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EPPLER STF 863-615 AIRFOIL (stf86361-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: EPPLER STF 863-615 AIRFOIL (stf86361-il)
Reynolds number: 200,000
Max Cl/Cd: 56.33 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-stf86361-il-200000-n5.txt
Download as CSV file: xf-stf86361-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER STF 863-615 AIRFOIL                      
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -14.000  -0.0763   0.11188   0.10785  -0.1298   0.9308   0.0198
 -13.750  -0.0796   0.10801   0.10399  -0.1317   0.9297   0.0201
 -13.500  -0.0811   0.10418   0.10017  -0.1333   0.9286   0.0201
 -13.250  -0.0828   0.10010   0.09610  -0.1349   0.9276   0.0202
 -13.000  -0.0734   0.09826   0.09426  -0.1334   0.9267   0.0213
 -12.750  -0.0708   0.09507   0.09107  -0.1342   0.9257   0.0218
 -12.500  -0.0699   0.09137   0.08738  -0.1354   0.9248   0.0221
 -12.250  -0.0701   0.08743   0.08345  -0.1366   0.9240   0.0225
 -12.000  -0.0712   0.08327   0.07929  -0.1381   0.9233   0.0227
 -11.750  -0.0732   0.07883   0.07486  -0.1397   0.9226   0.0229
 -11.500  -0.0765   0.07402   0.07006  -0.1416   0.9220   0.0230
  -8.500  -0.3579   0.05030   0.04515  -0.1206   0.8865   0.0144
  -8.250  -0.3542   0.04749   0.04218  -0.1193   0.8847   0.0141
  -8.000  -0.3432   0.04439   0.03879  -0.1191   0.8834   0.0138
  -7.750  -0.3260   0.04117   0.03522  -0.1194   0.8824   0.0137
  -7.250  -0.3249   0.03806   0.03162  -0.1118   0.8755   0.0137
  -7.000  -0.3066   0.03587   0.02903  -0.1110   0.8736   0.0139
  -6.750  -0.2837   0.03408   0.02680  -0.1107   0.8724   0.0143
  -6.500  -0.2600   0.03230   0.02483  -0.1110   0.8715   0.0158
  -6.250  -0.2338   0.03112   0.02350  -0.1116   0.8706   0.0173
  -6.000  -0.2053   0.02974   0.02188  -0.1120   0.8698   0.0180
  -5.750  -0.1765   0.02857   0.02050  -0.1123   0.8692   0.0184
  -5.500  -0.1479   0.02764   0.01941  -0.1126   0.8686   0.0191
  -5.250  -0.1182   0.02721   0.01876  -0.1132   0.8681   0.0202
  -5.000  -0.1126   0.02649   0.01818  -0.1097   0.8640   0.0216
  -4.750  -0.0930   0.02598   0.01767  -0.1088   0.8616   0.0227
  -4.500  -0.0671   0.02543   0.01709  -0.1091   0.8600   0.0233
  -4.250  -0.0377   0.02487   0.01650  -0.1102   0.8586   0.0240
  -4.000  -0.0063   0.02439   0.01597  -0.1117   0.8575   0.0249
  -3.750   0.0261   0.02401   0.01548  -0.1135   0.8566   0.0269
  -3.500   0.0600   0.02363   0.01500  -0.1155   0.8558   0.0284
  -3.250   0.0936   0.02340   0.01467  -0.1172   0.8550   0.0294
  -3.000   0.1271   0.02323   0.01442  -0.1188   0.8544   0.0309
  -2.750   0.1395   0.02357   0.01470  -0.1167   0.8493   0.0323
  -2.500   0.1646   0.02362   0.01474  -0.1168   0.8466   0.0367
  -2.250   0.2133   0.02236   0.01564  -0.1235   0.8466   0.6234
  -2.000   0.2398   0.02266   0.01585  -0.1234   0.8445   0.6381
  -1.750   0.2691   0.02284   0.01595  -0.1238   0.8428   0.6484
  -1.500   0.2986   0.02306   0.01615  -0.1239   0.8414   0.6621
  -1.250   0.3303   0.02312   0.01617  -0.1245   0.8404   0.6697
  -1.000   0.3402   0.02362   0.01664  -0.1218   0.8329   0.6743
  -0.750   0.3619   0.02400   0.01705  -0.1204   0.8303   0.6859
  -0.500   0.3854   0.02438   0.01749  -0.1190   0.8286   0.7018
