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FX 60-100 (126) AIRFOIL (fx601001-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: FX 60-100 (126) AIRFOIL (fx601001-il)
Reynolds number: 500,000
Max Cl/Cd: 103 at α=4.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx601001-il-500000.txt
Download as CSV file: xf-fx601001-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 60-100 (126) AIRFOIL                         
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.3076   0.08919   0.08705  -0.0403   1.0000   0.0242
  -9.750  -0.3100   0.08466   0.08255  -0.0414   1.0000   0.0243
  -7.250  -0.3931   0.02018   0.01558  -0.0992   0.9831   0.0137
  -7.000  -0.3620   0.01813   0.01327  -0.1009   0.9791   0.0140
  -6.750  -0.3279   0.01662   0.01158  -0.1028   0.9760   0.0146
  -6.500  -0.2924   0.01535   0.01015  -0.1049   0.9738   0.0152
  -6.250  -0.2557   0.01422   0.00887  -0.1070   0.9720   0.0160
  -6.000  -0.2179   0.01349   0.00805  -0.1093   0.9706   0.0173
  -5.750  -0.1823   0.01236   0.00679  -0.1113   0.9679   0.0183
  -5.500  -0.1502   0.01138   0.00573  -0.1125   0.9627   0.0201
  -5.250  -0.1153   0.01080   0.00508  -0.1141   0.9591   0.0225
  -5.000  -0.0798   0.01015   0.00437  -0.1157   0.9560   0.0275
  -4.750  -0.0500   0.00971   0.00399  -0.1161   0.9494   0.0452
  -4.500  -0.0187   0.00938   0.00369  -0.1168   0.9437   0.0615
  -4.250   0.0111   0.00917   0.00342  -0.1171   0.9373   0.0697
  -4.000   0.0400   0.00885   0.00310  -0.1173   0.9295   0.0820
  -3.750   0.0689   0.00845   0.00279  -0.1175   0.9218   0.1078
  -3.500   0.0979   0.00759   0.00241  -0.1184   0.9138   0.2470
  -3.250   0.1261   0.00701   0.00222  -0.1187   0.9048   0.3677
  -3.000   0.1544   0.00693   0.00223  -0.1186   0.8961   0.4263
  -2.750   0.1823   0.00698   0.00223  -0.1183   0.8858   0.4503
  -2.500   0.2103   0.00706   0.00222  -0.1180   0.8756   0.4669
  -2.250   0.2383   0.00714   0.00222  -0.1177   0.8655   0.4786
  -2.000   0.2662   0.00721   0.00221  -0.1174   0.8549   0.4879
  -1.750   0.2941   0.00730   0.00220  -0.1172   0.8432   0.4971
  -1.500   0.3216   0.00733   0.00220  -0.1169   0.8309   0.5045
  -1.250   0.3491   0.00740   0.00219  -0.1165   0.8168   0.5131
  -1.000   0.3763   0.00747   0.00220  -0.1161   0.8012   0.5217
  -0.750   0.4036   0.00751   0.00218  -0.1158   0.7856   0.5287
  -0.500   0.4312   0.00754   0.00215  -0.1155   0.7710   0.5327
  -0.250   0.4589   0.00758   0.00212  -0.1153   0.7566   0.5364
   0.000   0.4865   0.00763   0.00209  -0.1151   0.7408   0.5404
   0.250   0.5137   0.00766   0.00207  -0.1148   0.7236   0.5444
   0.500   0.5411   0.00771   0.00207  -0.1146   0.7049   0.5481
   0.750   0.5684   0.00780   0.00207  -0.1143   0.6858   0.5519
   1.000   0.5956   0.00787   0.00208  -0.1141   0.6687   0.5557
   1.250   0.6230   0.00794   0.00212  -0.1139   0.6542   0.5595
   1.500   0.6506   0.00802   0.00217  -0.1138   0.6409   0.5630
   1.750   0.6782   0.00811   0.00223  -0.1137   0.6280   0.5660
   2.000   0.7057   0.00821   0.00229  -0.1135   0.6148   0.5688
   2.250   0.7331   0.00828   0.00236  -0.1134   0.6021   0.5714
   2.500   0.7605   0.00837   0.00244  -0.1132   0.5901   0.5741
   2.750   0.7879   0.00848   0.00255  -0.1131   0.5783   0.5771
