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S8036 (16%) (s8036-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: S8036 (16%) (s8036-il)
Reynolds number: 50,000
Max Cl/Cd: 25.68 at α=8.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s8036-il-50000-n5.txt
Download as CSV file: xf-s8036-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S8036 (16%)                                     
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -12.750  -0.4731   0.10870   0.10096  -0.0512   1.0000   0.0497
 -12.500  -0.4894   0.10078   0.09308  -0.0552   1.0000   0.0495
 -12.250  -0.5066   0.09354   0.08584  -0.0588   1.0000   0.0491
 -12.000  -0.5349   0.08548   0.07775  -0.0633   1.0000   0.0487
 -11.750  -0.5617   0.07897   0.07118  -0.0662   1.0000   0.0483
 -11.500  -0.5893   0.07339   0.06550  -0.0680   1.0000   0.0480
 -11.250  -0.6148   0.06887   0.06085  -0.0682   1.0000   0.0477
 -11.000  -0.6377   0.06518   0.05703  -0.0671   1.0000   0.0476
 -10.750  -0.6612   0.06204   0.05373  -0.0647   1.0000   0.0478
 -10.500  -0.6822   0.05946   0.05100  -0.0612   1.0000   0.0479
 -10.250  -0.7011   0.05729   0.04869  -0.0567   1.0000   0.0481
 -10.000  -0.7192   0.05502   0.04619  -0.0520   1.0000   0.0488
  -9.750  -0.7323   0.05278   0.04370  -0.0476   1.0000   0.0494
  -9.500  -0.7392   0.05084   0.04162  -0.0437   1.0000   0.0503
  -9.250  -0.7397   0.04941   0.04019  -0.0403   1.0000   0.0515
  -9.000  -0.7420   0.04793   0.03860  -0.0366   1.0000   0.0525
  -8.750  -0.7447   0.04646   0.03699  -0.0327   1.0000   0.0538
  -8.500  -0.7462   0.04493   0.03525  -0.0288   1.0000   0.0551
  -8.250  -0.7459   0.04349   0.03355  -0.0251   1.0000   0.0567
  -8.000  -0.7386   0.04207   0.03200  -0.0227   0.9988   0.0592
  -7.750  -0.7060   0.04034   0.03015  -0.0247   0.9914   0.0636
  -7.500  -0.6716   0.03853   0.02813  -0.0266   0.9844   0.0691
  -7.250  -0.6394   0.03709   0.02654  -0.0280   0.9764   0.0763
  -7.000  -0.6078   0.03573   0.02519  -0.0294   0.9687   0.0846
  -6.750  -0.5760   0.03442   0.02384  -0.0308   0.9611   0.0958
  -6.500  -0.5495   0.03322   0.02263  -0.0313   0.9520   0.1093
  -6.250  -0.5217   0.03198   0.02139  -0.0321   0.9441   0.1283
  -6.000  -0.5003   0.03074   0.02029  -0.0320   0.9347   0.1522
  -5.750  -0.4812   0.02948   0.01923  -0.0315   0.9255   0.1862
  -5.500  -0.4619   0.02806   0.01819  -0.0312   0.9171   0.2437
  -5.250  -0.4518   0.02685   0.01755  -0.0290   0.9071   0.3237
  -5.000  -0.4317   0.02606   0.01743  -0.0276   0.9001   0.4412
  -4.750  -0.4140   0.02612   0.01776  -0.0249   0.8910   0.5232
  -4.500  -0.3873   0.02634   0.01795  -0.0238   0.8842   0.5847
  -4.250  -0.3665   0.02663   0.01814  -0.0217   0.8762   0.6267
  -4.000  -0.3402   0.02698   0.01835  -0.0204   0.8690   0.6613
  -3.750  -0.3012   0.02741   0.01863  -0.0210   0.8646   0.6929
  -3.500  -0.2864   0.02770   0.01880  -0.0181   0.8551   0.7172
  -3.250  -0.2455   0.02816   0.01910  -0.0191   0.8501   0.7403
  -3.000  -0.2017   0.02843   0.01918  -0.0209   0.8460   0.7598
  -2.750  -0.1819   0.02865   0.01927  -0.0192   0.8368   0.7756
  -2.500  -0.1454   0.02865   0.01910  -0.0205   0.8316   0.7904
  -2.250  -0.1091   0.02879   0.01907  -0.0218   0.8254   0.8020
  -2.000  -0.0780   0.02889   0.01904  -0.0225   0.8181   0.8129
  -1.750  -0.0434   0.02877   0.01877  -0.0238   0.8131   0.8250
  -1.500  -0.0086   0.02898   0.01886  -0.0252   0.8058   0.8336
  -1.250   0.0207   0.02899   0.01876  -0.0258   0.7991   0.8444
  -1.000   0.0693   0.02895   0.01858  -0.0296   0.7950   0.8521
  -0.750   0.0878   0.02917   0.01875  -0.0285   0.7860   0.8629
  -0.500   0.1289   0.02919   0.01867  -0.0311   0.7804   0.8709
  -0.250   0.1666   0.02915   0.01853  -0.0332   0.7752   0.8794
   0.000   0.1965   0.02943   0.01879  -0.0342   0.7665   0.8877
   0.250   0.2349   0.02936   0.01864  -0.0364   0.7612   0.8960
