Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

S8035 for RC aerobatic 14% thick (s8035-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: S8035 for RC aerobatic 14% thick (s8035-il)
Reynolds number: 1,000,000
Max Cl/Cd: 83.72 at α=8.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s8035-il-1000000.txt
Download as CSV file: xf-s8035-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S8035 for RC aerobatic  14% thick               
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -19.250  -1.1778   0.09694   0.09346  -0.0230   1.0000   0.0145
 -19.000  -1.1976   0.09035   0.08676  -0.0261   1.0000   0.0145
 -18.750  -1.2155   0.08411   0.08042  -0.0290   1.0000   0.0146
 -18.500  -1.2280   0.07883   0.07503  -0.0313   1.0000   0.0148
 -18.250  -1.2459   0.07281   0.06889  -0.0340   1.0000   0.0149
 -18.000  -1.2580   0.06775   0.06373  -0.0362   1.0000   0.0150
 -17.750  -1.2687   0.06302   0.05889  -0.0382   1.0000   0.0151
 -17.500  -1.2749   0.05896   0.05473  -0.0398   1.0000   0.0153
 -17.250  -1.2924   0.05355   0.04919  -0.0419   1.0000   0.0155
 -17.000  -1.3044   0.04904   0.04457  -0.0435   1.0000   0.0156
 -16.750  -1.3163   0.04470   0.04013  -0.0449   1.0000   0.0160
 -16.500  -1.3224   0.04125   0.03658  -0.0457   1.0000   0.0163
 -16.250  -1.3243   0.03838   0.03364  -0.0462   1.0000   0.0167
 -16.000  -1.3260   0.03567   0.03084  -0.0464   1.0000   0.0170
 -15.750  -1.3237   0.03348   0.02858  -0.0463   1.0000   0.0173
 -15.500  -1.3187   0.03165   0.02669  -0.0460   1.0000   0.0179
 -15.250  -1.3132   0.02996   0.02492  -0.0455   1.0000   0.0183
 -15.000  -1.3066   0.02844   0.02333  -0.0448   1.0000   0.0186
 -14.750  -1.2997   0.02704   0.02185  -0.0439   1.0000   0.0189
 -14.500  -1.2991   0.02527   0.02000  -0.0425   1.0000   0.0196
 -14.250  -1.2952   0.02387   0.01856  -0.0409   1.0000   0.0205
 -14.000  -1.2880   0.02279   0.01743  -0.0393   1.0000   0.0211
 -13.750  -1.2795   0.02186   0.01646  -0.0375   1.0000   0.0218
 -13.500  -1.2703   0.02105   0.01558  -0.0355   1.0000   0.0225
 -13.250  -1.2590   0.02040   0.01488  -0.0336   1.0000   0.0231
 -13.000  -1.2522   0.01959   0.01401  -0.0310   1.0000   0.0239
 -12.750  -1.2455   0.01884   0.01323  -0.0281   1.0000   0.0250
 -12.500  -1.2375   0.01823   0.01260  -0.0252   1.0000   0.0262
 -12.250  -1.2280   0.01776   0.01210  -0.0223   1.0000   0.0274
 -12.000  -1.2190   0.01737   0.01166  -0.0191   1.0000   0.0282
 -11.750  -1.2127   0.01681   0.01109  -0.0154   1.0000   0.0302
 -11.500  -1.2003   0.01630   0.01059  -0.0129   1.0000   0.0325
 -11.250  -1.1850   0.01593   0.01019  -0.0108   1.0000   0.0342
 -11.000  -1.1725   0.01540   0.00967  -0.0082   1.0000   0.0375
 -10.750  -1.1569   0.01500   0.00926  -0.0061   1.0000   0.0403
 -10.500  -1.1405   0.01462   0.00886  -0.0040   1.0000   0.0432
 -10.250  -1.1251   0.01418   0.00845  -0.0019   1.0000   0.0467
 -10.000  -1.1073   0.01388   0.00812  -0.0001   1.0000   0.0493
  -9.750  -1.0906   0.01350   0.00775   0.0019   1.0000   0.0529
  -9.500  -1.0738   0.01313   0.00740   0.0039   1.0000   0.0568
  -9.250  -1.0554   0.01288   0.00712   0.0057   1.0000   0.0594
  -9.000  -1.0393   0.01250   0.00677   0.0078   1.0000   0.0646
  -8.750  -1.0222   0.01221   0.00650   0.0098   1.0000   0.0687
  -8.500  -0.9926   0.01187   0.00618   0.0092   0.9988   0.0752
  -8.250  -0.9579   0.01157   0.00589   0.0075   0.9968   0.0817
  -8.000  -0.9232   0.01120   0.00559   0.0058   0.9948   0.0911
  -7.750  -0.8874   0.01089   0.00532   0.0039   0.9932   0.1002
