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S4022 (s4022-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: S4022 (s4022-il)
Reynolds number: 100,000
Max Cl/Cd: 64.68 at α=7.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s4022-il-100000.txt
Download as CSV file: xf-s4022-il-100000.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 =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.500  -0.4121   0.10349   0.09935  -0.0276   1.0000   0.0984
  -7.250  -0.4408   0.10289   0.09887  -0.0260   1.0000   0.0990
  -7.000  -0.4653   0.10124   0.09733  -0.0280   1.0000   0.0995
  -6.750  -0.4708   0.09734   0.09351  -0.0273   1.0000   0.1006
  -6.500  -0.4539   0.09512   0.09126  -0.0196   1.0000   0.1041
  -6.250  -0.4593   0.09298   0.08918  -0.0185   1.0000   0.1070
  -6.000  -0.4688   0.09017   0.08643  -0.0206   1.0000   0.1107
  -5.750  -0.4779   0.08310   0.07933  -0.0352   1.0000   0.1149
  -5.500  -0.4713   0.08215   0.07847  -0.0272   0.9994   0.1174
  -5.250  -0.4376   0.07438   0.07053  -0.0436   0.9923   0.1299
  -5.000  -0.4136   0.07186   0.06803  -0.0439   0.9868   0.1380
  -4.750  -0.3782   0.06501   0.06093  -0.0577   0.9802   0.1583
  -4.500  -0.3536   0.06239   0.05830  -0.0587   0.9747   0.1745
  -4.250  -0.3226   0.05874   0.05452  -0.0645   0.9686   0.2018
  -4.000  -0.2128   0.03999   0.03344  -0.0912   0.9692   0.0881
  -3.750  -0.1638   0.03596   0.02848  -0.0951   0.9653   0.0708
  -3.500  -0.1185   0.03302   0.02511  -0.0989   0.9618   0.0672
  -3.250  -0.0800   0.03110   0.02275  -0.1010   0.9567   0.0653
  -3.000  -0.0417   0.02968   0.02104  -0.1030   0.9515   0.0655
  -2.750   0.0022   0.02877   0.01989  -0.1058   0.9477   0.0698
  -2.500   0.0311   0.02782   0.01895  -0.1064   0.9405   0.0752
  -2.250   0.0725   0.02705   0.01822  -0.1090   0.9359   0.0820
  -2.000   0.1080   0.02640   0.01758  -0.1108   0.9297   0.0953
  -1.750   0.1511   0.02422   0.01751  -0.1145   0.9259   0.5769
  -1.500   0.1805   0.02478   0.01830  -0.1130   0.9206   0.6963
  -1.250   0.1907   0.02513   0.01876  -0.1084   0.9106   0.7511
  -1.000   0.2051   0.02535   0.01901  -0.1045   0.9027   0.7965
  -0.750   0.2289   0.02535   0.01892  -0.1030   0.8954   0.8268
  -0.500   0.2461   0.02537   0.01888  -0.1006   0.8866   0.8540
  -0.250   0.2735   0.02518   0.01861  -0.0999   0.8805   0.8835
   0.000   0.2879   0.02509   0.01849  -0.0974   0.8707   0.9137
   0.250   0.3284   0.02470   0.01803  -0.0994   0.8659   0.9572
   0.500   0.3648   0.02486   0.01808  -0.1025   0.8558   1.0000
   0.750   0.4196   0.02482   0.01787  -0.1081   0.8520   1.0000
   1.000   0.4529   0.02518   0.01812  -0.1105   0.8420   1.0000
   1.250   0.5057   0.02501   0.01784  -0.1154   0.8382   1.0000
   1.500   0.5371   0.02537   0.01812  -0.1171   0.8280   1.0000
   1.750   0.5885   0.02505   0.01773  -0.1213   0.8243   1.0000
   2.000   0.6175   0.02540   0.01803  -0.1223   0.8138   1.0000
   2.250   0.6687   0.02488   0.01748  -0.1261   0.8104   1.0000
   2.500   0.6965   0.02517   0.01775  -0.1265   0.7998   1.0000
   2.750   0.7490   0.02443   0.01700  -0.1303   0.7966   1.0000
   3.000   0.7767   0.02465   0.01724  -0.1305   0.7860   1.0000
   3.250   0.8318   0.02380   0.01643  -0.1346   0.7826   1.0000
