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S4083 (8%) (s4083-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: S4083 (8%) (s4083-il)
Reynolds number: 50,000
Max Cl/Cd: 38.5 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s4083-il-50000-n5.txt
Download as CSV file: xf-s4083-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S4083 (8%)                                      
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.500  -0.3741   0.09834   0.09169  -0.0179   1.0000   0.1058
  -7.250  -0.3866   0.09710   0.09062  -0.0207   1.0000   0.1099
  -7.000  -0.3897   0.09468   0.08835  -0.0260   1.0000   0.1108
  -6.750  -0.3786   0.09015   0.08385  -0.0228   1.0000   0.1122
  -6.500  -0.3709   0.08664   0.08040  -0.0223   1.0000   0.1137
  -6.000  -0.3483   0.07389   0.06756  -0.0368   1.0000   0.0562
  -5.750  -0.3399   0.07110   0.06480  -0.0338   1.0000   0.0520
  -5.500  -0.3289   0.06701   0.06072  -0.0360   1.0000   0.0493
  -5.000  -0.2900   0.05551   0.04878  -0.0467   1.0000   0.0421
  -4.750  -0.2738   0.05181   0.04500  -0.0479   1.0000   0.0414
  -4.500  -0.2543   0.04786   0.04085  -0.0497   1.0000   0.0408
  -4.250  -0.2319   0.04387   0.03654  -0.0518   1.0000   0.0408
  -4.000  -0.2073   0.04010   0.03232  -0.0536   1.0000   0.0415
  -3.750  -0.1816   0.03684   0.02851  -0.0547   1.0000   0.0424
  -3.500  -0.1571   0.03391   0.02513  -0.0552   1.0000   0.0432
  -3.250  -0.1329   0.03133   0.02220  -0.0554   1.0000   0.0439
  -3.000  -0.1082   0.02912   0.01964  -0.0552   1.0000   0.0446
  -2.750  -0.0838   0.02728   0.01749  -0.0548   1.0000   0.0459
  -2.500  -0.0596   0.02575   0.01569  -0.0542   1.0000   0.0478
  -2.250  -0.0357   0.02451   0.01419  -0.0534   1.0000   0.0517
  -2.000  -0.0105   0.02344   0.01294  -0.0531   0.9985   0.0583
  -1.750   0.0358   0.02215   0.01142  -0.0566   0.9843   0.0730
  -1.500   0.0811   0.02087   0.01013  -0.0600   0.9680   0.1128
  -1.250   0.1251   0.01879   0.00921  -0.0638   0.9527   0.3346
  -1.000   0.1639   0.01657   0.00865  -0.0643   0.9342   1.0000
  -0.750   0.2072   0.01655   0.00806  -0.0671   0.9107   1.0000
  -0.500   0.2510   0.01652   0.00759  -0.0698   0.8870   1.0000
  -0.250   0.2963   0.01649   0.00717  -0.0728   0.8625   1.0000
   0.000   0.3400   0.01648   0.00681  -0.0754   0.8360   1.0000
   0.250   0.3813   0.01651   0.00653  -0.0775   0.8077   1.0000
   0.500   0.4194   0.01661   0.00630  -0.0789   0.7789   1.0000
   0.750   0.4540   0.01679   0.00618  -0.0796   0.7509   1.0000
   1.000   0.4852   0.01704   0.00616  -0.0798   0.7244   1.0000
   1.250   0.5142   0.01733   0.00622  -0.0797   0.6997   1.0000
   1.500   0.5426   0.01766   0.00631  -0.0794   0.6777   1.0000
   1.750   0.5697   0.01801   0.00649  -0.0790   0.6568   1.0000
   2.000   0.5970   0.01838   0.00668  -0.0786   0.6384   1.0000
   2.250   0.6238   0.01876   0.00695  -0.0782   0.6208   1.0000
   2.500   0.6506   0.01917   0.00726  -0.0779   0.6042   1.0000
   2.750   0.6774   0.01958   0.00759  -0.0776   0.5885   1.0000
   3.000   0.7042   0.02001   0.00797  -0.0773   0.5739   1.0000
