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I.S.A. 962 (isa962-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: I.S.A. 962 (isa962-il)
Reynolds number: 500,000
Max Cl/Cd: 88.29 at α=3.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-isa962-il-500000-n5.txt
Download as CSV file: xf-isa962-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: I.S.A. 962                                      
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.3276   0.10255   0.10011  -0.0280   1.0000   0.0229
 -10.250  -0.3235   0.09930   0.09688  -0.0293   1.0000   0.0226
 -10.000  -0.3298   0.09419   0.09179  -0.0330   1.0000   0.0238
  -9.750  -0.3177   0.09110   0.08871  -0.0350   0.9923   0.0237
  -9.500  -0.3038   0.08773   0.08533  -0.0380   0.9748   0.0235
  -9.250  -0.2902   0.08367   0.08125  -0.0423   0.9536   0.0233
  -9.000  -0.2795   0.07958   0.07712  -0.0465   0.9343   0.0233
  -8.750  -0.2733   0.07573   0.07321  -0.0500   0.9187   0.0233
  -8.500  -0.2683   0.06625   0.06362  -0.0627   0.9050   0.0241
  -8.250  -0.2541   0.06133   0.05862  -0.0682   0.8965   0.0241
  -8.000  -0.2377   0.05602   0.05322  -0.0740   0.8883   0.0241
  -7.750  -0.2194   0.05026   0.04733  -0.0799   0.8811   0.0242
  -7.500  -0.1995   0.04368   0.04057  -0.0859   0.8733   0.0242
  -7.250  -0.1783   0.03773   0.03438  -0.0904   0.8663   0.0245
  -7.000  -0.1551   0.03524   0.03177  -0.0918   0.8582   0.0247
  -6.750  -0.1382   0.02421   0.01988  -0.0960   0.8515   0.0252
  -6.500  -0.1149   0.02128   0.01655  -0.0964   0.8428   0.0254
  -6.250  -0.0903   0.01935   0.01427  -0.0963   0.8344   0.0257
  -6.000  -0.0647   0.01786   0.01250  -0.0962   0.8245   0.0259
  -5.750  -0.0385   0.01667   0.01105  -0.0960   0.8160   0.0262
  -5.500  -0.0118   0.01567   0.00983  -0.0957   0.8066   0.0264
  -5.250   0.0151   0.01484   0.00879  -0.0955   0.7953   0.0267
  -5.000   0.0421   0.01421   0.00797  -0.0952   0.7823   0.0271
  -4.750   0.0692   0.01365   0.00722  -0.0948   0.7689   0.0276
  -4.500   0.0966   0.01312   0.00653  -0.0946   0.7570   0.0278
  -4.250   0.1242   0.01265   0.00592  -0.0943   0.7455   0.0280
  -4.000   0.1517   0.01228   0.00542  -0.0940   0.7329   0.0283
  -3.750   0.1792   0.01197   0.00499  -0.0937   0.7203   0.0284
  -3.500   0.2066   0.01147   0.00441  -0.0935   0.7089   0.0288
  -3.250   0.2340   0.01113   0.00401  -0.0933   0.6975   0.0292
  -3.000   0.2615   0.01089   0.00372  -0.0931   0.6848   0.0296
  -2.500   0.3165   0.01054   0.00324  -0.0926   0.6565   0.0305
  -2.250   0.3440   0.01040   0.00304  -0.0923   0.6415   0.0310
  -2.000   0.3716   0.01028   0.00287  -0.0921   0.6276   0.0316
  -1.750   0.3993   0.01020   0.00273  -0.0919   0.6142   0.0325
  -1.500   0.4269   0.01014   0.00260  -0.0917   0.6004   0.0333
  -1.250   0.4544   0.01006   0.00247  -0.0915   0.5862   0.0339
  -1.000   0.4820   0.00997   0.00234  -0.0914   0.5721   0.0348
  -0.750   0.5097   0.00993   0.00226  -0.0912   0.5576   0.0359
  -0.500   0.5371   0.00993   0.00221  -0.0910   0.5411   0.0373
  -0.250   0.5644   0.00997   0.00217  -0.0908   0.5231   0.0389
   0.000   0.5915   0.01002   0.00215  -0.0905   0.5027   0.0413
   0.500   0.6433   0.01024   0.00225  -0.0898   0.4306   0.0978
   0.750   0.6689   0.01045   0.00236  -0.0894   0.3937   0.1229
   1.000   0.6948   0.01056   0.00249  -0.0892   0.3693   0.1753
   1.250   0.7209   0.01054   0.00266  -0.0890   0.3528   0.2836
   1.500   0.7467   0.01042   0.00283  -0.0888   0.3400   0.4300
   2.000   0.8029   0.00961   0.00315  -0.0891   0.3164   1.0000
   2.250   0.8291   0.00983   0.00328  -0.0888   0.3065   1.0000
   2.500   0.8560   0.00999   0.00340  -0.0886   0.2992   1.0000
   2.750   0.8821   0.01023   0.00356  -0.0882   0.2891   1.0000
   3.000   0.9086   0.01041   0.00370  -0.0880   0.2787   1.0000
