2.750  -0.0518   0.03718   0.02854  -0.0879   0.8626   0.6667
  -2.500  -0.0482   0.03851   0.02976  -0.0811   0.8578   0.7099
  -2.250  -0.0500   0.03955   0.03072  -0.0733   0.8521   0.7495
  -2.000  -0.0480   0.04009   0.03116  -0.0657   0.8480   0.7815
  -1.750  -0.0376   0.04026   0.03116  -0.0618   0.8435   0.8003
  -1.500  -0.0174   0.04035   0.03100  -0.0616   0.8381   0.8088
  -1.250   0.0083   0.04036   0.03076  -0.0617   0.8342   0.8153
  -1.000   0.0444   0.04047   0.03058  -0.0643   0.8313   0.8221
  -0.750   0.0549   0.04061   0.03060  -0.0622   0.8244   0.8276
  -0.500   0.0841   0.04076   0.03056  -0.0635   0.8201   0.8333
  -0.250   0.1187   0.04089   0.03047  -0.0656   0.8168   0.8384
   0.000   0.1320   0.04117   0.03066  -0.0642   0.8098   0.8436
   0.250   0.1622   0.04141   0.03074  -0.0658   0.8052   0.8486
   0.500   0.1972   0.04157   0.03075  -0.0678   0.8019   0.8529
   0.750   0.2098   0.04197   0.03110  -0.0665   0.7942   0.8576
   1.000   0.2410   0.04223   0.03125  -0.0681   0.7896   0.8620
   1.250   0.2710   0.04257   0.03150  -0.0696   0.7850   0.8661
   1.500   0.2882   0.04295   0.03185  -0.0689   0.7776   0.8704
   1.750   0.3212   0.04319   0.03201  -0.0705   0.7735   0.8745
   2.000   0.3410   0.04377   0.03256  -0.0707   0.7660   0.8789
   2.250   0.3684   0.04404   0.03281  -0.0714   0.7605   0.8829
   2.500   0.3948   0.04438   0.03314  -0.0721   0.7550   0.8870
   2.750   0.4164   0.04492   0.03368  -0.0724   0.7474   0.8914
   3.000   0.4513   0.04511   0.03387  -0.0741   0.7434   0.8954
   3.250   0.4634   0.04580   0.03460  -0.0730   0.7341   0.8998
   3.500   0.4962   0.04604   0.03486  -0.0745   0.7297   0.9041
   3.750   0.5124   0.04684   0.03573  -0.0742   0.7207   0.9087
   4.000   0.5417   0.04706   0.03599  -0.0750   0.7158   0.9132
   4.250   0.5576   0.04785   0.03685  -0.0746   0.7070   0.9181
   4.500   0.5882   0.04818   0.03725  -0.0758   0.7017   0.9228
   4.750   0.6033   0.04894   0.03812  -0.0752   0.6927   0.9282
   5.000   0.6340   0.04916   0.03842  -0.0763   0.6872   0.9337
   5.250   0.6492   0.04993   0.03930  -0.0757   0.6772   0.9397
   5.500   0.6834   0.04984   0.03934  -0.0769   0.6719   0.9462
   5.750   0.6979   0.05060   0.04023  -0.0762   0.6607   0.9537
   6.250   0.7491   0.05108   0.04098  -0.0771   0.6442   0.9774
   6.500   0.7666   0.05183   0.04191  -0.0770   0.6325   0.9999
   7.000   0.8279   0.05239   0.04279  -0.0794   0.6153   0.9999
   7.250   0.8487   0.05322   0.04382  -0.0797   0.6033   0.9999
   7.500   0.8738   0.05376   0.04453  -0.0803   0.5925   0.9999
   7.750   0.9112   0.05333   0.04432  -0.0816   0.5854   0.9999
   8.250   0.9531   0.05483   0.04626  -0.0819   0.5604   0.9999
   8.500   0.9802   0.05476   0.04643  -0.0820   0.5481   0.9999
   9.000   1.0394   0.05327   0.04544  -0.0815   0.5202   0.9999
   9.250   1.0658   0.05269   0.04509  -0.0809   0.5031   0.9999
   9.500   1.0951   0.05172   0.04434  -0.0803   0.4846   0.9999
   9.750   1.1205   0.05115   0.04397  -0.0795   0.4625   0.9999
  10.000   1.1468   0.05043   0.04341  -0.0785   0.4358   0.9999
  10.250   1.1647   0.05071   0.04378  -0.0773   0.4038   0.9999
  10.500   1.1799   0.05131   0.04437  -0.0760   0.3675   0.9999
  10.750   1.1905   0.05244   0.04540  -0.0745   0.3284   0.9999
  11.000   1.1971   0.05402   0.04675  -0.0729   0.2899   0.9999
  11.250   1.1986   0.05640   0.04896  -0.0715   0.2554   0.9999
  11.500   1.1981   0.05912   0.05153  -0.0703   0.2247   0.9999
  11.750   1.1970   0.06204   0.05433  -0.0692   0.1985   0.9999
  12.000   1.1968   0.06502   0.05724  -0.0684   0.1761   0.9999
  12.250   1.1966   0.06804   0.06013  -0.0677   0.1583   0.9999
  12.500   1.1977   0.07101   0.06305  -0.0670   0.1424   0.9999
  12.750   1.2003   0.07386   0.06588  -0.0665   0.1291   0.9999
  13.000   1.2036   0.07662   0.06862  -0.0660   0.1180   0.9999
  13.250   1.2103   0.07913   0.07127  -0.0654   0.1076   0.9999
  13.500   1.2171   0.08163   0.07386  -0.0648   0.0988   0.9999
  13.750   1.2232   0.08406   0.07624  -0.0644   0.0913   0.9999
  14.000   1.2332   0.08642   0.07891  -0.0638   0.0841   0.9999
  14.250   1.2446   0.08831   0.08077  -0.0631   0.0781   0.9999
  14.500   1.2487   0.09155   0.08442  -0.0630   0.0724   0.9999
  14.750   1.2560   0.09407   0.08700  -0.0628   0.0676   0.9999
  15.000   1.2630   0.09711   0.09030  -0.0624   0.0636   0.9999
  15.250   1.2595   0.10143   0.09496  -0.0629   0.0600   0.9999
  15.500   1.2581   0.10519   0.09885  -0.0637   0.0566   0.9999
  15.750   1.2592   0.10881   0.10254  -0.0642   0.0535   0.9999
  16.000   1.2453   0.11510   0.10925  -0.0664   0.0518   0.9999
  16.250   1.2304   0.12178   0.11625  -0.0693   0.0503   0.9999
  16.500   1.2140   0.12904   0.12380  -0.0731   0.0490   0.9999
  16.750   1.1962   0.13710   0.13211  -0.0778   0.0484   0.9999
  17.000   1.1729   0.14729   0.14254  -0.0842   0.0491   0.9999
  17.250   1.1447   0.16008   0.15553  -0.0927   0.0507   0.9999
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