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S1091 (s1091-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: S1091 (s1091-il)
Reynolds number: 200,000
Max Cl/Cd: 90.71 at α=3.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s1091-il-200000-n5.txt
Download as CSV file: xf-s1091-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S1091                                           
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -7.000  -0.2909   0.09835   0.09501  -0.0162   1.0000   0.0115
  -6.750  -0.2943   0.09679   0.09349  -0.0145   1.0000   0.0115
  -6.500  -0.2988   0.09520   0.09197  -0.0125   1.0000   0.0117
  -6.250  -0.2751   0.09139   0.08816  -0.0180   0.9960   0.0120
  -6.000  -0.2505   0.08750   0.08428  -0.0235   0.9913   0.0123
  -5.750  -0.2246   0.08370   0.08047  -0.0294   0.9865   0.0128
  -5.500  -0.1988   0.07992   0.07669  -0.0352   0.9813   0.0136
  -5.250  -0.1697   0.07610   0.07286  -0.0418   0.9753   0.0144
  -5.000  -0.1191   0.07243   0.06913  -0.0564   0.9674   0.0154
  -4.750  -0.1085   0.06806   0.06481  -0.0554   0.9624   0.0164
  -4.500  -0.0808   0.06465   0.06139  -0.0599   0.9568   0.0175
  -4.250  -0.0505   0.06116   0.05786  -0.0652   0.9490   0.0187
  -4.000  -0.0156   0.05755   0.05421  -0.0714   0.9416   0.0200
  -3.750   0.0421   0.05362   0.05015  -0.0834   0.9350   0.0218
  -3.500   0.0856   0.04995   0.04640  -0.0905   0.9274   0.0221
  -3.250   0.1160   0.04516   0.04158  -0.0950   0.9213   0.0229
  -3.000   0.1442   0.04238   0.03877  -0.0975   0.9131   0.0241
  -2.750   0.1860   0.03914   0.03544  -0.1030   0.9075   0.0258
  -2.500   0.2325   0.03559   0.03175  -0.1093   0.9002   0.0278
  -2.250   0.2978   0.02873   0.02447  -0.1188   0.8950   0.0151
  -2.000   0.3447   0.02486   0.02034  -0.1242   0.8877   0.0138
  -1.750   0.3948   0.02019   0.01513  -0.1293   0.8799   0.0128
  -1.500   0.4396   0.01666   0.01090  -0.1325   0.8698   0.0129
  -1.250   0.4811   0.01505   0.00865  -0.1347   0.8570   0.0155
  -1.000   0.5189   0.01342   0.00665  -0.1366   0.8417   0.0176
  -0.750   0.5537   0.01244   0.00538  -0.1375   0.8252   0.0191
  -0.500   0.5857   0.01193   0.00465  -0.1379   0.8085   0.0220
  -0.250   0.6155   0.01134   0.00393  -0.1379   0.7925   0.0255
   0.000   0.6440   0.01108   0.00351  -0.1377   0.7767   0.0288
   0.250   0.6715   0.01088   0.00321  -0.1373   0.7614   0.0376
   0.500   0.6986   0.01065   0.00304  -0.1368   0.7468   0.0843
   0.750   0.7249   0.01051   0.00306  -0.1364   0.7325   0.1717
   1.000   0.7509   0.01038   0.00313  -0.1359   0.7183   0.2756
   1.250   0.7758   0.01027   0.00322  -0.1351   0.7041   0.3905
   1.500   0.8011   0.01020   0.00325  -0.1344   0.6892   0.4958
   2.000   0.8566   0.00971   0.00321  -0.1338   0.6562   1.0000
   2.250   0.8816   0.00989   0.00325  -0.1329   0.6380   1.0000
   2.500   0.9062   0.01010   0.00331  -0.1320   0.6181   1.0000
   2.750   0.9305   0.01030   0.00340  -0.1311   0.5955   1.0000
   3.000   0.9545   0.01053   0.00351  -0.1301   0.5704   1.0000
   3.250   0.9779   0.01078   0.00362  -0.1290   0.5408   1.0000
   3.500   1.0004   0.01110   0.00374  -0.1277   0.5038   1.0000
   3.750   1.0221   0.01149   0.00391  -0.1264   0.4646   1.0000