  -0.250   0.4151   0.02435   0.01747  -0.1196   0.8274   0.7039
   0.000   0.4475   0.02426   0.01737  -0.1208   0.8264   0.7049
   0.500   0.4859   0.02472   0.01783  -0.1188   0.8160   0.7066
   0.750   0.5186   0.02456   0.01768  -0.1201   0.8144   0.7076
   1.000   0.5520   0.02437   0.01751  -0.1215   0.8131   0.7087
   1.250   0.5860   0.02417   0.01733  -0.1230   0.8121   0.7096
   1.500   0.5938   0.02472   0.01791  -0.1201   0.8024   0.7106
   1.750   0.6257   0.02458   0.01783  -0.1213   0.8007   0.7113
   2.000   0.6589   0.02439   0.01769  -0.1226   0.7995   0.7122
   2.500   0.7014   0.02471   0.01811  -0.1214   0.7879   0.7145
   2.750   0.7349   0.02444   0.01793  -0.1227   0.7863   0.7153
   3.250   0.7806   0.02446   0.01812  -0.1217   0.7740   0.7167
   4.750   0.9891   0.01756   0.01078  -0.1245   0.5478   0.7210
   5.000   0.9729   0.01943   0.01190  -0.1171   0.4297   0.7219
   5.250   0.9571   0.02159   0.01333  -0.1104   0.3040   0.7227
   5.500   0.9495   0.02364   0.01465  -0.1054   0.1796   0.7234
   5.750   0.9514   0.02528   0.01577  -0.1020   0.0882   0.7242
   6.000   0.9596   0.02659   0.01679  -0.0996   0.0376   0.7249
   6.250   0.9748   0.02743   0.01764  -0.0980   0.0277   0.7258
   6.500   0.9908   0.02822   0.01851  -0.0967   0.0242   0.7266
   6.750   1.0055   0.02913   0.01951  -0.0951   0.0222   0.7274
   7.000   1.0205   0.03001   0.02051  -0.0936   0.0212   0.7283
   7.250   1.0355   0.03091   0.02153  -0.0921   0.0200   0.7291
   7.500   1.0496   0.03186   0.02258  -0.0906   0.0186   0.7299
   7.750   1.0622   0.03291   0.02373  -0.0889   0.0177   0.7308
   8.000   1.0736   0.03408   0.02503  -0.0870   0.0170   0.7316
   8.250   1.0842   0.03533   0.02638  -0.0851   0.0164   0.7325
   8.500   1.0943   0.03671   0.02785  -0.0830   0.0159   0.7334
   8.750   1.1044   0.03827   0.02950  -0.0809   0.0153   0.7343
   9.000   1.1191   0.03979   0.03112  -0.0794   0.0147   0.7352
   9.250   1.1357   0.04083   0.03232  -0.0782   0.0139   0.7361
   9.500   1.1531   0.04205   0.03370  -0.0771   0.0131   0.7370
   9.750   1.1728   0.04346   0.03528  -0.0762   0.0126   0.7380
  10.000   1.1928   0.04503   0.03703  -0.0754   0.0120   0.7390
  10.250   1.2117   0.04679   0.03900  -0.0745   0.0115   0.7401
  10.500   1.2256   0.04857   0.04098  -0.0732   0.0110   0.7412
  10.750   1.2351   0.05037   0.04294  -0.0716   0.0104   0.7422
  11.000   1.2468   0.05399   0.04677  -0.0704   0.0095   0.7432
  11.250   1.2469   0.05591   0.04900  -0.0677   0.0092   0.7442
  11.500   1.2465   0.05850   0.05193  -0.0651   0.0090   0.7451
  11.750   1.2429   0.06156   0.05533  -0.0624   0.0088   0.7459
  12.000   1.2356   0.06491   0.05902  -0.0596   0.0086   0.7468
  12.250   1.2248   0.06861   0.06304  -0.0568   0.0085   0.7476
  12.500   1.2111   0.07259   0.06733  -0.0543   0.0084   0.7484
  12.750   1.1957   0.07685   0.07188  -0.0522   0.0084   0.7492
  13.000   1.1781   0.08151   0.07682  -0.0506   0.0083   0.7500
  13.250   1.1593   0.08660   0.08216  -0.0497   0.0083   0.7508
  13.500   1.1403   0.09202   0.08782  -0.0497   0.0083   0.7516
  13.750   1.1194   0.09819   0.09423  -0.0505   0.0083   0.7524
  14.000   1.0982   0.10497   0.10124  -0.0525   0.0083   0.7532
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