  -7.500  -0.8550   0.01059   0.00504   0.0028   0.9898   0.1083
  -7.250  -0.8213   0.01024   0.00476   0.0013   0.9866   0.1191
  -7.000  -0.7859   0.00992   0.00449  -0.0005   0.9839   0.1313
  -6.750  -0.7527   0.00959   0.00423  -0.0017   0.9800   0.1450
  -6.500  -0.7222   0.00927   0.00398  -0.0024   0.9734   0.1582
  -6.250  -0.6890   0.00897   0.00374  -0.0036   0.9682   0.1715
  -6.000  -0.6593   0.00870   0.00350  -0.0040   0.9594   0.1840
  -5.750  -0.6228   0.00841   0.00327  -0.0059   0.9536   0.1987
  -5.500  -0.5863   0.00812   0.00305  -0.0078   0.9449   0.2159
  -5.250  -0.5495   0.00786   0.00284  -0.0097   0.9333   0.2325
  -5.000  -0.5164   0.00766   0.00264  -0.0108   0.9165   0.2477
  -4.750  -0.4883   0.00750   0.00248  -0.0108   0.8968   0.2634
  -4.500  -0.4626   0.00738   0.00234  -0.0102   0.8786   0.2792
  -4.250  -0.4374   0.00725   0.00222  -0.0096   0.8625   0.2966
  -4.000  -0.4123   0.00713   0.00212  -0.0089   0.8475   0.3150
  -3.750  -0.3869   0.00702   0.00202  -0.0083   0.8330   0.3322
  -3.500  -0.3614   0.00692   0.00192  -0.0077   0.8186   0.3485
  -3.250  -0.3358   0.00682   0.00183  -0.0071   0.8040   0.3639
  -3.000  -0.3102   0.00674   0.00175  -0.0065   0.7886   0.3801
  -2.750  -0.2847   0.00666   0.00167  -0.0059   0.7718   0.3977
  -2.500  -0.2592   0.00658   0.00160  -0.0053   0.7552   0.4149
  -2.250  -0.2333   0.00652   0.00154  -0.0048   0.7400   0.4311
  -2.000  -0.2075   0.00645   0.00148  -0.0042   0.7250   0.4494
  -1.750  -0.1817   0.00638   0.00143  -0.0037   0.7097   0.4678
  -1.500  -0.1559   0.00633   0.00139  -0.0031   0.6941   0.4875
  -1.250  -0.1299   0.00628   0.00135  -0.0026   0.6791   0.5069
  -1.000  -0.1039   0.00625   0.00132  -0.0021   0.6630   0.5247
  -0.750  -0.0778   0.00623   0.00130  -0.0016   0.6460   0.5411
  -0.500  -0.0517   0.00622   0.00128  -0.0011   0.6281   0.5569
  -0.250  -0.0257   0.00621   0.00127  -0.0006   0.6101   0.5735
   0.000   0.0000   0.00621   0.00127   0.0000   0.5915   0.5914
   0.250   0.0258   0.00621   0.00127   0.0006   0.5736   0.6102
   0.500   0.0517   0.00622   0.00128   0.0011   0.5568   0.6285
   0.750   0.0778   0.00623   0.00130   0.0016   0.5411   0.6461
   1.000   0.1039   0.00625   0.00132   0.0021   0.5246   0.6631
   1.250   0.1299   0.00628   0.00135   0.0026   0.5070   0.6791
   1.500   0.1559   0.00633   0.00139   0.0031   0.4877   0.6940
   1.750   0.1817   0.00639   0.00143   0.0037   0.4675   0.7095
   2.000   0.2075   0.00645   0.00148   0.0042   0.4489   0.7250
   2.250   0.2333   0.00652   0.00154   0.0048   0.4313   0.7401
   2.500   0.2592   0.00658   0.00160   0.0053   0.4149   0.7553
   2.750   0.2848   0.00665   0.00167   0.0059   0.3982   0.7718
   3.000   0.3102   0.00674   0.00175   0.0065   0.3801   0.7884
   3.250   0.3358   0.00682   0.00183   0.0071   0.3639   0.8040
   3.500   0.3614   0.00692   0.00192   0.0077   0.3484   0.8186
   3.750   0.3868   0.00702   0.00202   0.0083   0.3318   0.8330
   4.000   0.4122   0.00713   0.00212   0.0089   0.3152   0.8476
   4.250   0.4374   0.00725   0.00223   0.0096   0.2964   0.8626
   4.500   0.4625   0.00738   0.00234   0.0102   0.2790   0.8786
   4.750   0.4883   0.00751   0.00248   0.0108   0.2633   0.8967
   5.000   0.5163   0.00766   0.00264   0.0108   0.2477   0.9164
   5.250   0.5495   0.00786   0.00284   0.0097   0.2324   0.9334
   5.500   0.5863   0.00812   0.00305   0.0078   0.2160   0.9449
   5.750   0.6228   0.00841   0.00327   0.0059   0.1985   0.9534
   6.000   0.6593   0.00870   0.00350   0.0040   0.1839   0.9594
