Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

I.S.A. 961 (isa961-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: I.S.A. 961 (isa961-il)
Reynolds number: 500,000
Max Cl/Cd: 80.02 at α=3.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-isa961-il-500000.txt
Download as CSV file: xf-isa961-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.2629   0.08618   0.08420  -0.0325   1.0000   0.0252
  -9.500  -0.2737   0.08437   0.08245  -0.0301   0.9998   0.0259
  -9.250  -0.2744   0.07790   0.07599  -0.0370   0.9973   0.0282
  -9.000  -0.3494   0.08678   0.08470  -0.0313   1.0000   0.0246
  -8.750  -0.2700   0.06566   0.06377  -0.0453   0.9911   0.0291
  -8.250  -0.3697   0.03030   0.02731  -0.0852   0.9787   0.0163
  -8.000  -0.3454   0.02269   0.01874  -0.0895   0.9745   0.0158
  -7.750  -0.3134   0.01969   0.01523  -0.0916   0.9726   0.0160
  -7.500  -0.2810   0.01780   0.01298  -0.0931   0.9701   0.0164
  -7.250  -0.2522   0.01651   0.01144  -0.0934   0.9647   0.0168
  -7.000  -0.2197   0.01553   0.01024  -0.0944   0.9612   0.0171
  -6.750  -0.1883   0.01376   0.00823  -0.0953   0.9581   0.0179
  -6.500  -0.1606   0.01289   0.00729  -0.0953   0.9517   0.0190
  -6.250  -0.1299   0.01226   0.00658  -0.0957   0.9459   0.0205
  -6.000  -0.1012   0.01167   0.00588  -0.0956   0.9373   0.0217
  -5.750  -0.0728   0.01099   0.00507  -0.0953   0.9275   0.0231
  -5.500  -0.0462   0.01047   0.00446  -0.0946   0.9159   0.0258
  -5.250  -0.0197   0.01008   0.00398  -0.0939   0.9048   0.0296
  -5.000   0.0075   0.00978   0.00382  -0.0935   0.8957   0.0557
  -4.750   0.0359   0.01006   0.00403  -0.0932   0.8865   0.0678
  -4.500   0.0628   0.01001   0.00397  -0.0928   0.8754   0.0740
  -4.250   0.0901   0.01006   0.00391  -0.0924   0.8637   0.0784
  -4.000   0.1167   0.00977   0.00356  -0.0919   0.8528   0.0836
  -3.750   0.1438   0.00960   0.00335  -0.0916   0.8418   0.0873
  -3.500   0.1711   0.00949   0.00319  -0.0912   0.8299   0.0913
  -3.250   0.1981   0.00929   0.00292  -0.0908   0.8172   0.0955
  -3.000   0.2249   0.00910   0.00270  -0.0904   0.8020   0.0995
  -2.750   0.2520   0.00897   0.00250  -0.0900   0.7862   0.1022
  -2.500   0.2792   0.00887   0.00232  -0.0897   0.7711   0.1048
  -2.250   0.3065   0.00877   0.00216  -0.0894   0.7562   0.1079
  -2.000   0.3337   0.00869   0.00206  -0.0890   0.7404   0.1139
  -1.750   0.3610   0.00866   0.00197  -0.0887   0.7237   0.1215
  -1.500   0.3880   0.00863   0.00191  -0.0884   0.7062   0.1363
  -1.250   0.4150   0.00860   0.00188  -0.0881   0.6875   0.1595
  -1.000   0.4418   0.00861   0.00184  -0.0878   0.6652   0.1794
  -0.750   0.4679   0.00865   0.00182  -0.0874   0.6368   0.1983
  -0.500   0.4936   0.00873   0.00183  -0.0869   0.6036   0.2209
  -0.250   0.5190   0.00881   0.00186  -0.0864   0.5677   0.2601
   0.000   0.5437   0.00880   0.00193  -0.0859   0.5275   0.3521
   0.250   0.5789   0.00753   0.00209  -0.0878   0.4864   1.0000
   0.500   0.6037   0.00783   0.00217  -0.0872   0.4529   1.0000
   0.750   0.6288   0.00810   0.00226  -0.0867   0.4246   1.0000
   1.000   0.6541   0.00835   0.00236  -0.0862   0.3995   1.0000
   1.250   0.6794   0.00862   0.00247  -0.0858   0.3741   1.0000
   1.500   0.7045   0.00892   0.00259  -0.0853   0.3447   1.0000
   1.750   0.7297   0.00920   0.00272  -0.0849   0.3179   1.0000
   2.000   0.7549   0.00950   0.00287  -0.0844   0.2920   1.0000
   2.250   0.7798   0.00982   0.00303  -0.0840   0.2676   1.0000
   2.500   0.8048   0.01013   0.00321  -0.0835   0.2464   1.0000
   2.750   0.8298   0.01043   0.00340  -0.0831   0.2286   1.0000
   3.000   0.8550   0.01072   0.00359  -0.0827   0.2109   1.0000
   3.250   0.8802   0.01100   0.00377  -0.0824   0.1939   1.0000
   3.500   0.9023   0.01162   0.00410  -0.0816   0.1402   1.0000
   3.750   0.9264   0.01201   0.00438  -0.0811   0.1280   1.0000
   4.000   0.9513   0.01231   0.00465  -0.0806   0.1222   1.0000
   4.250   0.9767   0.01256   0.00489  -0.0803   0.1184   1.0000