   3.500   0.8606   0.02390   0.01656  -0.1348   0.7718   1.0000
   3.750   0.9158   0.02294   0.01568  -0.1387   0.7678   1.0000
   4.000   0.9446   0.02294   0.01574  -0.1387   0.7563   1.0000
   4.250   0.9790   0.02271   0.01556  -0.1394   0.7458   1.0000
   4.500   1.0319   0.02174   0.01470  -0.1429   0.7392   1.0000
   4.750   1.0625   0.02159   0.01462  -0.1429   0.7264   1.0000
   5.000   1.0952   0.02133   0.01443  -0.1431   0.7131   1.0000
   5.250   1.1289   0.02100   0.01417  -0.1434   0.6991   1.0000
   5.500   1.1627   0.02068   0.01390  -0.1438   0.6841   1.0000
   5.750   1.1964   0.02035   0.01367  -0.1440   0.6681   1.0000
   6.000   1.2181   0.02040   0.01381  -0.1424   0.6484   1.0000
   6.250   1.2466   0.02020   0.01365  -0.1417   0.6283   1.0000
   6.500   1.2700   0.02020   0.01369  -0.1403   0.6061   1.0000
   6.750   1.2953   0.02017   0.01365  -0.1391   0.5826   1.0000
   7.000   1.3143   0.02034   0.01391  -0.1370   0.5565   1.0000
   7.250   1.3317   0.02059   0.01418  -0.1346   0.5285   1.0000
   7.500   1.3477   0.02092   0.01448  -0.1321   0.4982   1.0000
   7.750   1.3592   0.02140   0.01497  -0.1288   0.4648   1.0000
   8.000   1.3687   0.02201   0.01549  -0.1253   0.4285   1.0000
   8.250   1.3739   0.02279   0.01617  -0.1212   0.3891   1.0000
   8.500   1.3743   0.02377   0.01698  -0.1164   0.3473   1.0000
   8.750   1.3722   0.02505   0.01808  -0.1116   0.3037   1.0000
   9.000   1.3690   0.02665   0.01940  -0.1069   0.2618   1.0000
   9.250   1.3663   0.02850   0.02098  -0.1027   0.2254   1.0000
   9.500   1.3654   0.03046   0.02273  -0.0989   0.1948   1.0000
   9.750   1.3663   0.03245   0.02454  -0.0957   0.1701   1.0000
  10.000   1.3679   0.03440   0.02637  -0.0928   0.1493   1.0000
  10.250   1.3688   0.03636   0.02828  -0.0901   0.1300   1.0000
  10.500   1.3688   0.03833   0.03025  -0.0876   0.1122   1.0000
  10.750   1.3688   0.04058   0.03247  -0.0853   0.0970   1.0000
  11.000   1.3675   0.04320   0.03502  -0.0830   0.0825   1.0000
  11.250   1.3669   0.04625   0.03805  -0.0806   0.0676   1.0000
  11.500   1.3727   0.04934   0.04108  -0.0787   0.0562   1.0000
  11.750   1.3809   0.05189   0.04380  -0.0770   0.0493   1.0000
  12.000   1.3946   0.05479   0.04679  -0.0759   0.0440   1.0000
  12.250   1.4053   0.05747   0.04975  -0.0746   0.0405   1.0000
  12.500   1.4185   0.06038   0.05282  -0.0735   0.0381   1.0000
  12.750   1.4383   0.06415   0.05670  -0.0730   0.0361   1.0000
  13.000   1.4476   0.06970   0.06259  -0.0722   0.0352   1.0000
  13.250   1.4398   0.07381   0.06707  -0.0705   0.0350   1.0000
  13.500   1.4288   0.07829   0.07191  -0.0692   0.0349   1.0000
  13.750   1.4145   0.08310   0.07705  -0.0684   0.0349   1.0000
  14.000   1.3986   0.08822   0.08248  -0.0681   0.0349   1.0000
  14.250   1.3806   0.09368   0.08823  -0.0685   0.0349   1.0000
  14.500   1.3612   0.09953   0.09436  -0.0695   0.0350   1.0000
  14.750   1.3414   0.10580   0.10088  -0.0713   0.0351   1.0000
  15.000   1.3215   0.11246   0.10776  -0.0739   0.0352   1.0000
  15.250   1.0587   0.12696   0.12362  -0.0787   0.0409   1.0000
  15.500   1.0182   0.13864   0.13546  -0.0867   0.0429   1.0000
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