   3.000   0.8152   0.00860   0.00266  -0.1129   0.5660   0.5805
   3.250   0.8426   0.00870   0.00277  -0.1128   0.5532   0.5836
   3.500   0.8698   0.00879   0.00290  -0.1126   0.5396   0.5868
   3.750   0.8968   0.00892   0.00305  -0.1124   0.5244   0.5903
   4.000   0.9234   0.00907   0.00319  -0.1121   0.5034   0.5943
   4.250   0.9496   0.00926   0.00334  -0.1118   0.4771   0.5987
   4.500   0.9754   0.00947   0.00353  -0.1114   0.4426   0.6034
   4.750   0.9989   0.00996   0.00378  -0.1107   0.3866   0.6087
   5.000   1.0215   0.01058   0.00415  -0.1100   0.3311   0.6144
   5.250   1.0452   0.01112   0.00453  -0.1094   0.2892   0.6218
   5.500   1.0695   0.01157   0.00490  -0.1089   0.2549   0.6314
   5.750   1.0936   0.01202   0.00528  -0.1084   0.2236   0.6450
   6.000   1.1176   0.01249   0.00569  -0.1079   0.1948   0.6657
   6.250   1.1413   0.01294   0.00614  -0.1074   0.1677   0.7005
   6.500   1.1638   0.01340   0.00663  -0.1067   0.1348   0.7660
   6.750   1.1750   0.01427   0.00737  -0.1038   0.0634   1.0000
   7.000   1.1919   0.01572   0.00851  -0.1023   0.0230   1.0000
   7.250   1.2145   0.01642   0.00926  -0.1014   0.0193   1.0000
   7.500   1.2358   0.01723   0.01010  -0.1004   0.0167   1.0000
   7.750   1.2546   0.01831   0.01128  -0.0990   0.0151   1.0000
   8.000   1.2752   0.01909   0.01215  -0.0978   0.0144   1.0000
   8.250   1.2943   0.01999   0.01316  -0.0965   0.0136   1.0000
   8.500   1.3120   0.02099   0.01424  -0.0950   0.0130   1.0000
   8.750   1.3282   0.02207   0.01540  -0.0934   0.0124   1.0000
   9.000   1.3423   0.02331   0.01670  -0.0915   0.0118   1.0000
   9.250   1.3505   0.02512   0.01861  -0.0888   0.0111   1.0000
   9.500   1.3571   0.02721   0.02083  -0.0860   0.0106   1.0000
   9.750   1.3700   0.02820   0.02193  -0.0839   0.0104   1.0000
  10.000   1.3800   0.02957   0.02341  -0.0815   0.0102   1.0000
  10.250   1.3892   0.03107   0.02505  -0.0792   0.0099   1.0000
  10.500   1.3978   0.03274   0.02685  -0.0769   0.0097   1.0000
  10.750   1.4058   0.03456   0.02881  -0.0747   0.0095   1.0000
  11.000   1.4127   0.03653   0.03093  -0.0726   0.0093   1.0000
  11.250   1.4183   0.03869   0.03325  -0.0706   0.0091   1.0000
  11.500   1.4221   0.04107   0.03580  -0.0686   0.0090   1.0000
  11.750   1.4238   0.04369   0.03861  -0.0668   0.0089   1.0000
  12.000   1.4228   0.04668   0.04181  -0.0650   0.0088   1.0000
  12.250   1.4189   0.05002   0.04537  -0.0635   0.0088   1.0000
  12.500   1.4105   0.05405   0.04967  -0.0623   0.0088   1.0000
  12.750   1.3984   0.05866   0.05454  -0.0616   0.0089   1.0000
  13.000   1.3827   0.06393   0.06008  -0.0616   0.0090   1.0000
  13.250   1.3642   0.06990   0.06632  -0.0624   0.0092   1.0000
  13.500   1.3450   0.07631   0.07296  -0.0642   0.0094   1.0000
  13.750   1.3247   0.08328   0.08015  -0.0669   0.0095   1.0000
  14.000   1.3045   0.09068   0.08776  -0.0704   0.0096   1.0000
  14.250   1.2831   0.09889   0.09616  -0.0748   0.0098   1.0000
  14.500   1.2629   0.10748   0.10492  -0.0800   0.0099   1.0000
  14.750   1.2415   0.11708   0.11469  -0.0861   0.0100   1.0000
  15.000   1.2206   0.12737   0.12515  -0.0930   0.0101   1.0000
  15.250   1.1993   0.13853   0.13645  -0.1007   0.0102   1.0000
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