   6.250   0.6890   0.00897   0.00374   0.0036   0.1716   0.9683
   6.500   0.7222   0.00927   0.00398   0.0024   0.1582   0.9733
   6.750   0.7528   0.00959   0.00423   0.0017   0.1450   0.9799
   7.000   0.7859   0.00992   0.00449   0.0005   0.1311   0.9839
   7.250   0.8213   0.01025   0.00476  -0.0013   0.1190   0.9866
   7.500   0.8550   0.01059   0.00504  -0.0028   0.1084   0.9898
   7.750   0.8874   0.01089   0.00532  -0.0039   0.1002   0.9932
   8.000   0.9232   0.01120   0.00559  -0.0058   0.0911   0.9948
   8.250   0.9580   0.01157   0.00589  -0.0075   0.0817   0.9969
   8.500   0.9928   0.01187   0.00618  -0.0092   0.0753   0.9988
   8.750   1.0222   0.01221   0.00650  -0.0098   0.0688   1.0000
   9.000   1.0393   0.01250   0.00677  -0.0078   0.0646   1.0000
   9.250   1.0554   0.01288   0.00712  -0.0057   0.0594   1.0000
   9.500   1.0738   0.01313   0.00740  -0.0039   0.0568   1.0000
   9.750   1.0906   0.01350   0.00775  -0.0019   0.0529   1.0000
  10.000   1.1073   0.01387   0.00812   0.0001   0.0493   1.0000
  10.250   1.1251   0.01418   0.00845   0.0019   0.0468   1.0000
  10.500   1.1406   0.01462   0.00886   0.0040   0.0432   1.0000
  10.750   1.1569   0.01500   0.00926   0.0061   0.0404   1.0000
  11.000   1.1725   0.01540   0.00967   0.0082   0.0375   1.0000
  11.250   1.1852   0.01593   0.01018   0.0107   0.0342   1.0000
  11.500   1.2005   0.01630   0.01058   0.0129   0.0324   1.0000
  11.750   1.2132   0.01679   0.01107   0.0154   0.0304   1.0000
  12.000   1.2190   0.01737   0.01166   0.0191   0.0283   1.0000
  12.250   1.2283   0.01776   0.01210   0.0222   0.0274   1.0000
  12.500   1.2375   0.01824   0.01261   0.0252   0.0263   1.0000
  12.750   1.2462   0.01882   0.01322   0.0280   0.0252   1.0000
  13.000   1.2525   0.01959   0.01401   0.0310   0.0239   1.0000
  13.250   1.2605   0.02034   0.01481   0.0334   0.0229   1.0000
  13.500   1.2705   0.02106   0.01559   0.0355   0.0225   1.0000
  13.750   1.2807   0.02181   0.01640   0.0373   0.0217   1.0000
  14.000   1.2889   0.02276   0.01739   0.0391   0.0210   1.0000
  14.250   1.2957   0.02387   0.01855   0.0408   0.0203   1.0000
  14.500   1.2997   0.02526   0.02000   0.0424   0.0197   1.0000
  14.750   1.2992   0.02712   0.02193   0.0439   0.0190   1.0000
  15.000   1.3098   0.02823   0.02310   0.0446   0.0185   1.0000
  15.250   1.3137   0.02997   0.02493   0.0454   0.0183   1.0000
  15.500   1.3208   0.03152   0.02655   0.0459   0.0178   1.0000
  15.750   1.3247   0.03346   0.02856   0.0462   0.0174   1.0000
  16.000   1.3263   0.03572   0.03089   0.0462   0.0170   1.0000
  16.250   1.3266   0.03822   0.03347   0.0461   0.0166   1.0000
  16.500   1.3235   0.04122   0.03655   0.0456   0.0163   1.0000
  16.750   1.3187   0.04454   0.03997   0.0448   0.0160   1.0000
  17.000   1.3077   0.04875   0.04427   0.0435   0.0157   1.0000
  17.250   1.2904   0.05394   0.04959   0.0416   0.0154   1.0000
  17.500   1.2803   0.05840   0.05415   0.0398   0.0152   1.0000
  17.750   1.2745   0.06240   0.05826   0.0383   0.0150   1.0000
  18.000   1.2623   0.06735   0.06332   0.0362   0.0150   1.0000
  18.250   1.2517   0.07220   0.06827   0.0341   0.0147   1.0000
  18.500   1.2326   0.07838   0.07458   0.0313   0.0147   1.0000
  18.750   1.2174   0.08408   0.08038   0.0287   0.0146   1.0000
  19.000   1.2001   0.09024   0.08665   0.0259   0.0145   1.0000
  19.250   1.1827   0.09647   0.09298   0.0230   0.0144   1.0000
<< Back to S8035 for RC aerobatic 14% thick (s8035-il)

Polar data table (+)

Polar graphs


<< Back to S8035 for RC aerobatic 14% thick (s8035-il)