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I.S.A. 962 (isa962-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: I.S.A. 962 (isa962-il)
Reynolds number: 200,000
Max Cl/Cd: 69.8 at α=2°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-isa962-il-200000-n5.txt
Download as CSV file: xf-isa962-il-200000-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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.3305   0.11088   0.10704  -0.0287   1.0000   0.0394
 -10.500  -0.3325   0.10777   0.10397  -0.0318   1.0000   0.0396
 -10.250  -0.3322   0.10453   0.10077  -0.0341   1.0000   0.0397
 -10.000  -0.3324   0.10139   0.09767  -0.0358   1.0000   0.0398
  -9.750  -0.3232   0.09808   0.09440  -0.0343   1.0000   0.0401
  -9.500  -0.3146   0.09552   0.09187  -0.0331   1.0000   0.0404
  -9.250  -0.3112   0.09330   0.08970  -0.0321   1.0000   0.0408
  -9.000  -0.3141   0.09151   0.08798  -0.0305   1.0000   0.0412
  -8.750  -0.2980   0.08831   0.08479  -0.0337   0.9936   0.0423
  -8.500  -0.2821   0.08477   0.08125  -0.0383   0.9838   0.0439
  -8.250  -0.2617   0.07823   0.07465  -0.0550   0.9657   0.0466
  -8.000  -0.2364   0.07232   0.06865  -0.0655   0.9559   0.0468
  -7.750  -0.2162   0.06756   0.06385  -0.0699   0.9484   0.0471
  -7.500  -0.1976   0.06462   0.06091  -0.0708   0.9419   0.0476
  -7.250  -0.1760   0.06169   0.05795  -0.0730   0.9346   0.0481
  -6.750  -0.1197   0.04686   0.04259  -0.0895   0.9178   0.0395
  -6.500  -0.0984   0.04480   0.04049  -0.0903   0.9101   0.0390
  -6.250  -0.0746   0.04147   0.03701  -0.0925   0.9025   0.0382
  -6.000  -0.0498   0.03713   0.03241  -0.0951   0.8945   0.0372
  -5.750  -0.0245   0.03196   0.02681  -0.0974   0.8863   0.0364
  -5.500   0.0000   0.02730   0.02161  -0.0986   0.8777   0.0360
  -5.250   0.0255   0.02485   0.01878  -0.0988   0.8692   0.0367
  -5.000   0.0507   0.02275   0.01629  -0.0987   0.8592   0.0372
  -4.750   0.0769   0.02095   0.01409  -0.0984   0.8504   0.0373
  -4.500   0.1032   0.01954   0.01236  -0.0981   0.8401   0.0374
  -4.250   0.1300   0.01842   0.01096  -0.0977   0.8307   0.0376
  -4.000   0.1570   0.01749   0.00978  -0.0973   0.8210   0.0379
  -3.750   0.1841   0.01671   0.00882  -0.0969   0.8105   0.0383
  -3.500   0.2114   0.01605   0.00798  -0.0965   0.8008   0.0387
  -3.250   0.2387   0.01548   0.00727  -0.0960   0.7898   0.0392
  -3.000   0.2659   0.01499   0.00667  -0.0956   0.7782   0.0400
  -2.750   0.2928   0.01445   0.00612  -0.0953   0.7673   0.0412
  -2.500   0.3200   0.01407   0.00570  -0.0949   0.7561   0.0423
  -2.250   0.3472   0.01371   0.00529  -0.0945   0.7443   0.0431
  -2.000   0.3745   0.01341   0.00493  -0.0941   0.7325   0.0440
  -1.750   0.4017   0.01315   0.00460  -0.0937   0.7205   0.0450
  -1.500   0.4290   0.01295   0.00434  -0.0933   0.7083   0.0461
  -1.250   0.4562   0.01276   0.00410  -0.0930   0.6960   0.0476
  -1.000   0.4833   0.01260   0.00390  -0.0926   0.6824   0.0500
  -0.750   0.5103   0.01252   0.00375  -0.0922   0.6680   0.0541
  -0.500   0.5373   0.01241   0.00362  -0.0919   0.6539   0.0603
  -0.250   0.5644   0.01228   0.00358  -0.0915   0.6402   0.0816
   0.000   0.5913   0.01217   0.00355  -0.0912   0.6267   0.1288
   0.250   0.6175   0.01194   0.00360  -0.0910   0.6123   0.2290
   0.500   0.6427   0.01157   0.00368  -0.0906   0.5969   0.4059
   1.000   0.7027   0.01059   0.00372  -0.0910   0.5593   1.0000
   1.250   0.7285   0.01078   0.00376  -0.0905   0.5393   1.0000
   1.500   0.7542   0.01099   0.00383  -0.0899   0.5174   1.0000
   1.750   0.7794   0.01123   0.00391  -0.0893   0.4915   1.0000
   2.000   0.8041   0.01152   0.00402  -0.0886   0.4617   1.0000
   2.250   0.8279   0.01188   0.00417  -0.0879   0.4283   1.0000
   2.500   0.8518   0.01225   0.00435  -0.0872   0.4011   1.0000
   2.750   0.8758   0.01262   0.00456  -0.0865   0.3792   1.0000
   3.000   0.8998   0.01300   0.00480  -0.0859   0.3610   1.0000
