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SARATOV AIRFOIL (saratov-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: SARATOV AIRFOIL (saratov-il)
Reynolds number: 500,000
Max Cl/Cd: 112.25 at α=7.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-saratov-il-500000.txt
Download as CSV file: xf-saratov-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: SARATOV AIRFOIL                                 
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.0116   0.09883   0.09437  -0.0974   0.5762   0.0362
  -9.750  -0.0182   0.09592   0.09148  -0.1008   0.5742   0.0384
  -9.500  -0.0137   0.09315   0.08869  -0.1021   0.5712   0.0385
  -9.250  -0.0038   0.08954   0.08505  -0.1019   0.5680   0.0392
  -9.000   0.0112   0.08799   0.08346  -0.1016   0.5650   0.0399
  -8.750   0.0234   0.08636   0.08183  -0.1019   0.5629   0.0407
  -8.500   0.0331   0.08444   0.07990  -0.1025   0.5606   0.0418
  -8.250   0.0408   0.08232   0.07778  -0.1033   0.5587   0.0440
  -8.000   0.0329   0.07993   0.07543  -0.1060   0.5575   0.0461
  -7.750   0.0348   0.07758   0.07309  -0.1065   0.5559   0.0463
  -7.500   0.0372   0.07377   0.06928  -0.1063   0.5542   0.0472
  -7.250   0.0515   0.07250   0.06797  -0.1057   0.5523   0.0478
  -7.000   0.0633   0.07107   0.06651  -0.1057   0.5505   0.0485
  -6.750   0.0759   0.06951   0.06494  -0.1063   0.5490   0.0495
  -6.500   0.0880   0.06767   0.06312  -0.1074   0.5479   0.0513
  -6.250   0.0901   0.02569   0.02019  -0.1683   0.5487   0.0467
  -6.000   0.1231   0.02177   0.01592  -0.1740   0.5474   0.0480
  -5.750   0.1522   0.02044   0.01444  -0.1756   0.5459   0.0490
  -5.500   0.1814   0.01930   0.01316  -0.1770   0.5444   0.0501
  -5.250   0.2105   0.01827   0.01197  -0.1782   0.5428   0.0513
  -5.000   0.2394   0.01741   0.01096  -0.1791   0.5412   0.0526
  -4.750   0.2681   0.01670   0.01010  -0.1798   0.5398   0.0541
  -4.500   0.2967   0.01612   0.00937  -0.1803   0.5384   0.0551
  -4.250   0.3251   0.01559   0.00869  -0.1807   0.5372   0.0562
  -4.000   0.3531   0.01519   0.00820  -0.1808   0.5360   0.0585
  -3.750   0.3815   0.01485   0.00778  -0.1811   0.5347   0.0607
  -3.500   0.4101   0.01454   0.00737  -0.1814   0.5334   0.0631
  -3.250   0.4386   0.01420   0.00693  -0.1817   0.5326   0.0656
  -3.000   0.4672   0.01381   0.00647  -0.1819   0.5319   0.0693
  -2.750   0.4958   0.01328   0.00588  -0.1823   0.5312   0.0748
  -2.500   0.5243   0.01268   0.00525  -0.1827   0.5304   0.0886
  -2.250   0.5524   0.01242   0.00508  -0.1829   0.5296   0.1290
  -2.000   0.5807   0.01266   0.00530  -0.1828   0.5289   0.1397
  -1.750   0.6086   0.01290   0.00559  -0.1826   0.5281   0.1454
  -1.500   0.6366   0.01318   0.00589  -0.1824   0.5273   0.1505
  -1.250   0.6647   0.01334   0.00600  -0.1823   0.5266   0.1538
  -1.000   0.6925   0.01331   0.00593  -0.1823   0.5259   0.1571
  -0.750   0.7202   0.01348   0.00615  -0.1821   0.5253   0.1604
  -0.500   0.7480   0.01362   0.00631  -0.1820   0.5246   0.1636
  -0.250   0.7759   0.01364   0.00630  -0.1820   0.5240   0.1658
   0.000   0.8038   0.01368   0.00630  -0.1819   0.5234   0.1680
   0.250   0.8318   0.01378   0.00636  -0.1818   0.5228   0.1698
   0.500   0.8595   0.01362   0.00616  -0.1819   0.5223   0.1723
   0.750   0.8872   0.01362   0.00618  -0.1818   0.5214   0.1748
   1.000   0.9147   0.01368   0.00624  -0.1817   0.5198   0.1772
   1.250   0.9424   0.01382   0.00634  -0.1816   0.5178   0.1799
   1.500   0.9701   0.01401   0.00651  -0.1816   0.5164   0.1817
   1.750   0.9975   0.01396   0.00647  -0.1815   0.5158   0.1829