   0.500   0.2706   0.02960   0.01885  -0.0385   0.7535   0.9033
   0.750   0.3008   0.02969   0.01891  -0.0395   0.7463   0.9128
   1.000   0.3517   0.02950   0.01867  -0.0438   0.7418   0.9181
   1.250   0.3690   0.02999   0.01919  -0.0430   0.7314   0.9294
   1.500   0.4158   0.02985   0.01902  -0.0466   0.7259   0.9355
   1.750   0.4400   0.03024   0.01944  -0.0470   0.7166   0.9460
   2.000   0.4813   0.03017   0.01938  -0.0498   0.7099   0.9535
   2.250   0.5123   0.03041   0.01966  -0.0512   0.7012   0.9629
   2.500   0.5477   0.03044   0.01973  -0.0531   0.6933   0.9721
   2.750   0.5828   0.03056   0.01989  -0.0552   0.6847   0.9813
   3.000   0.6208   0.03051   0.01989  -0.0576   0.6760   0.9896
   3.250   0.6567   0.03060   0.02006  -0.0600   0.6662   0.9990
   3.500   0.6744   0.03054   0.02001  -0.0585   0.6576   1.0000
   3.750   0.6687   0.03106   0.02056  -0.0535   0.6466   1.0000
   4.000   0.6911   0.03075   0.02024  -0.0523   0.6391   1.0000
   4.250   0.6791   0.03143   0.02094  -0.0463   0.6270   1.0000
   4.500   0.6907   0.03146   0.02098  -0.0435   0.6177   1.0000
   4.750   0.7010   0.03152   0.02105  -0.0405   0.6073   1.0000
   5.000   0.6996   0.03201   0.02155  -0.0359   0.5954   1.0000
   5.250   0.7258   0.03162   0.02117  -0.0348   0.5860   1.0000
   5.750   0.7370   0.03223   0.02181  -0.0274   0.5610   1.0000
   6.000   0.7519   0.03222   0.02182  -0.0249   0.5490   1.0000
   6.250   0.7825   0.03159   0.02121  -0.0243   0.5378   1.0000
   6.500   0.7858   0.03199   0.02165  -0.0203   0.5235   1.0000
   6.750   0.7913   0.03233   0.02201  -0.0166   0.5091   1.0000
   7.000   0.7982   0.03258   0.02227  -0.0130   0.4948   1.0000
   7.250   0.8070   0.03274   0.02246  -0.0096   0.4800   1.0000
   7.500   0.8173   0.03287   0.02261  -0.0066   0.4647   1.0000
   7.750   0.8281   0.03305   0.02279  -0.0037   0.4485   1.0000
   8.000   0.8387   0.03328   0.02303  -0.0008   0.4313   1.0000
   8.250   0.8497   0.03357   0.02331   0.0018   0.4133   1.0000
   8.500   0.8621   0.03384   0.02353   0.0043   0.3946   1.0000
   8.750   0.8758   0.03411   0.02372   0.0065   0.3757   1.0000
   9.000   0.8823   0.03490   0.02446   0.0092   0.3563   1.0000
   9.250   0.8894   0.03576   0.02527   0.0116   0.3373   1.0000
   9.500   0.8967   0.03669   0.02613   0.0138   0.3190   1.0000
   9.750   0.9040   0.03773   0.02709   0.0159   0.3017   1.0000
  10.000   0.9113   0.03886   0.02816   0.0178   0.2858   1.0000
  10.250   0.9184   0.04009   0.02933   0.0195   0.2709   1.0000
  10.500   0.9257   0.04138   0.03058   0.0212   0.2571   1.0000
  10.750   0.9349   0.04262   0.03174   0.0227   0.2449   1.0000
  11.000   0.9429   0.04401   0.03311   0.0241   0.2333   1.0000
  11.250   0.9497   0.04560   0.03475   0.0253   0.2224   1.0000
  11.500   0.9602   0.04692   0.03604   0.0265   0.2129   1.0000
  11.750   0.9687   0.04848   0.03765   0.0276   0.2039   1.0000
  12.000   0.9775   0.05007   0.03929   0.0286   0.1957   1.0000
  12.250   0.9871   0.05159   0.04084   0.0295   0.1879   1.0000
  12.500   0.9963   0.05331   0.04264   0.0303   0.1811   1.0000
  12.750   1.0030   0.05520   0.04465   0.0311   0.1744   1.0000
  13.000   1.0171   0.05653   0.04596   0.0319   0.1684   1.0000
  13.250   1.0149   0.05932   0.04899   0.0325   0.1630   1.0000
  13.500   1.0255   0.06095   0.05066   0.0331   0.1577   1.0000
  13.750   1.0324   0.06306   0.05286   0.0337   0.1532   1.0000
  14.000   1.0220   0.06683   0.05689   0.0339   0.1492   1.0000
  14.250   1.0210   0.06971   0.05992   0.0340   0.1451   1.0000
  14.500   1.0424   0.07035   0.06046   0.0348   0.1405   1.0000
  14.750   1.0159   0.07614   0.06659   0.0339   0.1383   1.0000
  15.000   0.9814   0.08345   0.07419   0.0320   0.1362   1.0000
  15.250   0.9295   0.09430   0.08529   0.0279   0.1345   1.0000
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