   4.000   1.0436   0.01193   0.00413  -0.1250   0.4270   1.0000
   4.500   1.0865   0.01291   0.00474  -0.1225   0.3550   1.0000
   4.750   1.1082   0.01340   0.00507  -0.1214   0.3234   1.0000
   5.000   1.1299   0.01390   0.00542  -0.1203   0.2928   1.0000
   5.250   1.1514   0.01443   0.00579  -0.1192   0.2627   1.0000
   5.500   1.1728   0.01498   0.00624  -0.1180   0.2323   1.0000
   5.750   1.1939   0.01555   0.00668  -0.1169   0.2037   1.0000
   6.000   1.2151   0.01613   0.00715  -0.1158   0.1795   1.0000
   6.250   1.2363   0.01670   0.00764  -0.1147   0.1591   1.0000
   6.500   1.2572   0.01730   0.00820  -0.1135   0.1413   1.0000
   6.750   1.2779   0.01790   0.00877  -0.1124   0.1266   1.0000
   7.000   1.2986   0.01850   0.00935  -0.1112   0.1146   1.0000
   7.250   1.3188   0.01913   0.00998  -0.1099   0.1045   1.0000
   7.500   1.3383   0.01982   0.01064  -0.1086   0.0961   1.0000
   7.750   1.3584   0.02041   0.01133  -0.1074   0.0893   1.0000
   8.000   1.3767   0.02117   0.01210  -0.1059   0.0840   1.0000
   8.250   1.3960   0.02181   0.01284  -0.1045   0.0803   1.0000
   8.500   1.4145   0.02251   0.01363  -0.1030   0.0767   1.0000
   8.750   1.4315   0.02331   0.01449  -0.1013   0.0737   1.0000
   9.000   1.4464   0.02429   0.01553  -0.0994   0.0711   1.0000
   9.250   1.4636   0.02506   0.01644  -0.0977   0.0693   1.0000
   9.500   1.4798   0.02589   0.01742  -0.0959   0.0674   1.0000
   9.750   1.4949   0.02674   0.01840  -0.0940   0.0654   1.0000
  10.000   1.5087   0.02760   0.01937  -0.0919   0.0633   1.0000
  10.250   1.5208   0.02859   0.02047  -0.0897   0.0615   1.0000
  10.500   1.5311   0.02983   0.02178  -0.0872   0.0599   1.0000
  10.750   1.5430   0.03096   0.02306  -0.0851   0.0585   1.0000
  11.000   1.5560   0.03176   0.02407  -0.0831   0.0562   1.0000
  11.250   1.5680   0.03245   0.02492  -0.0811   0.0526   1.0000
  11.500   1.5770   0.03339   0.02593  -0.0790   0.0495   1.0000
  11.750   1.5864   0.03446   0.02715  -0.0770   0.0465   1.0000
  12.000   1.5988   0.03528   0.02818  -0.0754   0.0430   1.0000
  12.500   1.6240   0.03692   0.02994  -0.0729   0.0249   1.0000
  12.750   1.6206   0.03945   0.03230  -0.0706   0.0109   1.0000
  13.000   1.6119   0.04270   0.03562  -0.0682   0.0057   1.0000
  13.250   1.6048   0.04593   0.03901  -0.0664   0.0038   1.0000
  13.500   1.5989   0.04919   0.04248  -0.0650   0.0030   1.0000
  13.750   1.5901   0.05303   0.04652  -0.0642   0.0025   1.0000
  14.000   1.5830   0.05680   0.05051  -0.0638   0.0024   1.0000
  14.250   1.5739   0.06107   0.05502  -0.0639   0.0022   1.0000
  14.500   1.5637   0.06572   0.05991  -0.0645   0.0021   1.0000
  14.750   1.5516   0.07090   0.06532  -0.0657   0.0020   1.0000
  15.000   1.5371   0.07682   0.07147  -0.0676   0.0019   1.0000
  15.250   1.5218   0.08323   0.07810  -0.0701   0.0019   1.0000
  15.500   1.5034   0.09067   0.08577  -0.0735   0.0019   1.0000
  15.750   1.4844   0.09874   0.09406  -0.0776   0.0019   1.0000
  16.000   1.4627   0.10792   0.10346  -0.0826   0.0019   1.0000
  16.250   1.4401   0.11778   0.11353  -0.0882   0.0021   1.0000
  16.500   1.4145   0.12887   0.12482  -0.0947   0.0022   1.0000
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