   2.000   1.0248   0.01390   0.00644  -0.1813   0.5149   0.1840
   2.250   1.0518   0.01387   0.00642  -0.1811   0.5138   0.1850
   2.500   1.0789   0.01387   0.00645  -0.1809   0.5126   0.1859
   2.750   1.1059   0.01379   0.00640  -0.1807   0.5113   0.1877
   3.000   1.1329   0.01377   0.00644  -0.1805   0.5102   0.1899
   3.250   1.1599   0.01378   0.00650  -0.1803   0.5088   0.1920
   3.500   1.1868   0.01380   0.00655  -0.1801   0.5072   0.1943
   3.750   1.2138   0.01384   0.00663  -0.1799   0.5058   0.1969
   4.000   1.2409   0.01390   0.00672  -0.1797   0.5046   0.1995
   4.250   1.2681   0.01399   0.00682  -0.1795   0.5033   0.2018
   4.500   1.2953   0.01409   0.00697  -0.1794   0.5015   0.2062
   4.750   1.3220   0.01431   0.00725  -0.1793   0.4995   0.2111
   5.000   1.3474   0.01424   0.00729  -0.1787   0.4978   0.2160
   5.250   1.3729   0.01420   0.00737  -0.1782   0.4956   0.2221
   5.500   1.3986   0.01419   0.00748  -0.1778   0.4932   0.2305
   5.750   1.4238   0.01407   0.00745  -0.1772   0.4892   0.2425
   6.000   1.4496   0.01415   0.00753  -0.1766   0.4835   0.2595
   6.250   1.4721   0.01406   0.00765  -0.1754   0.4787   0.2737
   6.750   1.5180   0.01401   0.00770  -0.1732   0.4654   0.2953
   7.000   1.5395   0.01390   0.00765  -0.1718   0.4550   0.3064
   7.250   1.5602   0.01390   0.00773  -0.1703   0.4384   0.3087
   7.500   1.5537   0.01519   0.00839  -0.1643   0.3155   0.3107
   7.750   1.5235   0.01794   0.01051  -0.1548   0.1994   0.3113
   8.000   1.5186   0.01931   0.01172  -0.1495   0.1706   0.3145
   8.250   1.5225   0.02031   0.01267  -0.1458   0.1583   0.3210
   8.500   1.5305   0.02114   0.01356  -0.1429   0.1503   0.3228
   8.750   1.5353   0.02217   0.01461  -0.1397   0.1423   0.3251
   9.000   1.5438   0.02307   0.01556  -0.1371   0.1352   0.3290
   9.250   1.5483   0.02425   0.01673  -0.1342   0.1268   0.3348
   9.500   1.5551   0.02534   0.01787  -0.1318   0.1177   0.3365
   9.750   1.5572   0.02682   0.01936  -0.1291   0.1057   0.3387
  10.000   1.5525   0.02894   0.02140  -0.1261   0.0859   0.3410
  10.250   1.5376   0.03216   0.02450  -0.1228   0.0612   0.3428
  10.500   1.5199   0.03610   0.02835  -0.1201   0.0423   0.3446
  10.750   1.5086   0.03984   0.03207  -0.1182   0.0333   0.3479
  11.000   1.5031   0.04306   0.03535  -0.1168   0.0292   0.3491
  11.250   1.5003   0.04611   0.03847  -0.1156   0.0267   0.3511
  11.500   1.5005   0.04888   0.04132  -0.1146   0.0251   0.3543
  11.750   1.4995   0.05184   0.04433  -0.1137   0.0236   0.3576
  12.000   1.4962   0.05510   0.04764  -0.1127   0.0223   0.3610
  12.250   1.4987   0.05768   0.05031  -0.1119   0.0216   0.3631
  12.500   1.5019   0.06023   0.05294  -0.1112   0.0208   0.3660
  12.750   1.5049   0.06284   0.05561  -0.1105   0.0201   0.3694
  13.000   1.5079   0.06551   0.05833  -0.1099   0.0195   0.3729
  13.250   1.5107   0.06814   0.06104  -0.1093   0.0188   0.3767
  13.500   1.5109   0.07121   0.06415  -0.1088   0.0182   0.3813
  13.750   1.5093   0.07447   0.06748  -0.1082   0.0176   0.3868
  14.000   1.5159   0.07677   0.06984  -0.1077   0.0173   0.3943
  14.250   1.5232   0.07896   0.07213  -0.1074   0.0167   0.4011
  14.500   1.5290   0.08141   0.07464  -0.1070   0.0162   0.4044
  14.750   1.5346   0.08389   0.07718  -0.1066   0.0158   0.4053
  15.000   1.5406   0.08632   0.07968  -0.1063   0.0154   0.4053
  15.250   1.5463   0.08877   0.08217  -0.1060   0.0150   0.4054
  15.500   1.5515   0.09128   0.08472  -0.1057   0.0146   0.4054
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