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FX 73-K-170/22 (fx73k170-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: FX 73-K-170/22 (fx73k170-il)
Reynolds number: 500,000
Max Cl/Cd: 112.89 at α=7.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx73k170-il-500000.txt
Download as CSV file: xf-fx73k170-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 73-K-170/22                                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.0315   0.04051   0.03719  -0.1563   0.7989   0.0290
 -10.250  -0.0605   0.03483   0.03144  -0.1592   0.7969   0.0289
 -10.000  -0.0850   0.03076   0.02728  -0.1605   0.7943   0.0289
  -9.750  -0.1057   0.02763   0.02405  -0.1607   0.7915   0.0289
  -9.500  -0.1300   0.02552   0.02177  -0.1595   0.7886   0.0296
  -9.250  -0.1538   0.02570   0.02173  -0.1552   0.7858   0.0304
  -9.000  -0.2459   0.02583   0.02015  -0.1544   0.7870   0.0155
  -8.750  -0.2272   0.02537   0.01951  -0.1534   0.7851   0.0153
  -8.500  -0.2098   0.02373   0.01770  -0.1525   0.7831   0.0151
  -8.250  -0.1949   0.02226   0.01605  -0.1509   0.7809   0.0153
  -8.000  -0.1768   0.02044   0.01409  -0.1498   0.7785   0.0154
  -7.750  -0.1565   0.01941   0.01297  -0.1489   0.7761   0.0155
  -7.500  -0.1370   0.01827   0.01181  -0.1480   0.7738   0.0162
  -7.250  -0.1159   0.01753   0.01099  -0.1472   0.7718   0.0165
  -7.000  -0.0937   0.01696   0.01036  -0.1466   0.7699   0.0170
  -6.750  -0.0720   0.01646   0.00980  -0.1460   0.7680   0.0177
  -6.500  -0.0522   0.01603   0.00936  -0.1449   0.7656   0.0186
  -6.250  -0.0316   0.01559   0.00888  -0.1439   0.7630   0.0192
  -6.000  -0.0145   0.01476   0.00801  -0.1424   0.7604   0.0203
  -5.750   0.0074   0.01426   0.00748  -0.1418   0.7581   0.0215
  -5.500   0.0313   0.01384   0.00700  -0.1414   0.7561   0.0228
  -5.250   0.0550   0.01336   0.00646  -0.1410   0.7542   0.0263
  -5.000   0.0791   0.01308   0.00614  -0.1406   0.7522   0.0306
  -4.750   0.0990   0.01256   0.00572  -0.1395   0.7495   0.0486
  -4.500   0.1194   0.01198   0.00538  -0.1386   0.7468   0.0998
  -4.250   0.1393   0.01125   0.00502  -0.1378   0.7442   0.1946
  -4.000   0.1589   0.01046   0.00466  -0.1370   0.7420   0.3211
  -3.750   0.1785   0.00977   0.00443  -0.1360   0.7401   0.4599
  -3.500   0.2040   0.00967   0.00449  -0.1357   0.7382   0.5328
  -3.250   0.2283   0.00976   0.00462  -0.1350   0.7357   0.5648
  -3.000   0.2536   0.00984   0.00467  -0.1345   0.7329   0.5808
  -2.750   0.2803   0.00990   0.00471  -0.1343   0.7303   0.5920
  -2.500   0.3080   0.00998   0.00472  -0.1342   0.7280   0.6034
  -2.250   0.3363   0.01010   0.00477  -0.1343   0.7261   0.6152
  -2.000   0.3655   0.01021   0.00486  -0.1345   0.7242   0.6244
  -1.750   0.3923   0.01032   0.00490  -0.1344   0.7218   0.6317
  -1.500   0.4169   0.01033   0.00496  -0.1338   0.7188   0.6364
  -1.250   0.4434   0.01037   0.00499  -0.1336   0.7160   0.6416
  -1.000   0.4709   0.01039   0.00493  -0.1337   0.7135   0.6466
  -0.750   0.4994   0.01036   0.00488  -0.1339   0.7114   0.6505
  -0.500   0.5288   0.01037   0.00485  -0.1344   0.7095   0.6540
  -0.250   0.5558   0.01042   0.00487  -0.1344   0.7071   0.6577
   0.000   0.5797   0.01045   0.00491  -0.1337   0.7040   0.6616
   0.250   0.6057   0.01045   0.00489  -0.1336   0.7012   0.6646
   0.500   0.6332   0.01041   0.00485  -0.1336   0.6986   0.6674
   0.750   0.6619   0.01039   0.00481  -0.1340   0.6963   0.6702
   1.000   0.6913   0.01040   0.00478  -0.1345   0.6943   0.6733
   1.250   0.7157   0.01045   0.00484  -0.1340   0.6914   0.6764
   1.500   0.7399   0.01049   0.00488  -0.1335   0.6882   0.6792
   1.750   0.7661   0.01045   0.00486  -0.1333   0.6851   0.6815
   2.000   0.7941   0.01042   0.00483  -0.1335   0.6824   0.6839
   2.250   0.8232   0.01041   0.00480  -0.1340   0.6800   0.6864
   2.500   0.8479   0.01047   0.00489  -0.1336   0.6770   0.6893
   2.750   0.8711   0.01051   0.00496  -0.1328   0.6734   0.6919
