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S4022 (s4022-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: S4022 (s4022-il)
Reynolds number: 1,000,000
Max Cl/Cd: 148.3 at α=3.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s4022-il-1000000.txt
Download as CSV file: xf-s4022-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S4022                                           
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.2255   0.08341   0.08176  -0.0790   0.9851   0.0111
  -8.750  -0.2136   0.07772   0.07607  -0.0849   0.9841   0.0111
  -8.500  -0.2108   0.07283   0.07119  -0.0879   0.9782   0.0111
  -8.250  -0.2255   0.05734   0.05574  -0.1041   0.9731   0.0116
  -8.000  -0.2276   0.03912   0.03718  -0.1306   0.9613   0.0117
  -7.750  -0.2175   0.03443   0.03227  -0.1351   0.9532   0.0120
  -7.500  -0.1912   0.03204   0.02974  -0.1390   0.9504   0.0123
  -7.250  -0.1605   0.03013   0.02770  -0.1430   0.9485   0.0130
  -7.000  -0.1358   0.02724   0.02458  -0.1456   0.9426   0.0138
  -6.750  -0.1031   0.02516   0.02227  -0.1483   0.9385   0.0157
  -6.500  -0.0623   0.02485   0.02172  -0.1514   0.9363   0.0166
  -6.250  -0.0309   0.01772   0.01391  -0.1572   0.9310   0.0180
  -6.000   0.0018   0.01643   0.01252  -0.1592   0.9252   0.0190
  -5.750   0.0406   0.01414   0.00986  -0.1614   0.9211   0.0160
  -5.500   0.0700   0.01303   0.00859  -0.1621   0.9132   0.0162
  -5.250   0.1042   0.01191   0.00729  -0.1638   0.9072   0.0162
  -5.000   0.1320   0.01098   0.00624  -0.1640   0.8985   0.0161
  -4.750   0.1626   0.01021   0.00536  -0.1648   0.8912   0.0161
  -4.500   0.1909   0.00979   0.00486  -0.1650   0.8826   0.0164
  -4.250   0.2193   0.00914   0.00412  -0.1654   0.8746   0.0163
  -4.000   0.2483   0.00860   0.00348  -0.1658   0.8665   0.0163
  -3.750   0.2763   0.00821   0.00302  -0.1659   0.8581   0.0164
  -3.500   0.3055   0.00781   0.00249  -0.1663   0.8504   0.0172
  -3.250   0.3336   0.00748   0.00206  -0.1665   0.8419   0.0188
  -3.000   0.3619   0.00734   0.00185  -0.1666   0.8342   0.0202
  -2.750   0.3898   0.00723   0.00169  -0.1666   0.8261   0.0213
  -2.500   0.4177   0.00715   0.00155  -0.1667   0.8184   0.0225
  -2.250   0.4455   0.00709   0.00144  -0.1667   0.8106   0.0272
  -2.000   0.4747   0.00655   0.00130  -0.1674   0.8030   0.1639
  -1.750   0.5040   0.00601   0.00122  -0.1684   0.7955   0.3379
  -1.500   0.5326   0.00569   0.00122  -0.1689   0.7877   0.4604
  -1.250   0.5605   0.00561   0.00126  -0.1690   0.7801   0.5279
  -1.000   0.5880   0.00561   0.00129  -0.1689   0.7719   0.5564
  -0.750   0.6154   0.00563   0.00131  -0.1688   0.7641   0.5791
  -0.500   0.6427   0.00567   0.00135  -0.1687   0.7556   0.5990
  -0.250   0.6699   0.00571   0.00139  -0.1685   0.7473   0.6180
   0.000   0.6968   0.00577   0.00143  -0.1683   0.7387   0.6279
   0.250   0.7240   0.00581   0.00146  -0.1681   0.7295   0.6363
   0.500   0.7509   0.00587   0.00149  -0.1679   0.7204   0.6448
   1.250   0.8306   0.00607   0.00164  -0.1671   0.6889   0.6686
   1.500   0.8569   0.00616   0.00169  -0.1668   0.6774   0.6763
   1.750   0.8829   0.00624   0.00177  -0.1664   0.6657   0.6839
   2.000   0.9088   0.00634   0.00184  -0.1660   0.6532   0.6918
   2.250   0.9344   0.00645   0.00193  -0.1656   0.6389   0.7002
   2.500   0.9597   0.00656   0.00202  -0.1651   0.6234   0.7086
   2.750   0.9851   0.00670   0.00213  -0.1646   0.6081   0.7181
   3.000   1.0103   0.00682   0.00224  -0.1641   0.5926   0.7275
   3.250   1.0351   0.00698   0.00237  -0.1635   0.5756   0.7375
   3.500   1.0594   0.00716   0.00250  -0.1629   0.5569   0.7484
   3.750   1.0837   0.00734   0.00267  -0.1622   0.5383   0.7604
   4.000   1.1076   0.00754   0.00283  -0.1615   0.5171   0.7732
   4.250   1.1311   0.00776   0.00301  -0.1606   0.4959   0.7875
   4.500   1.1543   0.00799   0.00320  -0.1598   0.4729   0.8035
