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I.S.A. 961 (isa961-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: I.S.A. 961 (isa961-il)
Reynolds number: 100,000
Max Cl/Cd: 55.53 at α=3.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-isa961-il-100000.txt
Download as CSV file: xf-isa961-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: I.S.A. 961                                      
  
 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  -0.3456   0.09443   0.08995  -0.0283   1.0000   0.0910
  -8.250  -0.3653   0.09349   0.08916  -0.0290   1.0000   0.0921
  -8.000  -0.3826   0.09233   0.08808  -0.0323   1.0000   0.0927
  -7.750  -0.3903   0.08957   0.08536  -0.0342   1.0000   0.0932
  -7.500  -0.3861   0.08543   0.08130  -0.0280   1.0000   0.0943
  -7.250  -0.3847   0.08278   0.07870  -0.0246   1.0000   0.0956
  -7.000  -0.3850   0.08040   0.07636  -0.0228   1.0000   0.0974
  -6.750  -0.3851   0.07793   0.07391  -0.0224   1.0000   0.0996
  -6.500  -0.3829   0.07511   0.07108  -0.0241   1.0000   0.1032
  -6.250  -0.3733   0.07074   0.06656  -0.0323   1.0000   0.1074
  -6.000  -0.3694   0.06795   0.06383  -0.0291   1.0000   0.1089
  -5.750  -0.3620   0.06546   0.06136  -0.0278   1.0000   0.1117
  -5.500  -0.3405   0.06144   0.05707  -0.0345   1.0000   0.1214
  -5.250  -0.3352   0.05935   0.05510  -0.0310   1.0000   0.1251
  -5.000  -0.2812   0.04416   0.03879  -0.0448   1.0000   0.0780
  -4.750  -0.2514   0.03920   0.03350  -0.0475   0.9989   0.0753
  -4.500  -0.2023   0.03212   0.02533  -0.0531   0.9961   0.0773
  -4.250  -0.1572   0.02970   0.02252  -0.0571   0.9905   0.0886
  -4.000  -0.1089   0.02767   0.02001  -0.0613   0.9848   0.1106
  -3.750  -0.0657   0.02728   0.01937  -0.0646   0.9762   0.1368
  -3.500  -0.0232   0.02728   0.01941  -0.0680   0.9682   0.1594
  -3.250   0.0203   0.02603   0.01776  -0.0711   0.9608   0.1675
  -3.000   0.0615   0.02529   0.01682  -0.0738   0.9529   0.1755
  -2.750   0.1065   0.02437   0.01557  -0.0770   0.9457   0.1803
  -2.500   0.1446   0.02371   0.01488  -0.0791   0.9367   0.1876
  -2.250   0.1919   0.02295   0.01400  -0.0827   0.9302   0.1970
  -2.000   0.2281   0.02241   0.01343  -0.0842   0.9198   0.2060
  -1.750   0.2794   0.02155   0.01261  -0.0883   0.9145   0.2226
  -1.500   0.3162   0.02085   0.01210  -0.0897   0.9031   0.2488
  -1.250   0.3603   0.01978   0.01131  -0.0920   0.8925   0.3052
  -1.000   0.4228   0.01673   0.01015  -0.0970   0.8855   1.0000
  -0.750   0.4606   0.01635   0.00946  -0.0976   0.8712   1.0000
  -0.500   0.4941   0.01604   0.00897  -0.0976   0.8567   1.0000
  -0.250   0.5253   0.01578   0.00856  -0.0972   0.8419   1.0000
   0.000   0.5549   0.01554   0.00820  -0.0966   0.8267   1.0000
   0.250   0.5835   0.01532   0.00787  -0.0958   0.8111   1.0000
   0.500   0.6115   0.01514   0.00758  -0.0949   0.7952   1.0000
   0.750   0.6381   0.01501   0.00737  -0.0939   0.7779   1.0000
   1.000   0.6635   0.01495   0.00722  -0.0927   0.7585   1.0000
   1.250   0.6901   0.01485   0.00703  -0.0917   0.7388   1.0000
   1.500   0.7166   0.01479   0.00685  -0.0907   0.7178   1.0000
   1.750   0.7418   0.01481   0.00678  -0.0896   0.6937   1.0000
   2.000   0.7670   0.01488   0.00673  -0.0885   0.6689   1.0000
   2.250   0.7925   0.01500   0.00670  -0.0875   0.6445   1.0000
   2.500   0.8169   0.01520   0.00682  -0.0865   0.6183   1.0000
   2.750   0.8411   0.01545   0.00693  -0.0855   0.5918   1.0000
   3.000   0.8650   0.01574   0.00707  -0.0845   0.5652   1.0000
   3.250   0.8887   0.01606   0.00722  -0.0835   0.5392   1.0000