   3.250   0.7309   0.02045   0.00841  -0.0769   0.5598   1.0000
   3.500   0.7574   0.02091   0.00884  -0.0766   0.5465   1.0000
   3.750   0.7837   0.02137   0.00930  -0.0762   0.5336   1.0000
   4.000   0.8098   0.02185   0.00978  -0.0758   0.5212   1.0000
   4.250   0.8355   0.02233   0.01035  -0.0754   0.5089   1.0000
   4.500   0.8605   0.02284   0.01093  -0.0748   0.4961   1.0000
   4.750   0.8852   0.02337   0.01154  -0.0742   0.4835   1.0000
   5.000   0.9097   0.02392   0.01218  -0.0735   0.4712   1.0000
   5.250   0.9340   0.02447   0.01289  -0.0729   0.4591   1.0000
   5.500   0.9583   0.02503   0.01356  -0.0722   0.4471   1.0000
   5.750   0.9824   0.02559   0.01421  -0.0714   0.4352   1.0000
   6.000   1.0064   0.02614   0.01488  -0.0706   0.4231   1.0000
   6.250   1.0290   0.02675   0.01567  -0.0697   0.4100   1.0000
   6.500   1.0514   0.02735   0.01650  -0.0687   0.3965   1.0000
   6.750   1.0734   0.02795   0.01729  -0.0676   0.3828   1.0000
   7.000   1.0950   0.02855   0.01809  -0.0665   0.3688   1.0000
   7.250   1.1161   0.02914   0.01887  -0.0652   0.3543   1.0000
   7.500   1.1368   0.02973   0.01965  -0.0639   0.3393   1.0000
   7.750   1.1567   0.03031   0.02046  -0.0625   0.3236   1.0000
   8.000   1.1744   0.03101   0.02145  -0.0609   0.3058   1.0000
   8.250   1.1919   0.03166   0.02234  -0.0593   0.2878   1.0000
   8.500   1.2088   0.03227   0.02310  -0.0575   0.2696   1.0000
   8.750   1.2234   0.03311   0.02417  -0.0556   0.2494   1.0000
   9.000   1.2362   0.03392   0.02511  -0.0534   0.2282   1.0000
   9.250   1.2458   0.03499   0.02641  -0.0511   0.2044   1.0000
   9.500   1.2522   0.03627   0.02775  -0.0487   0.1801   1.0000
   9.750   1.2544   0.03789   0.02937  -0.0460   0.1561   1.0000
  10.000   1.2523   0.03992   0.03137  -0.0433   0.1339   1.0000
  10.250   1.2459   0.04226   0.03372  -0.0403   0.1149   1.0000
  10.500   1.2361   0.04502   0.03648  -0.0376   0.0998   1.0000
  10.750   1.2251   0.04819   0.03965  -0.0358   0.0878   1.0000
  11.000   1.2134   0.05179   0.04326  -0.0350   0.0783   1.0000
  11.250   1.2010   0.05592   0.04739  -0.0352   0.0705   1.0000
  11.500   1.1914   0.06027   0.05188  -0.0359   0.0630   1.0000
  11.750   1.1798   0.06502   0.05661  -0.0373   0.0583   1.0000
  12.000   1.1724   0.06966   0.06146  -0.0384   0.0526   1.0000
  12.250   1.1636   0.07447   0.06632  -0.0399   0.0489   1.0000
  12.500   1.1558   0.07925   0.07115  -0.0412   0.0459   1.0000
  12.750   1.1503   0.08400   0.07615  -0.0423   0.0431   1.0000
  13.000   1.1441   0.08889   0.08121  -0.0437   0.0407   1.0000
  13.250   1.1384   0.09373   0.08617  -0.0452   0.0390   1.0000
  13.500   1.1332   0.09844   0.09094  -0.0467   0.0375   1.0000
  13.750   1.1273   0.10353   0.09612  -0.0483   0.0362   1.0000
  14.000   1.1181   0.10982   0.10268  -0.0511   0.0355   1.0000
  14.250   1.1076   0.11659   0.10969  -0.0543   0.0352   1.0000
  14.500   1.0951   0.12415   0.11745  -0.0582   0.0350   1.0000
  14.750   1.0817   0.13238   0.12586  -0.0627   0.0351   1.0000
  15.000   1.0671   0.14139   0.13500  -0.0678   0.0354   1.0000
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