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I.S.A. 960 (isa960-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: I.S.A. 960 (isa960-il)
Reynolds number: 100,000
Max Cl/Cd: 55.87 at α=3.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-isa960-il-100000.txt
Download as CSV file: xf-isa960-il-100000.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 =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.3410   0.09220   0.08789  -0.0287   1.0000   0.0989
  -8.250  -0.3571   0.09089   0.08671  -0.0275   1.0000   0.1006
  -8.000  -0.3778   0.08997   0.08589  -0.0292   1.0000   0.1022
  -7.750  -0.3952   0.08875   0.08469  -0.0348   1.0000   0.1030
  -7.500  -0.3961   0.08473   0.08077  -0.0311   1.0000   0.1038
  -7.250  -0.3936   0.08206   0.07818  -0.0248   1.0000   0.1057
  -7.000  -0.3948   0.08013   0.07631  -0.0221   1.0000   0.1085
  -6.750  -0.3968   0.07795   0.07415  -0.0222   1.0000   0.1123
  -6.500  -0.3907   0.07411   0.07012  -0.0326   0.9998   0.1176
  -6.250  -0.3541   0.06905   0.06513  -0.0337   0.9924   0.1214
  -6.000  -0.2981   0.06231   0.05805  -0.0489   0.9835   0.1329
  -5.750  -0.2598   0.05829   0.05401  -0.0524   0.9741   0.1416
  -5.500  -0.1983   0.04157   0.03591  -0.0701   0.9696   0.0886
  -5.250  -0.1551   0.03596   0.02989  -0.0750   0.9612   0.0861
  -5.000  -0.1072   0.03032   0.02318  -0.0801   0.9553   0.0898
  -4.750  -0.0662   0.02814   0.02089  -0.0830   0.9470   0.0951
  -4.500  -0.0209   0.02575   0.01793  -0.0863   0.9406   0.1058
  -4.250   0.0235   0.02404   0.01591  -0.0890   0.9324   0.1194
  -4.000   0.0698   0.02284   0.01443  -0.0920   0.9239   0.1455
  -3.750   0.1152   0.02164   0.01322  -0.0949   0.9152   0.1706
  -3.500   0.1534   0.02086   0.01226  -0.0962   0.9023   0.1901
  -3.250   0.1887   0.02014   0.01144  -0.0970   0.8889   0.2075
  -3.000   0.2206   0.01934   0.01063  -0.0972   0.8765   0.2173
  -2.750   0.2524   0.01859   0.00974  -0.0973   0.8652   0.2242
  -2.500   0.2827   0.01791   0.00904  -0.0971   0.8537   0.2334
  -2.250   0.3094   0.01735   0.00850  -0.0964   0.8404   0.2448
  -2.000   0.3362   0.01681   0.00801  -0.0957   0.8275   0.2619
  -1.750   0.3629   0.01627   0.00757  -0.0950   0.8146   0.2884
  -1.500   0.3894   0.01567   0.00712  -0.0942   0.8016   0.3281
  -1.250   0.4236   0.01331   0.00671  -0.0944   0.7891   1.0000
  -1.000   0.4519   0.01330   0.00631  -0.0938   0.7761   1.0000
  -0.750   0.4794   0.01330   0.00606  -0.0932   0.7635   1.0000
  -0.500   0.5062   0.01334   0.00590  -0.0926   0.7494   1.0000
  -0.250   0.5328   0.01337   0.00573  -0.0918   0.7332   1.0000
   0.000   0.5593   0.01344   0.00563  -0.0912   0.7175   1.0000
   0.250   0.5856   0.01355   0.00559  -0.0906   0.7021   1.0000
   0.500   0.6114   0.01367   0.00558  -0.0899   0.6852   1.0000
   0.750   0.6369   0.01379   0.00562  -0.0893   0.6672   1.0000
   1.000   0.6625   0.01392   0.00566  -0.0887   0.6498   1.0000
   1.250   0.6882   0.01406   0.00573  -0.0881   0.6327   1.0000
   1.500   0.7138   0.01421   0.00580  -0.0875   0.6147   1.0000
   1.750   0.7394   0.01436   0.00588  -0.0869   0.5960   1.0000
   2.000   0.7648   0.01453   0.00597  -0.0863   0.5759   1.0000
   2.250   0.7900   0.01473   0.00607  -0.0857   0.5553   1.0000
   2.500   0.8150   0.01497   0.00621  -0.0850   0.5348   1.0000
   2.750   0.8397   0.01524   0.00639  -0.0844   0.5131   1.0000
   3.000   0.8635   0.01556   0.00659  -0.0836   0.4881   1.0000
