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DU86-084/18 8.44% (du8608418-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: DU86-084/18 8.44% (du8608418-il)
Reynolds number: 1,000,000
Max Cl/Cd: 70.61 at α=6.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-du8608418-il-1000000-n5.txt
Download as CSV file: xf-du8608418-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: DU86-084/18 8.44%                               
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.5585   0.08420   0.08197  -0.0210   0.8224   0.0028
  -9.500  -0.5732   0.07717   0.07498  -0.0251   0.8220   0.0027
  -9.250  -0.5833   0.07136   0.06920  -0.0295   0.8214   0.0027
  -9.000  -0.6045   0.06455   0.06238  -0.0348   0.8209   0.0027
  -8.750  -0.6267   0.05874   0.05651  -0.0354   0.8204   0.0027
  -8.500  -0.6436   0.05144   0.04904  -0.0357   0.8201   0.0026
  -8.250  -0.6578   0.04351   0.04085  -0.0346   0.8197   0.0026
  -8.000  -0.6860   0.03081   0.02745  -0.0303   0.8193   0.0024
  -7.750  -0.6869   0.02425   0.02020  -0.0271   0.8189   0.0023
  -7.500  -0.6740   0.02061   0.01605  -0.0251   0.8185   0.0023
  -7.250  -0.6549   0.01836   0.01344  -0.0239   0.8181   0.0023
  -7.000  -0.6336   0.01664   0.01144  -0.0229   0.8179   0.0024
  -6.750  -0.6110   0.01523   0.00980  -0.0221   0.8177   0.0024
  -6.500  -0.5870   0.01423   0.00864  -0.0216   0.8174   0.0025
  -6.250  -0.5626   0.01337   0.00764  -0.0210   0.8172   0.0026
  -6.000  -0.5375   0.01266   0.00681  -0.0206   0.8168   0.0027
  -5.750  -0.5119   0.01211   0.00615  -0.0203   0.8163   0.0028
  -5.500  -0.4863   0.01151   0.00546  -0.0200   0.8159   0.0031
  -5.250  -0.4602   0.01105   0.00496  -0.0197   0.8156   0.0037
  -5.000  -0.4334   0.01076   0.00464  -0.0196   0.8152   0.0044
  -4.750  -0.4065   0.01046   0.00430  -0.0195   0.8147   0.0050
  -4.500  -0.3793   0.01024   0.00406  -0.0195   0.8141   0.0056
  -4.250  -0.3524   0.00992   0.00369  -0.0193   0.8136   0.0066
  -4.000  -0.3253   0.00967   0.00344  -0.0193   0.8130   0.0083
  -3.750  -0.2980   0.00948   0.00322  -0.0193   0.8123   0.0095
  -3.500  -0.2706   0.00927   0.00299  -0.0192   0.8116   0.0120
  -3.250  -0.2433   0.00906   0.00280  -0.0191   0.8107   0.0184
  -3.000  -0.2160   0.00886   0.00264  -0.0191   0.8098   0.0296
  -2.750  -0.1889   0.00865   0.00248  -0.0190   0.8087   0.0490
  -2.500  -0.1617   0.00842   0.00234  -0.0190   0.8071   0.0755
  -2.250  -0.1344   0.00814   0.00218  -0.0190   0.8046   0.1068
  -2.000  -0.1075   0.00782   0.00202  -0.0189   0.8019   0.1536
  -1.750  -0.0812   0.00739   0.00187  -0.0188   0.7994   0.2326
  -1.500  -0.0552   0.00693   0.00173  -0.0187   0.7973   0.3322
  -1.250  -0.0289   0.00656   0.00163  -0.0186   0.7954   0.4155
  -1.000  -0.0019   0.00623   0.00153  -0.0186   0.7926   0.4830
  -0.750   0.0249   0.00586   0.00142  -0.0185   0.7890   0.5587
  -0.500   0.0508   0.00539   0.00128  -0.0183   0.7853   0.6572
  -0.250   0.0727   0.00480   0.00129  -0.0168   0.7816   0.8212
   0.000   0.1002   0.00480   0.00136  -0.0166   0.7751   0.8566
   0.250   0.1286   0.00477   0.00133  -0.0166   0.7684   0.8673
   0.750   0.1848   0.00464   0.00117  -0.0164   0.7356   0.8815
   1.000   0.2105   0.00473   0.00101  -0.0158   0.6809   0.8871
   1.250   0.2350   0.00506   0.00109  -0.0151   0.6174   0.8915
   1.750   0.2851   0.00577   0.00136  -0.0142   0.4936   0.9001
   2.000   0.3101   0.00608   0.00149  -0.0137   0.4424   0.9042