   4.500   1.0021   0.01279   0.00514  -0.0800   0.1160   1.0000
   4.750   1.0272   0.01304   0.00540  -0.0796   0.1137   1.0000
   5.000   1.0521   0.01331   0.00568  -0.0792   0.1114   1.0000
   5.250   1.0766   0.01362   0.00600  -0.0788   0.1086   1.0000
   5.500   1.1012   0.01390   0.00629  -0.0784   0.1047   1.0000
   5.750   1.1264   0.01411   0.00653  -0.0781   0.1016   1.0000
   6.000   1.1507   0.01441   0.00683  -0.0776   0.0968   1.0000
   6.250   1.1746   0.01473   0.00716  -0.0771   0.0915   1.0000
   6.500   1.1980   0.01508   0.00745  -0.0766   0.0699   1.0000
   6.750   1.2192   0.01564   0.00789  -0.0758   0.0614   1.0000
   7.000   1.2411   0.01611   0.00839  -0.0750   0.0589   1.0000
   7.250   1.2619   0.01666   0.00898  -0.0740   0.0561   1.0000
   7.500   1.2825   0.01721   0.00956  -0.0731   0.0527   1.0000
   7.750   1.3040   0.01764   0.01006  -0.0723   0.0504   1.0000
   8.000   1.3253   0.01806   0.01055  -0.0715   0.0471   1.0000
   8.250   1.3436   0.01872   0.01125  -0.0702   0.0425   1.0000
   8.500   1.3669   0.01892   0.01147  -0.0697   0.0368   1.0000
   8.750   1.3816   0.01980   0.01215  -0.0680   0.0187   1.0000
   9.000   1.3961   0.02064   0.01301  -0.0660   0.0157   1.0000
   9.250   1.4097   0.02137   0.01385  -0.0639   0.0149   1.0000
   9.500   1.4212   0.02222   0.01481  -0.0616   0.0141   1.0000
   9.750   1.4309   0.02320   0.01593  -0.0591   0.0134   1.0000
  10.000   1.4385   0.02437   0.01720  -0.0565   0.0129   1.0000
  10.250   1.4429   0.02578   0.01874  -0.0537   0.0123   1.0000
  10.500   1.4422   0.02763   0.02074  -0.0507   0.0118   1.0000
  10.750   1.4482   0.02906   0.02227  -0.0486   0.0115   1.0000
  11.000   1.4538   0.03059   0.02391  -0.0468   0.0112   1.0000
  11.250   1.4567   0.03241   0.02584  -0.0450   0.0109   1.0000
  11.500   1.4577   0.03450   0.02805  -0.0433   0.0106   1.0000
  11.750   1.4570   0.03687   0.03053  -0.0418   0.0104   1.0000
  12.000   1.4552   0.03948   0.03328  -0.0406   0.0102   1.0000
  12.250   1.4518   0.04241   0.03633  -0.0397   0.0100   1.0000
  12.500   1.4474   0.04562   0.03965  -0.0391   0.0099   1.0000
  12.750   1.4417   0.04911   0.04325  -0.0388   0.0097   1.0000
  13.000   1.4351   0.05288   0.04714  -0.0388   0.0096   1.0000
  13.250   1.4279   0.05688   0.05126  -0.0391   0.0095   1.0000
  13.500   1.4196   0.06113   0.05561  -0.0396   0.0094   1.0000
  13.750   1.4111   0.06557   0.06016  -0.0403   0.0093   1.0000
  14.000   1.4023   0.07012   0.06481  -0.0410   0.0091   1.0000
  14.250   1.3940   0.07462   0.06941  -0.0418   0.0091   1.0000
  14.500   1.3862   0.07906   0.07393  -0.0425   0.0090   1.0000
  14.750   1.3793   0.08326   0.07821  -0.0430   0.0089   1.0000
  15.000   1.3738   0.08699   0.08201  -0.0429   0.0087   1.0000
  15.250   1.3706   0.09016   0.08524  -0.0421   0.0086   1.0000
  15.500   1.3654   0.09463   0.08984  -0.0434   0.0086   1.0000
  15.750   1.3596   0.09946   0.09481  -0.0453   0.0085   1.0000
  16.000   1.3529   0.10457   0.10006  -0.0476   0.0084   1.0000
  16.250   1.3465   0.10966   0.10528  -0.0498   0.0084   1.0000
  16.500   1.3397   0.11490   0.11068  -0.0522   0.0083   1.0000
  16.750   1.3332   0.12009   0.11599  -0.0545   0.0082   1.0000
  17.000   1.3265   0.12541   0.12144  -0.0571   0.0081   1.0000
  17.250   1.3195   0.13079   0.12696  -0.0597   0.0080   1.0000
  17.500   1.3124   0.13630   0.13259  -0.0625   0.0080   1.0000
  17.750   1.3053   0.14190   0.13832  -0.0654   0.0079   1.0000
  18.000   1.2976   0.14778   0.14432  -0.0686   0.0079   1.0000
  18.250   1.2899   0.15379   0.15047  -0.0720   0.0079   1.0000
  18.500   1.2816   0.16009   0.15690  -0.0758   0.0079   1.0000
  18.750   1.2728   0.16664   0.16358  -0.0797   0.0079   1.0000
  19.000   1.2634   0.17355   0.17062  -0.0841   0.0079   1.0000
  19.250   1.2535   0.18085   0.17806  -0.0887   0.0079   1.0000
<< Back to I.S.A. 961 (isa961-il)

Polar data table (+)

Polar graphs


<< Back to I.S.A. 961 (isa961-il)