   4.750   1.1769   0.00824   0.00342  -0.1588   0.4489   0.8215
   5.000   1.1985   0.00853   0.00366  -0.1577   0.4216   0.8432
   5.250   1.2178   0.00890   0.00395  -0.1561   0.3867   0.8702
   5.500   1.2337   0.00925   0.00423  -0.1537   0.3507   0.9133
   5.750   1.2501   0.00957   0.00447  -0.1514   0.3186   1.0000
   6.000   1.2698   0.01011   0.00483  -0.1501   0.2824   1.0000
   6.250   1.2880   0.01074   0.00525  -0.1485   0.2419   1.0000
   6.500   1.3055   0.01140   0.00569  -0.1468   0.2032   1.0000
   6.750   1.3210   0.01210   0.00619  -0.1447   0.1641   1.0000
   7.000   1.3369   0.01273   0.00665  -0.1427   0.1353   1.0000
   7.250   1.3536   0.01330   0.00711  -0.1407   0.1123   1.0000
   7.500   1.3696   0.01388   0.00758  -0.1387   0.0928   1.0000
   7.750   1.3862   0.01444   0.00806  -0.1369   0.0767   1.0000
   8.000   1.4017   0.01507   0.00859  -0.1348   0.0607   1.0000
   8.250   1.4177   0.01565   0.00913  -0.1329   0.0492   1.0000
   8.500   1.4324   0.01630   0.00972  -0.1308   0.0375   1.0000
   8.750   1.4453   0.01709   0.01042  -0.1284   0.0234   1.0000
   9.000   1.4537   0.01815   0.01137  -0.1253   0.0107   1.0000
   9.250   1.4668   0.01894   0.01219  -0.1229   0.0082   1.0000
   9.500   1.4818   0.01959   0.01291  -0.1210   0.0076   1.0000
   9.750   1.4958   0.02032   0.01370  -0.1190   0.0071   1.0000
  10.000   1.5085   0.02114   0.01457  -0.1168   0.0065   1.0000
  10.250   1.5195   0.02210   0.01561  -0.1145   0.0060   1.0000
  10.500   1.5278   0.02327   0.01688  -0.1118   0.0055   1.0000
  10.750   1.5346   0.02459   0.01831  -0.1091   0.0052   1.0000
  11.000   1.5459   0.02558   0.01937  -0.1071   0.0051   1.0000
  11.250   1.5558   0.02670   0.02057  -0.1050   0.0049   1.0000
  11.500   1.5650   0.02791   0.02185  -0.1030   0.0047   1.0000
  11.750   1.5727   0.02926   0.02329  -0.1009   0.0045   1.0000
  12.000   1.5795   0.03075   0.02487  -0.0988   0.0044   1.0000
  12.250   1.5856   0.03233   0.02654  -0.0968   0.0042   1.0000
  12.500   1.5907   0.03405   0.02835  -0.0949   0.0040   1.0000
  12.750   1.5948   0.03593   0.03032  -0.0931   0.0039   1.0000
  13.000   1.5978   0.03798   0.03249  -0.0913   0.0037   1.0000
  13.250   1.5990   0.04028   0.03489  -0.0896   0.0036   1.0000
  13.500   1.5975   0.04296   0.03768  -0.0880   0.0035   1.0000
  13.750   1.5938   0.04603   0.04087  -0.0865   0.0034   1.0000
  14.000   1.5856   0.04975   0.04474  -0.0852   0.0033   1.0000
  14.250   1.5738   0.05414   0.04930  -0.0841   0.0032   1.0000
  14.500   1.5597   0.05909   0.05443  -0.0834   0.0031   1.0000
  14.750   1.5499   0.06371   0.05921  -0.0831   0.0031   1.0000
  15.000   1.5504   0.06706   0.06268  -0.0833   0.0030   1.0000
  15.250   1.5497   0.07069   0.06641  -0.0836   0.0030   1.0000
  15.500   1.5475   0.07465   0.07050  -0.0842   0.0030   1.0000
  15.750   1.5445   0.07886   0.07484  -0.0850   0.0029   1.0000
  16.000   1.5385   0.08371   0.07982  -0.0861   0.0029   1.0000
  16.250   1.5332   0.08859   0.08483  -0.0875   0.0028   1.0000
  16.500   1.5246   0.09417   0.09056  -0.0893   0.0028   1.0000
  16.750   1.5165   0.09981   0.09633  -0.0914   0.0028   1.0000
  17.000   1.5074   0.10579   0.10245  -0.0938   0.0027   1.0000
  17.250   1.4968   0.11221   0.10902  -0.0966   0.0027   1.0000
  17.500   1.4873   0.11859   0.11553  -0.0996   0.0027   1.0000
  17.750   1.4767   0.12526   0.12235  -0.1030   0.0026   1.0000
  18.000   1.4650   0.13230   0.12953  -0.1067   0.0026   1.0000
  18.250   1.4531   0.13952   0.13689  -0.1108   0.0026   1.0000
  18.500   1.4425   0.14665   0.14416  -0.1150   0.0026   1.0000
  18.750   1.4303   0.15423   0.15187  -0.1197   0.0026   1.0000
  19.000   1.4191   0.16172   0.15949  -0.1245   0.0026   1.0000
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