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FX 74-130 WP1 (fx74130wp1-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: FX 74-130 WP1 (fx74130wp1-il)
Reynolds number: 100,000
Max Cl/Cd: 39.65 at α=9°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx74130wp1-il-100000.txt
Download as CSV file: xf-fx74130wp1-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 74-130 WP1                                   
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.4279   0.12063   0.11643  -0.0457   0.9867   0.0748
  -8.750  -0.4411   0.11811   0.11396  -0.0494   0.9847   0.0753
  -8.500  -0.4610   0.11603   0.11195  -0.0500   0.9831   0.0754
  -8.250  -0.4334   0.11030   0.10619  -0.0460   0.9821   0.0779
  -8.000  -0.4308   0.10782   0.10372  -0.0442   0.9811   0.0802
  -7.750  -0.4376   0.10545   0.10139  -0.0433   0.9798   0.0820
  -7.500  -0.4496   0.10303   0.09902  -0.0428   0.9785   0.0838
  -7.250  -0.4709   0.10118   0.09723  -0.0406   0.9791   0.0842
  -7.000  -0.4978   0.09944   0.09556  -0.0378   0.9812   0.0844
  -6.750  -0.5714   0.10076   0.09706  -0.0225   1.0000   0.0796
  -6.500  -0.5780   0.09772   0.09402  -0.0221   1.0000   0.0812
  -6.250  -0.5852   0.09432   0.09060  -0.0224   1.0000   0.0834
  -6.000  -0.5914   0.09056   0.08678  -0.0238   1.0000   0.0860
  -5.750  -0.6014   0.08758   0.08314  -0.0308   1.0000   0.0898
  -5.500  -0.5954   0.08153   0.07747  -0.0277   1.0000   0.0919
  -5.250  -0.5895   0.07881   0.07479  -0.0259   1.0000   0.0951
  -5.000  -0.5810   0.07489   0.07035  -0.0303   1.0000   0.1050
  -4.750  -0.5746   0.07148   0.06717  -0.0276   1.0000   0.1088
  -4.500  -0.5607   0.06801   0.06332  -0.0301   1.0000   0.1202
  -4.250  -0.5510   0.06522   0.06066  -0.0284   1.0000   0.1274
  -4.000  -0.5365   0.06194   0.05721  -0.0294   1.0000   0.1385
  -3.750  -0.5206   0.05902   0.05414  -0.0301   1.0000   0.1527
  -3.500  -0.5045   0.05645   0.05146  -0.0303   1.0000   0.1690
  -3.250  -0.4870   0.05395   0.04880  -0.0310   1.0000   0.1951
  -2.500  -0.3747   0.04236   0.03472  -0.0349   1.0000   0.0885
  -2.250  -0.3459   0.03910   0.03102  -0.0346   1.0000   0.0708
  -2.000  -0.3172   0.03812   0.02928  -0.0336   1.0000   0.0619
  -1.750  -0.2926   0.03672   0.02759  -0.0333   1.0000   0.0616
  -1.500  -0.2674   0.03501   0.02572  -0.0334   1.0000   0.0636
  -1.250  -0.2411   0.03419   0.02478  -0.0334   0.9995   0.0648
  -1.000  -0.2100   0.03374   0.02423  -0.0341   0.9976   0.0668
  -0.750  -0.1779   0.03374   0.02419  -0.0351   0.9955   0.0718
  -0.500  -0.1491   0.03359   0.02412  -0.0359   0.9936   0.0827
  -0.250  -0.1172   0.03357   0.02410  -0.0372   0.9900   0.1018
   0.000  -0.1153   0.03179   0.02551  -0.0302   0.9924   0.8369
   0.250  -0.1089   0.03191   0.02564  -0.0225   0.9831   1.0000
   0.500  -0.0761   0.03286   0.02625  -0.0247   0.9751   1.0000
   0.750  -0.0491   0.03364   0.02679  -0.0260   0.9680   1.0000
   1.000  -0.0139   0.03490   0.02782  -0.0287   0.9608   1.0000
   1.250   0.0103   0.03548   0.02822  -0.0295   0.9518   1.0000
   1.500   0.0480   0.03708   0.02964  -0.0327   0.9458   1.0000
   1.750   0.0700   0.03746   0.02991  -0.0330   0.9352   1.0000
   2.000   0.1118   0.03962   0.03190  -0.0370   0.9304   1.0000
   2.250   0.1318   0.03969   0.03190  -0.0369   0.9185   1.0000