   3.500   0.9116   0.01643   0.00747  -0.0824   0.5130   1.0000
   3.750   0.9345   0.01683   0.00775  -0.0814   0.4883   1.0000
   4.000   0.9575   0.01726   0.00802  -0.0805   0.4663   1.0000
   4.250   0.9805   0.01771   0.00840  -0.0796   0.4458   1.0000
   4.500   1.0040   0.01819   0.00884  -0.0789   0.4288   1.0000
   4.750   1.0278   0.01869   0.00930  -0.0783   0.4142   1.0000
   5.000   1.0516   0.01919   0.00978  -0.0777   0.4008   1.0000
   5.250   1.0751   0.01969   0.01028  -0.0770   0.3875   1.0000
   5.500   1.0983   0.02019   0.01076  -0.0763   0.3745   1.0000
   5.750   1.1215   0.02068   0.01131  -0.0756   0.3624   1.0000
   6.000   1.1444   0.02118   0.01189  -0.0749   0.3505   1.0000
   6.250   1.1671   0.02170   0.01250  -0.0742   0.3392   1.0000
   6.500   1.1896   0.02225   0.01308  -0.0734   0.3281   1.0000
   6.750   1.2116   0.02280   0.01367  -0.0726   0.3166   1.0000
   7.000   1.2323   0.02335   0.01432  -0.0716   0.3036   1.0000
   7.250   1.2521   0.02392   0.01500  -0.0704   0.2898   1.0000
   7.500   1.2714   0.02456   0.01572  -0.0692   0.2761   1.0000
   7.750   1.2892   0.02521   0.01642  -0.0678   0.2612   1.0000
   8.000   1.3049   0.02583   0.01707  -0.0661   0.2452   1.0000
   8.250   1.3193   0.02646   0.01773  -0.0643   0.2293   1.0000
   8.500   1.3336   0.02715   0.01853  -0.0625   0.2148   1.0000
   8.750   1.3482   0.02788   0.01939  -0.0608   0.2016   1.0000
   9.000   1.3625   0.02864   0.02030  -0.0590   0.1894   1.0000
   9.250   1.3746   0.02939   0.02116  -0.0570   0.1761   1.0000
   9.500   1.3834   0.03018   0.02203  -0.0546   0.1625   1.0000
   9.750   1.3904   0.03118   0.02306  -0.0520   0.1508   1.0000
  10.000   1.3957   0.03243   0.02433  -0.0494   0.1407   1.0000
  10.250   1.3975   0.03402   0.02590  -0.0467   0.1322   1.0000
  10.500   1.3991   0.03579   0.02778  -0.0443   0.1220   1.0000
  10.750   1.3982   0.03783   0.02993  -0.0419   0.1106   1.0000
  11.000   1.3964   0.04004   0.03231  -0.0398   0.0975   1.0000
  11.250   1.3979   0.04214   0.03461  -0.0384   0.0769   1.0000
  11.500   1.3893   0.04528   0.03758  -0.0370   0.0666   1.0000
  11.750   1.3731   0.04939   0.04159  -0.0357   0.0618   1.0000
  12.000   1.3598   0.05351   0.04584  -0.0346   0.0576   1.0000
  12.250   1.3467   0.05778   0.05019  -0.0340   0.0545   1.0000
  12.500   1.3359   0.06169   0.05397  -0.0325   0.0513   1.0000
  12.750   1.3331   0.06514   0.05765  -0.0320   0.0489   1.0000
  13.000   1.3315   0.06847   0.06113  -0.0313   0.0464   1.0000
  13.250   1.3309   0.07166   0.06439  -0.0306   0.0441   1.0000
  13.500   1.3409   0.07384   0.06642  -0.0283   0.0411   1.0000
  13.750   1.3333   0.07801   0.07090  -0.0290   0.0402   1.0000
  14.000   1.3265   0.08229   0.07544  -0.0297   0.0391   1.0000
  14.250   1.3199   0.08674   0.08013  -0.0306   0.0381   1.0000
  14.500   1.3123   0.09148   0.08510  -0.0317   0.0374   1.0000
  14.750   1.3033   0.09657   0.09041  -0.0331   0.0369   1.0000
  15.000   1.2921   0.10221   0.09628  -0.0351   0.0366   1.0000
  15.250   1.2782   0.10851   0.10281  -0.0378   0.0365   1.0000
  15.500   1.2613   0.11569   0.11022  -0.0414   0.0365   1.0000
  15.750   1.2407   0.12395   0.11872  -0.0460   0.0368   1.0000
  16.000   1.2163   0.13358   0.12858  -0.0519   0.0373   1.0000
  16.250   1.1883   0.14481   0.14002  -0.0591   0.0381   1.0000
  16.500   1.1571   0.15783   0.15317  -0.0675   0.0393   1.0000
  16.750   1.1303   0.17063   0.16602  -0.0752   0.0405   1.0000
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