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S8064 (s8064-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: S8064 (s8064-il)
Reynolds number: 200,000
Max Cl/Cd: 68.86 at α=5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s8064-il-200000.txt
Download as CSV file: xf-s8064-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S8064                                           
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.4149   0.08868   0.08559  -0.0469   1.0000   0.0602
 -10.500  -0.4262   0.08553   0.08247  -0.0459   1.0000   0.0617
 -10.250  -0.4479   0.08000   0.07700  -0.0468   1.0000   0.0609
 -10.000  -0.4701   0.07437   0.07142  -0.0480   1.0000   0.0613
  -9.750  -0.5059   0.06693   0.06398  -0.0513   1.0000   0.0613
  -9.500  -0.5437   0.06184   0.05886  -0.0519   1.0000   0.0611
  -9.250  -0.5809   0.05836   0.05533  -0.0501   1.0000   0.0608
  -9.000  -0.6169   0.05602   0.05294  -0.0464   1.0000   0.0607
  -8.750  -0.6512   0.05430   0.05116  -0.0411   0.9997   0.0605
  -8.500  -0.6609   0.04971   0.04640  -0.0411   0.9957   0.0614
  -8.250  -0.7819   0.04214   0.03665  -0.0284   0.9929   0.0255
  -8.000  -0.7739   0.03767   0.03181  -0.0270   0.9897   0.0249
  -7.750  -0.7587   0.03416   0.02787  -0.0262   0.9868   0.0245
  -7.500  -0.7364   0.03138   0.02462  -0.0260   0.9844   0.0248
  -7.250  -0.7152   0.02970   0.02256  -0.0253   0.9815   0.0254
  -7.000  -0.6952   0.02730   0.01984  -0.0244   0.9786   0.0265
  -6.750  -0.6702   0.02541   0.01786  -0.0244   0.9761   0.0282
  -6.500  -0.6414   0.02400   0.01632  -0.0249   0.9737   0.0295
  -6.250  -0.6103   0.02280   0.01501  -0.0258   0.9717   0.0315
  -6.000  -0.5889   0.02197   0.01404  -0.0247   0.9682   0.0342
  -5.750  -0.5702   0.02064   0.01276  -0.0235   0.9642   0.0406
  -5.500  -0.5441   0.01970   0.01181  -0.0236   0.9610   0.0540
  -5.250  -0.5146   0.01878   0.01098  -0.0245   0.9584   0.0789
  -5.000  -0.4987   0.01819   0.01051  -0.0228   0.9535   0.1047
  -4.750  -0.4763   0.01748   0.01004  -0.0224   0.9492   0.1497
  -4.500  -0.4509   0.01651   0.00957  -0.0228   0.9459   0.2436
  -4.250  -0.4350   0.01558   0.00931  -0.0214   0.9414   0.3829
  -4.000  -0.4203   0.01497   0.00922  -0.0191   0.9359   0.5042
  -3.750  -0.3935   0.01467   0.00930  -0.0189   0.9324   0.6013
  -3.500  -0.3600   0.01473   0.00957  -0.0196   0.9300   0.6738
  -3.250  -0.3488   0.01484   0.00970  -0.0161   0.9226   0.7093
  -3.000  -0.3177   0.01503   0.00986  -0.0164   0.9189   0.7421
  -2.750  -0.2820   0.01527   0.01003  -0.0176   0.9164   0.7685
  -2.500  -0.2690   0.01545   0.01019  -0.0144   0.9089   0.7874
  -2.250  -0.2387   0.01562   0.01032  -0.0145   0.9051   0.8070
  -2.000  -0.2025   0.01581   0.01046  -0.0157   0.9026   0.8248
  -1.750  -0.1900   0.01598   0.01061  -0.0124   0.8948   0.8402
  -1.500  -0.1589   0.01613   0.01074  -0.0125   0.8910   0.8555
  -1.250  -0.1224   0.01630   0.01088  -0.0136   0.8886   0.8701
  -1.000  -0.1098   0.01644   0.01101  -0.0103   0.8806   0.8843
  -0.750  -0.0755   0.01656   0.01110  -0.0112   0.8770   0.8953
  -0.500  -0.0325   0.01665   0.01116  -0.0139   0.8750   0.9028
  -0.250  -0.0114   0.01675   0.01124  -0.0125   0.8682   0.9135
   0.000   0.0293   0.01687   0.01133  -0.0150   0.8644   0.9194
   0.250   0.0678   0.01684   0.01127  -0.0170   0.8615   0.9270
   0.500   0.1191   0.01685   0.01127  -0.0215   0.8601   0.9295