   3.250   0.9241   0.01336   0.00506  -0.0853   0.3460   1.0000
   3.500   0.9485   0.01371   0.00533  -0.0847   0.3332   1.0000
   3.750   0.9727   0.01407   0.00561  -0.0841   0.3212   1.0000
   4.000   0.9969   0.01442   0.00591  -0.0836   0.3085   1.0000
   4.250   1.0213   0.01476   0.00621  -0.0831   0.2955   1.0000
   4.500   1.0453   0.01511   0.00652  -0.0825   0.2816   1.0000
   4.750   1.0691   0.01547   0.00683  -0.0819   0.2653   1.0000
   5.000   1.0923   0.01586   0.00716  -0.0812   0.2458   1.0000
   5.250   1.1147   0.01631   0.00751  -0.0805   0.2240   1.0000
   5.500   1.1362   0.01683   0.00791  -0.0796   0.2029   1.0000
   5.750   1.1572   0.01740   0.00838  -0.0787   0.1888   1.0000
   6.000   1.1781   0.01795   0.00887  -0.0778   0.1796   1.0000
   6.250   1.1989   0.01850   0.00939  -0.0768   0.1725   1.0000
   6.500   1.2189   0.01909   0.00995  -0.0758   0.1666   1.0000
   6.750   1.2398   0.01959   0.01050  -0.0749   0.1613   1.0000
   7.000   1.2593   0.02018   0.01109  -0.0737   0.1565   1.0000
   7.250   1.2769   0.02089   0.01176  -0.0724   0.1523   1.0000
   7.500   1.2976   0.02135   0.01233  -0.0715   0.1485   1.0000
   7.750   1.3169   0.02190   0.01294  -0.0703   0.1443   1.0000
   8.000   1.3343   0.02254   0.01360  -0.0690   0.1404   1.0000
   8.250   1.3490   0.02333   0.01437  -0.0673   0.1370   1.0000
   8.500   1.3665   0.02385   0.01501  -0.0658   0.1340   1.0000
   8.750   1.3831   0.02442   0.01567  -0.0644   0.1303   1.0000
   9.000   1.3980   0.02509   0.01638  -0.0628   0.1263   1.0000
   9.250   1.4103   0.02593   0.01721  -0.0609   0.1225   1.0000
   9.500   1.4268   0.02654   0.01794  -0.0597   0.1186   1.0000
   9.750   1.4419   0.02724   0.01874  -0.0583   0.1144   1.0000
  10.000   1.4546   0.02809   0.01962  -0.0568   0.1107   1.0000
  10.250   1.4674   0.02899   0.02057  -0.0554   0.1071   1.0000
  10.500   1.4816   0.02982   0.02151  -0.0542   0.1032   1.0000
  10.750   1.4938   0.03080   0.02257  -0.0529   0.0998   1.0000
  11.000   1.5038   0.03196   0.02377  -0.0516   0.0970   1.0000
  11.250   1.5157   0.03304   0.02496  -0.0504   0.0941   1.0000
  11.500   1.5271   0.03417   0.02620  -0.0493   0.0909   1.0000
  11.750   1.5367   0.03547   0.02757  -0.0482   0.0879   1.0000
  12.000   1.5436   0.03701   0.02917  -0.0470   0.0849   1.0000
  12.250   1.5538   0.03834   0.03064  -0.0461   0.0819   1.0000
  12.500   1.5621   0.03987   0.03228  -0.0452   0.0787   1.0000
  12.750   1.5677   0.04168   0.03416  -0.0444   0.0756   1.0000
  13.000   1.5734   0.04354   0.03612  -0.0436   0.0727   1.0000
  13.250   1.5798   0.04539   0.03811  -0.0430   0.0691   1.0000
  13.500   1.5821   0.04771   0.04049  -0.0424   0.0650   1.0000
  13.750   1.5856   0.04995   0.04286  -0.0420   0.0607   1.0000
  14.000   1.5857   0.05265   0.04564  -0.0417   0.0561   1.0000
  14.250   1.5854   0.05548   0.04857  -0.0415   0.0509   1.0000
  14.500   1.5810   0.05888   0.05204  -0.0416   0.0442   1.0000
  14.750   1.5715   0.06308   0.05628  -0.0419   0.0351   1.0000
  15.000   1.5555   0.06835   0.06156  -0.0428   0.0273   1.0000
  15.250   1.5398   0.07381   0.06711  -0.0439   0.0242   1.0000
  15.500   1.5241   0.07952   0.07294  -0.0454   0.0227   1.0000
  15.750   1.5075   0.08560   0.07917  -0.0473   0.0217   1.0000
  16.000   1.4899   0.09207   0.08580  -0.0495   0.0211   1.0000
  16.250   1.4722   0.09882   0.09272  -0.0521   0.0206   1.0000
  16.500   1.4532   0.10602   0.10010  -0.0550   0.0203   1.0000
  16.750   1.4328   0.11365   0.10790  -0.0584   0.0201   1.0000
  17.000   1.4113   0.12167   0.11610  -0.0620   0.0201   1.0000
  17.250   1.3885   0.13016   0.12478  -0.0661   0.0200   1.0000
  17.500   1.3647   0.13910   0.13390  -0.0707   0.0201   1.0000
  17.750   1.3397   0.14859   0.14356  -0.0757   0.0203   1.0000
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