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I.S.A. 960 (isa960-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: I.S.A. 960 (isa960-il)
Reynolds number: 200,000
Max Cl/Cd: 64.71 at α=6°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-isa960-il-200000.txt
Download as CSV file: xf-isa960-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: I.S.A. 960                                      
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3424   0.08871   0.08563  -0.0312   1.0000   0.0559
  -8.500  -0.3559   0.08753   0.08454  -0.0281   1.0000   0.0570
  -8.250  -0.3743   0.08655   0.08366  -0.0246   1.0000   0.0577
  -8.000  -0.3346   0.07775   0.07468  -0.0545   0.9878   0.0630
  -7.750  -0.3202   0.07266   0.06968  -0.0512   0.9847   0.0646
  -7.500  -0.2932   0.06911   0.06611  -0.0535   0.9779   0.0665
  -7.250  -0.2587   0.06410   0.06103  -0.0613   0.9715   0.0698
  -7.000  -0.2098   0.05514   0.05153  -0.0809   0.9603   0.0755
  -6.750  -0.2036   0.02703   0.02172  -0.0916   0.9574   0.0427
  -6.500  -0.1730   0.02238   0.01644  -0.0937   0.9472   0.0441
  -6.250  -0.1365   0.02030   0.01405  -0.0954   0.9364   0.0461
  -6.000  -0.1007   0.01882   0.01224  -0.0966   0.9249   0.0496
  -5.750  -0.0676   0.01727   0.01031  -0.0973   0.9140   0.0531
  -5.500  -0.0386   0.01652   0.00951  -0.0972   0.9009   0.0567
  -5.250  -0.0101   0.01601   0.00878  -0.0967   0.8869   0.0622
  -5.000   0.0166   0.01525   0.00798  -0.0962   0.8717   0.0680
  -4.750   0.0435   0.01474   0.00724  -0.0953   0.8542   0.0760
  -4.500   0.0695   0.01400   0.00648  -0.0947   0.8374   0.0907
  -4.250   0.0960   0.01378   0.00627  -0.0941   0.8187   0.1092
  -4.000   0.1228   0.01385   0.00621  -0.0935   0.7981   0.1228
  -3.750   0.1499   0.01383   0.00594  -0.0929   0.7771   0.1322
  -3.500   0.1763   0.01364   0.00567  -0.0923   0.7551   0.1392
  -3.250   0.2031   0.01363   0.00539  -0.0917   0.7340   0.1464
  -3.000   0.2295   0.01341   0.00514  -0.0913   0.7156   0.1550
  -2.750   0.2566   0.01326   0.00483  -0.0909   0.6985   0.1619
  -2.500   0.2833   0.01298   0.00454  -0.0906   0.6814   0.1695
  -2.250   0.3103   0.01274   0.00422  -0.0902   0.6638   0.1775
  -2.000   0.3370   0.01246   0.00394  -0.0899   0.6445   0.1881
  -1.750   0.3629   0.01224   0.00367  -0.0894   0.6113   0.2037
  -1.500   0.3883   0.01211   0.00346  -0.0888   0.5735   0.2249
  -1.250   0.4134   0.01208   0.00333  -0.0882   0.5368   0.2519
  -1.000   0.4383   0.01201   0.00327  -0.0877   0.5044   0.2965
  -0.750   0.4672   0.01032   0.00328  -0.0876   0.4739   1.0000
  -0.500   0.4925   0.01058   0.00325  -0.0871   0.4420   1.0000
  -0.250   0.5174   0.01089   0.00327  -0.0865   0.4038   1.0000
   0.000   0.5405   0.01141   0.00337  -0.0857   0.3353   1.0000
   0.250   0.5633   0.01201   0.00354  -0.0850   0.2754   1.0000
   0.500   0.5891   0.01227   0.00365  -0.0846   0.2626   1.0000
   0.750   0.6153   0.01248   0.00375  -0.0844   0.2554   1.0000
   1.000   0.6416   0.01268   0.00387  -0.0841   0.2502   1.0000
   1.250   0.6680   0.01286   0.00399  -0.0839   0.2466   1.0000
   1.500   0.6945   0.01304   0.00413  -0.0836   0.2432   1.0000
   1.750   0.7204   0.01327   0.00430  -0.0833   0.2377   1.0000
   2.000   0.7464   0.01350   0.00448  -0.0830   0.2340   1.0000
   2.250   0.7726   0.01369   0.00465  -0.0828   0.2309   1.0000
   2.500   0.7987   0.01390   0.00485  -0.0825   0.2278   1.0000
   2.750   0.8246   0.01411   0.00506  -0.0823   0.2246   1.0000
   3.000   0.8503   0.01435   0.00528  -0.0820   0.2218   1.0000
   3.250   0.8758   0.01460   0.00552  -0.0816   0.2193   1.0000
   3.500   0.9014   0.01483   0.00578  -0.0813   0.2173   1.0000
   3.750   0.9271   0.01505   0.00604  -0.0810   0.2153   1.0000