   3.250   0.8873   0.01592   0.00685  -0.0828   0.4623   1.0000
   3.500   0.9106   0.01630   0.00716  -0.0820   0.4348   1.0000
   3.750   0.9334   0.01674   0.00748  -0.0812   0.4062   1.0000
   4.000   0.9559   0.01720   0.00783  -0.0803   0.3797   1.0000
   4.250   0.9781   0.01770   0.00823  -0.0795   0.3561   1.0000
   4.500   1.0002   0.01823   0.00869  -0.0786   0.3373   1.0000
   4.750   1.0221   0.01879   0.00916  -0.0777   0.3205   1.0000
   5.000   1.0437   0.01938   0.00968  -0.0768   0.3059   1.0000
   5.250   1.0649   0.02003   0.01026  -0.0759   0.2940   1.0000
   5.500   1.0866   0.02066   0.01089  -0.0751   0.2828   1.0000
   5.750   1.1080   0.02135   0.01156  -0.0742   0.2724   1.0000
   6.000   1.1289   0.02216   0.01229  -0.0733   0.2629   1.0000
   6.250   1.1508   0.02291   0.01310  -0.0725   0.2534   1.0000
   6.500   1.1733   0.02381   0.01396  -0.0718   0.2454   1.0000
   6.750   1.1966   0.02468   0.01486  -0.0713   0.2381   1.0000
   7.000   1.2217   0.02570   0.01582  -0.0711   0.2327   1.0000
   7.250   1.2463   0.02660   0.01690  -0.0708   0.2278   1.0000
   7.500   1.2710   0.02751   0.01789  -0.0706   0.2230   1.0000
   7.750   1.2939   0.02839   0.01877  -0.0702   0.2168   1.0000
   8.000   1.3106   0.02891   0.01952  -0.0687   0.2082   1.0000
   8.250   1.3268   0.02942   0.02014  -0.0673   0.1999   1.0000
   8.500   1.3430   0.02992   0.02087  -0.0658   0.1924   1.0000
   8.750   1.3593   0.03047   0.02157  -0.0644   0.1862   1.0000
   9.000   1.3717   0.03084   0.02219  -0.0624   0.1777   1.0000
   9.250   1.3826   0.03122   0.02281  -0.0602   0.1684   1.0000
   9.500   1.3878   0.03163   0.02332  -0.0572   0.1577   1.0000
   9.750   1.3914   0.03253   0.02424  -0.0544   0.1481   1.0000
  10.000   1.3902   0.03426   0.02581  -0.0515   0.1369   1.0000
  10.250   1.3880   0.03695   0.02832  -0.0488   0.1225   1.0000
  10.500   1.3850   0.04031   0.03160  -0.0463   0.1034   1.0000
  10.750   1.3720   0.04261   0.03440  -0.0432   0.0899   1.0000
  11.000   1.3758   0.04396   0.03627  -0.0421   0.0651   1.0000
  11.250   1.3779   0.04600   0.03810  -0.0416   0.0587   1.0000
  11.500   1.3725   0.04912   0.04123  -0.0404   0.0551   1.0000
  11.750   1.3657   0.05252   0.04473  -0.0394   0.0524   1.0000
  12.000   1.3569   0.05625   0.04852  -0.0387   0.0502   1.0000
  12.250   1.3474   0.06013   0.05241  -0.0380   0.0483   1.0000
  12.500   1.3448   0.06340   0.05585  -0.0373   0.0465   1.0000
  12.750   1.3427   0.06670   0.05932  -0.0368   0.0447   1.0000
  13.000   1.3415   0.06992   0.06270  -0.0362   0.0434   1.0000
  13.250   1.3414   0.07308   0.06598  -0.0356   0.0423   1.0000
  13.500   1.3415   0.07632   0.06932  -0.0351   0.0412   1.0000
  13.750   1.3417   0.07964   0.07275  -0.0345   0.0404   1.0000
  14.000   1.3424   0.08306   0.07628  -0.0340   0.0396   1.0000
  14.250   1.3407   0.08700   0.08038  -0.0337   0.0391   1.0000
  14.500   1.3349   0.09170   0.08526  -0.0339   0.0386   1.0000
  14.750   1.3235   0.09712   0.09089  -0.0351   0.0384   1.0000
  15.000   1.3093   0.10301   0.09703  -0.0373   0.0384   1.0000
  15.250   1.2936   0.10945   0.10371  -0.0402   0.0383   1.0000
  15.500   1.2764   0.11644   0.11092  -0.0436   0.0384   1.0000
  15.750   1.2583   0.12397   0.11869  -0.0477   0.0385   1.0000
  16.000   1.2353   0.13323   0.12823  -0.0542   0.0391   1.0000
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