   3.250   0.9348   0.01063   0.00386  -0.0877   0.2670   1.0000
   3.500   0.9606   0.01088   0.00402  -0.0874   0.2511   1.0000
   3.750   0.9856   0.01119   0.00421  -0.0870   0.2281   1.0000
   4.000   1.0093   0.01164   0.00447  -0.0865   0.1956   1.0000
   4.250   1.0332   0.01207   0.00477  -0.0859   0.1774   1.0000
   4.500   1.0574   0.01244   0.00506  -0.0854   0.1672   1.0000
   4.750   1.0825   0.01272   0.00532  -0.0850   0.1616   1.0000
   5.000   1.1069   0.01305   0.00562  -0.0845   0.1562   1.0000
   5.250   1.1314   0.01337   0.00591  -0.0841   0.1514   1.0000
   5.500   1.1564   0.01362   0.00618  -0.0837   0.1480   1.0000
   5.750   1.1808   0.01392   0.00648  -0.0832   0.1442   1.0000
   6.000   1.2046   0.01426   0.00681  -0.0827   0.1400   1.0000
   6.250   1.2282   0.01461   0.00715  -0.0821   0.1363   1.0000
   6.500   1.2526   0.01487   0.00745  -0.0817   0.1339   1.0000
   6.750   1.2765   0.01517   0.00777  -0.0812   0.1308   1.0000
   7.000   1.2996   0.01551   0.00811  -0.0806   0.1265   1.0000
   7.250   1.3219   0.01591   0.00850  -0.0799   0.1217   1.0000
   7.500   1.3452   0.01621   0.00882  -0.0793   0.1173   1.0000
   7.750   1.3674   0.01658   0.00918  -0.0786   0.1123   1.0000
   8.000   1.3888   0.01699   0.00958  -0.0778   0.1079   1.0000
   8.250   1.4106   0.01735   0.00998  -0.0771   0.1039   1.0000
   8.500   1.4312   0.01778   0.01040  -0.0762   0.0992   1.0000
   8.750   1.4511   0.01824   0.01085  -0.0752   0.0944   1.0000
   9.000   1.4704   0.01869   0.01132  -0.0741   0.0898   1.0000
   9.250   1.4879   0.01922   0.01184  -0.0727   0.0856   1.0000
   9.500   1.5045   0.01970   0.01236  -0.0711   0.0823   1.0000
   9.750   1.5201   0.02025   0.01293  -0.0695   0.0783   1.0000
  10.000   1.5341   0.02092   0.01359  -0.0677   0.0741   1.0000
  10.250   1.5495   0.02151   0.01423  -0.0662   0.0708   1.0000
  10.500   1.5635   0.02221   0.01496  -0.0646   0.0669   1.0000
  10.750   1.5765   0.02301   0.01578  -0.0629   0.0632   1.0000
  11.000   1.5888   0.02388   0.01666  -0.0613   0.0578   1.0000
  11.250   1.5996   0.02489   0.01768  -0.0597   0.0525   1.0000
  11.500   1.6081   0.02611   0.01888  -0.0579   0.0452   1.0000
  11.750   1.6046   0.02831   0.02095  -0.0552   0.0246   1.0000
  12.000   1.6018   0.03057   0.02320  -0.0528   0.0174   1.0000
  12.250   1.6067   0.03228   0.02497  -0.0513   0.0158   1.0000
  12.500   1.6112   0.03407   0.02685  -0.0499   0.0148   1.0000
  12.750   1.6167   0.03583   0.02871  -0.0488   0.0141   1.0000
  13.000   1.6220   0.03767   0.03066  -0.0477   0.0136   1.0000
  13.250   1.6258   0.03972   0.03280  -0.0468   0.0131   1.0000
  13.500   1.6281   0.04198   0.03517  -0.0460   0.0127   1.0000
  13.750   1.6287   0.04451   0.03781  -0.0454   0.0123   1.0000
  14.000   1.6272   0.04735   0.04076  -0.0449   0.0119   1.0000
  14.250   1.6233   0.05054   0.04408  -0.0445   0.0116   1.0000
  14.500   1.6218   0.05359   0.04725  -0.0444   0.0114   1.0000
  14.750   1.6196   0.05684   0.05062  -0.0445   0.0112   1.0000
  15.000   1.6156   0.06041   0.05432  -0.0448   0.0109   1.0000
  15.250   1.6098   0.06436   0.05839  -0.0454   0.0107   1.0000
  15.500   1.6023   0.06866   0.06282  -0.0462   0.0106   1.0000
  15.750   1.5927   0.07340   0.06771  -0.0472   0.0104   1.0000
  16.000   1.5812   0.07855   0.07299  -0.0486   0.0103   1.0000
  16.250   1.5677   0.08420   0.07878  -0.0503   0.0102   1.0000
  16.500   1.5522   0.09035   0.08509  -0.0523   0.0101   1.0000
  16.750   1.5348   0.09694   0.09183  -0.0546   0.0100   1.0000
  17.000   1.5161   0.10395   0.09899  -0.0573   0.0100   1.0000
  17.250   1.4961   0.11131   0.10651  -0.0602   0.0099   1.0000
  17.500   1.4754   0.11884   0.11418  -0.0633   0.0099   1.0000
  17.750   1.4540   0.12667   0.12215  -0.0668   0.0099   1.0000
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