   0.750   0.1703   0.01681   0.01122  -0.0260   0.8589   0.9322
   1.000   0.1881   0.01692   0.01135  -0.0243   0.8489   0.9418
   1.250   0.2399   0.01679   0.01124  -0.0289   0.8469   0.9433
   1.500   0.2922   0.01656   0.01103  -0.0335   0.8452   0.9447
   1.750   0.3306   0.01656   0.01109  -0.0359   0.8373   0.9486
   2.000   0.3744   0.01621   0.01077  -0.0387   0.8332   0.9519
   2.250   0.4128   0.01573   0.01032  -0.0401   0.8299   0.9562
   2.500   0.4533   0.01546   0.01014  -0.0427   0.8201   0.9591
   2.750   0.4988   0.01478   0.00950  -0.0453   0.8157   0.9613
   3.000   0.5325   0.01435   0.00915  -0.0462   0.8043   0.9662
   3.250   0.5649   0.01382   0.00870  -0.0466   0.7931   0.9713
   3.500   0.6047   0.01315   0.00809  -0.0484   0.7796   0.9746
   3.750   0.6401   0.01260   0.00762  -0.0494   0.7637   0.9793
   4.000   0.6737   0.01214   0.00722  -0.0501   0.7458   0.9841
   4.250   0.7113   0.01172   0.00684  -0.0518   0.7194   0.9879
   4.500   0.7455   0.01146   0.00653  -0.0528   0.6838   0.9925
   4.750   0.7786   0.01141   0.00634  -0.0537   0.6321   0.9966
   5.000   0.8043   0.01168   0.00632  -0.0534   0.5592   1.0000
   5.250   0.8109   0.01221   0.00649  -0.0497   0.4829   1.0000
   5.500   0.8100   0.01297   0.00680  -0.0448   0.3942   1.0000
   5.750   0.8044   0.01379   0.00719  -0.0393   0.3143   1.0000
   6.000   0.7960   0.01453   0.00757  -0.0333   0.2491   1.0000
   6.250   0.7882   0.01528   0.00798  -0.0272   0.1953   1.0000
   6.500   0.7862   0.01611   0.00851  -0.0223   0.1532   1.0000
   6.750   0.7892   0.01694   0.00913  -0.0182   0.1255   1.0000
   7.000   0.7965   0.01773   0.00981  -0.0148   0.1075   1.0000
   7.250   0.8036   0.01855   0.01055  -0.0114   0.0956   1.0000
   7.500   0.8139   0.01933   0.01130  -0.0086   0.0855   1.0000
   7.750   0.8273   0.02006   0.01205  -0.0064   0.0762   1.0000
   8.000   0.8401   0.02095   0.01292  -0.0043   0.0680   1.0000
   8.250   0.8543   0.02174   0.01372  -0.0024   0.0605   1.0000
   8.500   0.8702   0.02280   0.01485  -0.0007   0.0541   1.0000
   8.750   0.8856   0.02406   0.01603   0.0008   0.0475   1.0000
   9.000   0.9029   0.02502   0.01714   0.0022   0.0419   1.0000
   9.250   0.9207   0.02642   0.01849   0.0033   0.0373   1.0000
   9.500   0.9473   0.02838   0.02065   0.0034   0.0342   1.0000
   9.750   0.9696   0.02996   0.02242   0.0041   0.0319   1.0000
  10.000   0.9844   0.03111   0.02364   0.0056   0.0297   1.0000
  10.250   1.0115   0.03471   0.02741   0.0046   0.0274   1.0000
  10.500   1.0219   0.03654   0.02954   0.0069   0.0268   1.0000
  10.750   1.0300   0.03891   0.03224   0.0092   0.0264   1.0000
  11.000   1.0319   0.04142   0.03509   0.0122   0.0259   1.0000
  11.250   1.0288   0.04433   0.03834   0.0154   0.0257   1.0000
  11.500   1.0204   0.04742   0.04175   0.0188   0.0256   1.0000
  11.750   1.0099   0.05065   0.04526   0.0218   0.0257   1.0000
  12.000   0.9945   0.05420   0.04909   0.0247   0.0258   1.0000
  12.250   0.9775   0.05802   0.05315   0.0268   0.0260   1.0000
  12.500   0.9586   0.06201   0.05736   0.0283   0.0262   1.0000
  12.750   0.9362   0.06661   0.06218   0.0290   0.0263   1.0000
  13.000   0.9153   0.07158   0.06733   0.0286   0.0266   1.0000
  13.250   0.8933   0.07713   0.07302   0.0272   0.0269   1.0000
  13.500   0.8681   0.08371   0.07976   0.0246   0.0270   1.0000
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