   2.250   0.3343   0.00641   0.00164  -0.0130   0.3899   0.9089
   2.500   0.3591   0.00676   0.00179  -0.0125   0.3369   0.9138
   2.750   0.3843   0.00706   0.00193  -0.0121   0.2908   0.9168
   3.000   0.4103   0.00728   0.00205  -0.0119   0.2583   0.9182
   3.250   0.4365   0.00757   0.00218  -0.0118   0.2198   0.9189
   3.500   0.4632   0.00781   0.00231  -0.0118   0.1904   0.9195
   3.750   0.4898   0.00807   0.00247  -0.0118   0.1601   0.9199
   4.000   0.5164   0.00834   0.00262  -0.0118   0.1332   0.9202
   4.250   0.5431   0.00859   0.00279  -0.0118   0.1117   0.9206
   4.500   0.5700   0.00882   0.00296  -0.0118   0.0951   0.9210
   4.750   0.5967   0.00906   0.00315  -0.0118   0.0804   0.9214
   5.000   0.6231   0.00935   0.00338  -0.0117   0.0637   0.9218
   5.250   0.6494   0.00964   0.00361  -0.0117   0.0497   0.9224
   5.500   0.6757   0.00993   0.00385  -0.0116   0.0393   0.9229
   5.750   0.7023   0.01018   0.00410  -0.0116   0.0328   0.9233
   6.000   0.7286   0.01046   0.00436  -0.0115   0.0264   0.9237
   6.250   0.7551   0.01072   0.00463  -0.0115   0.0230   0.9241
   6.500   0.7809   0.01106   0.00496  -0.0114   0.0166   0.9245
   6.750   0.8059   0.01151   0.00536  -0.0112   0.0086   0.9250
   7.000   0.8312   0.01193   0.00576  -0.0110   0.0057   0.9254
   7.250   0.8569   0.01227   0.00614  -0.0108   0.0049   0.9258
   7.500   0.8821   0.01266   0.00657  -0.0106   0.0042   0.9262
   7.750   0.9069   0.01313   0.00709  -0.0104   0.0034   0.9267
   8.000   0.9315   0.01359   0.00761  -0.0101   0.0029   0.9271
   8.250   0.9563   0.01401   0.00808  -0.0099   0.0026   0.9276
   8.500   0.9805   0.01451   0.00867  -0.0095   0.0023   0.9280
   8.750   1.0046   0.01500   0.00921  -0.0092   0.0020   0.9284
   9.250   1.0477   0.01660   0.01102  -0.0078   0.0014   0.9300
   9.500   1.0700   0.01721   0.01172  -0.0073   0.0013   0.9307
   9.750   1.0912   0.01796   0.01258  -0.0066   0.0012   0.9314
  10.000   1.1114   0.01878   0.01352  -0.0058   0.0012   0.9322
  10.250   1.1305   0.01970   0.01458  -0.0048   0.0011   0.9331
  10.500   1.1479   0.02076   0.01579  -0.0037   0.0011   0.9341
  10.750   1.1637   0.02195   0.01715  -0.0024   0.0011   0.9352
  11.000   1.1784   0.02313   0.01852  -0.0010   0.0010   0.9365
  11.250   1.1904   0.02449   0.02006   0.0007   0.0010   0.9380
  11.500   1.1981   0.02613   0.02190   0.0029   0.0010   0.9398
  11.750   1.2022   0.02758   0.02354   0.0056   0.0010   0.9420
  12.000   1.1990   0.02917   0.02533   0.0092   0.0010   0.9462
  12.250   1.1955   0.03091   0.02726   0.0123   0.0010   0.9519
  12.500   1.1872   0.03333   0.02993   0.0149   0.0009   0.9624
  12.750   1.1897   0.03573   0.03253   0.0152   0.0010   0.9805
  13.250   1.1661   0.04242   0.03962   0.0176   0.0009   1.0000
  13.500   1.1461   0.04723   0.04464   0.0174   0.0009   1.0000
  13.750   1.1349   0.05160   0.04916   0.0160   0.0009   1.0000
  14.000   1.1184   0.05760   0.05532   0.0128   0.0010   1.0000
  14.250   1.0929   0.06689   0.06480   0.0065   0.0010   1.0000
  14.500   1.0648   0.07905   0.07715  -0.0020   0.0010   1.0000
  14.750   1.0262   0.09397   0.09221  -0.0108   0.0010   1.0000
  15.000   0.9945   0.10636   0.10468  -0.0175   0.0010   1.0000
  15.250   0.9680   0.11753   0.11590  -0.0235   0.0010   1.0000
  15.500   0.9268   0.13297   0.13139  -0.0316   0.0011   1.0000
  15.750   0.8992   0.14586   0.14432  -0.0383   0.0011   1.0000
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