   4.000   0.9526   0.01528   0.00631  -0.0807   0.2131   1.0000
   4.250   0.9778   0.01555   0.00662  -0.0804   0.2093   1.0000
   4.500   1.0025   0.01584   0.00694  -0.0799   0.2063   1.0000
   4.750   1.0267   0.01617   0.00729  -0.0795   0.2032   1.0000
   5.000   1.0518   0.01643   0.00762  -0.0791   0.1997   1.0000
   5.250   1.0763   0.01672   0.00800  -0.0786   0.1954   1.0000
   5.500   1.1003   0.01706   0.00838  -0.0781   0.1909   1.0000
   5.750   1.1240   0.01741   0.00878  -0.0776   0.1866   1.0000
   6.000   1.1480   0.01774   0.00919  -0.0771   0.1805   1.0000
   6.250   1.1711   0.01811   0.00961  -0.0765   0.1740   1.0000
   6.750   1.2149   0.01899   0.01039  -0.0751   0.1551   1.0000
   7.000   1.2340   0.01963   0.01097  -0.0740   0.1485   1.0000
   7.250   1.2516   0.02038   0.01171  -0.0727   0.1439   1.0000
   7.500   1.2681   0.02118   0.01249  -0.0713   0.1402   1.0000
   7.750   1.2854   0.02194   0.01332  -0.0699   0.1371   1.0000
   8.000   1.3003   0.02286   0.01429  -0.0683   0.1338   1.0000
   8.250   1.3131   0.02406   0.01542  -0.0664   0.1302   1.0000
   8.500   1.3277   0.02503   0.01650  -0.0647   0.1260   1.0000
   8.750   1.3413   0.02640   0.01784  -0.0632   0.1202   1.0000
   9.000   1.3557   0.02785   0.01934  -0.0618   0.1128   1.0000
   9.250   1.3704   0.02943   0.02091  -0.0606   0.1043   1.0000
   9.500   1.3731   0.03048   0.02208  -0.0575   0.0951   1.0000
   9.750   1.3875   0.02918   0.02113  -0.0559   0.0447   1.0000
  10.000   1.3884   0.03118   0.02312  -0.0532   0.0367   1.0000
  10.250   1.3934   0.03289   0.02491  -0.0512   0.0326   1.0000
  10.500   1.3943   0.03500   0.02711  -0.0491   0.0302   1.0000
  10.750   1.3992   0.03682   0.02909  -0.0475   0.0288   1.0000
  11.000   1.4018   0.03890   0.03133  -0.0459   0.0276   1.0000
  11.250   1.4025   0.04125   0.03382  -0.0446   0.0266   1.0000
  11.500   1.4012   0.04389   0.03660  -0.0434   0.0258   1.0000
  11.750   1.3978   0.04688   0.03972  -0.0426   0.0251   1.0000
  12.000   1.3911   0.05032   0.04327  -0.0419   0.0245   1.0000
  12.250   1.3819   0.05418   0.04725  -0.0413   0.0239   1.0000
  12.500   1.3757   0.05777   0.05094  -0.0409   0.0234   1.0000
  12.750   1.3737   0.06097   0.05428  -0.0407   0.0229   1.0000
  13.000   1.3712   0.06430   0.05774  -0.0406   0.0225   1.0000
  13.250   1.3688   0.06767   0.06122  -0.0404   0.0221   1.0000
  13.500   1.3666   0.07108   0.06474  -0.0403   0.0218   1.0000
  13.750   1.3648   0.07451   0.06829  -0.0403   0.0214   1.0000
  14.000   1.3635   0.07791   0.07181  -0.0402   0.0212   1.0000
  14.250   1.3625   0.08130   0.07532  -0.0402   0.0209   1.0000
  14.500   1.3614   0.08478   0.07892  -0.0403   0.0207   1.0000
  14.750   1.3591   0.08855   0.08284  -0.0406   0.0205   1.0000
  15.000   1.3555   0.09260   0.08705  -0.0412   0.0204   1.0000
  15.250   1.3501   0.09705   0.09167  -0.0421   0.0203   1.0000
  15.500   1.3431   0.10189   0.09669  -0.0435   0.0203   1.0000
  15.750   1.3345   0.10715   0.10216  -0.0453   0.0203   1.0000
  16.000   1.3245   0.11284   0.10804  -0.0477   0.0202   1.0000
  16.250   1.3124   0.11913   0.11453  -0.0506   0.0203   1.0000
  16.500   1.2982   0.12609   0.12170  -0.0543   0.0203   1.0000
  16.750   1.2817   0.13391   0.12974  -0.0588   0.0204   1.0000
  17.000   1.2626   0.14280   0.13884  -0.0643   0.0207   1.0000
  17.250   1.2395   0.15327   0.14954  -0.0711   0.0211   1.0000
  17.500   1.2134   0.16518   0.16167  -0.0790   0.0216   1.0000
  17.750   1.1834   0.17920   0.17586  -0.0882   0.0223   1.0000
  18.000   1.1489   0.19633   0.19309  -0.0988   0.0232   1.0000
  18.250   0.7932   0.19361   0.19055  -0.0711   0.0298   1.0000
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