   3.000   0.8970   0.01052   0.00496  -0.1327   0.6700   0.6945
   3.250   0.9247   0.01049   0.00494  -0.1328   0.6671   0.6970
   3.500   0.9546   0.01052   0.00495  -0.1335   0.6643   0.6994
   3.750   0.9745   0.01057   0.00510  -0.1321   0.6604   0.7018
   4.000   0.9983   0.01060   0.00516  -0.1315   0.6566   0.7045
   4.250   1.0248   0.01062   0.00518  -0.1314   0.6531   0.7074
   4.500   1.0547   0.01068   0.00521  -0.1321   0.6498   0.7103
   4.750   1.0732   0.01073   0.00535  -0.1305   0.6455   0.7128
   5.000   1.0959   0.01075   0.00543  -0.1296   0.6410   0.7154
   5.250   1.1220   0.01079   0.00549  -0.1295   0.6373   0.7183
   5.500   1.1471   0.01087   0.00559  -0.1292   0.6331   0.7213
   5.750   1.1646   0.01093   0.00573  -0.1273   0.6276   0.7248
   6.000   1.1882   0.01096   0.00576  -0.1267   0.6225   0.7277
   6.250   1.2091   0.01102   0.00589  -0.1255   0.6169   0.7306
   6.500   1.2252   0.01108   0.00602  -0.1233   0.6105   0.7338
   6.750   1.2505   0.01115   0.00608  -0.1231   0.6047   0.7375
   7.000   1.2568   0.01124   0.00626  -0.1189   0.5973   0.7415
   7.250   1.2756   0.01130   0.00632  -0.1173   0.5896   0.7453
   7.500   1.2850   0.01148   0.00662  -0.1139   0.5821   0.7493
   7.750   1.2948   0.01169   0.00684  -0.1107   0.5705   0.7540
   8.000   1.3043   0.01199   0.00715  -0.1075   0.5573   0.7587
   8.250   1.3164   0.01235   0.00756  -0.1052   0.5442   0.7638
   8.500   1.3276   0.01285   0.00809  -0.1029   0.5297   0.7702
   8.750   1.3398   0.01349   0.00877  -0.1012   0.5130   0.7766
   9.000   1.3532   0.01426   0.00957  -0.0999   0.4951   0.7840
   9.250   1.3658   0.01523   0.01053  -0.0988   0.4751   0.7924
   9.500   1.3771   0.01643   0.01172  -0.0979   0.4527   0.8034
   9.750   1.3853   0.01807   0.01332  -0.0970   0.4217   0.8176
  10.000   1.3905   0.02023   0.01540  -0.0964   0.3831   0.8393
  10.250   1.4110   0.02271   0.01786  -0.0996   0.3411   0.8921
  10.500   1.4168   0.02568   0.02064  -0.0999   0.2964   1.0000
  10.750   1.4131   0.02785   0.02267  -0.0973   0.2680   1.0000
  11.000   1.4072   0.03027   0.02491  -0.0946   0.2359   1.0000
  11.250   1.3981   0.03301   0.02743  -0.0917   0.2006   1.0000
  11.500   1.3938   0.03550   0.02974  -0.0895   0.1703   1.0000
  11.750   1.3923   0.03783   0.03195  -0.0875   0.1453   1.0000
  12.000   1.3871   0.04053   0.03446  -0.0854   0.1166   1.0000
  12.250   1.3860   0.04295   0.03675  -0.0837   0.0933   1.0000
  12.500   1.3858   0.04537   0.03908  -0.0822   0.0762   1.0000
  12.750   1.3858   0.04782   0.04145  -0.0807   0.0600   1.0000
  13.000   1.3876   0.05016   0.04373  -0.0795   0.0492   1.0000
  13.250   1.3894   0.05254   0.04607  -0.0783   0.0405   1.0000
  13.500   1.3914   0.05494   0.04848  -0.0772   0.0358   1.0000
  13.750   1.3976   0.05699   0.05059  -0.0765   0.0322   1.0000
  14.000   1.4002   0.05943   0.05304  -0.0756   0.0291   1.0000
  14.250   1.4051   0.06168   0.05535  -0.0749   0.0265   1.0000
  14.500   1.4092   0.06399   0.05771  -0.0742   0.0244   1.0000
  14.750   1.4068   0.06709   0.06084  -0.0733   0.0221   1.0000
  15.000   1.4131   0.06925   0.06309  -0.0728   0.0202   1.0000
  15.250   1.4157   0.07187   0.06577  -0.0723   0.0190   1.0000
  15.500   1.4105   0.07544   0.06938  -0.0716   0.0170   1.0000
  15.750   1.4144   0.07796   0.07200  -0.0712   0.0160   1.0000
  16.000   1.4168   0.08070   0.07481  -0.0709   0.0148   1.0000
  16.250   1.4146   0.08401   0.07816  -0.0706   0.0137   1.0000
  16.500   1.4099   0.08772   0.08197  -0.0704   0.0131   1.0000
  16.750   1.4111   0.09074   0.08509  -0.0703   0.0124   1.0000
  17.000   1.4123   0.09376   0.08820  -0.0703   0.0118   1.0000
  17.250   1.4112   0.09712   0.09163  -0.0704   0.0112   1.0000
  17.500   1.4087   0.10068   0.09525  -0.0706   0.0107   1.0000
  17.750   1.4041   0.10457   0.09921  -0.0709   0.0104   1.0000
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