   2.500   0.1550   0.04039   0.03254  -0.0374   0.9081   1.0000
   2.750   0.1983   0.04247   0.03451  -0.0415   0.9021   1.0000
   3.000   0.2189   0.04277   0.03478  -0.0415   0.8898   1.0000
   3.250   0.2428   0.04351   0.03548  -0.0421   0.8778   1.0000
   3.500   0.2702   0.04444   0.03638  -0.0432   0.8656   1.0000
   3.750   0.3038   0.04535   0.03727  -0.0451   0.8504   1.0000
   4.000   0.3870   0.04472   0.03657  -0.0510   0.8046   1.0000
   4.250   0.4172   0.04511   0.03698  -0.0519   0.7913   1.0000
   4.500   0.4452   0.04553   0.03742  -0.0525   0.7788   1.0000
   4.750   0.4740   0.04601   0.03793  -0.0532   0.7677   1.0000
   5.000   0.5192   0.04644   0.03844  -0.0560   0.7609   1.0000
   5.250   0.5400   0.04684   0.03889  -0.0557   0.7489   1.0000
   5.500   0.5645   0.04726   0.03938  -0.0559   0.7377   1.0000
   5.750   0.5950   0.04758   0.03978  -0.0567   0.7279   1.0000
   6.000   0.6354   0.04761   0.03995  -0.0586   0.7206   1.0000
   6.250   0.6594   0.04787   0.04031  -0.0585   0.7088   1.0000
   6.500   0.6873   0.04798   0.04054  -0.0588   0.6976   1.0000
   6.750   0.7307   0.04743   0.04015  -0.0605   0.6903   1.0000
   7.000   0.7663   0.04688   0.03979  -0.0611   0.6801   1.0000
   7.250   0.7962   0.04639   0.03947  -0.0611   0.6678   1.0000
   7.500   0.8310   0.04539   0.03866  -0.0612   0.6557   1.0000
   7.750   0.8987   0.04178   0.03539  -0.0634   0.6503   1.0000
   8.000   0.9494   0.03818   0.03208  -0.0632   0.6369   1.0000
   8.500   1.0198   0.03200   0.02642  -0.0594   0.5927   1.0000
   8.750   1.0426   0.03046   0.02503  -0.0569   0.5512   1.0000
   9.000   1.0829   0.02731   0.02080  -0.0536   0.3692   1.0000
   9.250   1.0629   0.03030   0.02273  -0.0483   0.2376   1.0000
   9.500   1.0473   0.03359   0.02510  -0.0441   0.1487   1.0000
   9.750   1.0457   0.03608   0.02720  -0.0413   0.1141   1.0000
  10.000   1.0533   0.03805   0.02902  -0.0392   0.0969   1.0000
  10.250   1.0700   0.03970   0.03054  -0.0379   0.0849   1.0000
  10.500   1.0987   0.04120   0.03187  -0.0378   0.0736   1.0000
  10.750   1.1338   0.04259   0.03347  -0.0379   0.0667   1.0000
  11.000   1.1845   0.04489   0.03582  -0.0398   0.0588   1.0000
  11.250   1.2264   0.04758   0.03886  -0.0410   0.0541   1.0000
  11.500   1.2702   0.05239   0.04386  -0.0434   0.0492   1.0000
  11.750   1.2800   0.05572   0.04769  -0.0414   0.0485   1.0000
  12.000   1.2836   0.05930   0.05171  -0.0391   0.0481   1.0000
  12.250   1.2784   0.06262   0.05546  -0.0362   0.0474   1.0000
  12.500   1.2686   0.06598   0.05919  -0.0332   0.0467   1.0000
  12.750   1.2566   0.06968   0.06324  -0.0305   0.0464   1.0000
  13.000   1.2417   0.07365   0.06754  -0.0281   0.0463   1.0000
  13.250   1.2246   0.07790   0.07209  -0.0261   0.0464   1.0000
  13.500   1.2060   0.08253   0.07699  -0.0246   0.0468   1.0000
  13.750   1.1857   0.08748   0.08220  -0.0236   0.0471   1.0000
  14.000   1.1653   0.09276   0.08770  -0.0233   0.0476   1.0000
  14.250   1.1449   0.09843   0.09357  -0.0236   0.0482   1.0000
  14.500   1.1262   0.10454   0.09984  -0.0246   0.0488   1.0000
  14.750   0.8779   0.10768   0.10399  -0.0212   0.0562   1.0000
  15.000   0.8399   0.11686   0.11330  -0.0271   0.0581   1.0000
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