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EPPLER 694 AIRFOIL (e694-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 694 AIRFOIL (e694-il)
Reynolds number: 200,000
Max Cl/Cd: 59.43 at α=7.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e694-il-200000-n5.txt
Download as CSV file: xf-e694-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 694 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
  ------ -------- --------- --------- -------- -------- --------
 -11.750  -0.0774   0.10749   0.10325  -0.1372   0.9291   0.0206
 -11.500  -0.0712   0.10497   0.10073  -0.1378   0.9272   0.0200
 -11.000  -0.0831   0.09045   0.08625  -0.1450   0.9239   0.0167
 -10.750  -0.0767   0.08642   0.08220  -0.1480   0.9229   0.0165
 -10.500  -0.0718   0.08159   0.07738  -0.1519   0.9220   0.0164
 -10.250  -0.0942   0.07985   0.07571  -0.1470   0.9140   0.0162
 -10.000  -0.1018   0.07372   0.06962  -0.1505   0.9112   0.0161
  -9.500  -0.1590   0.05733   0.05314  -0.1583   0.8993   0.0153
  -9.250  -0.1848   0.05169   0.04730  -0.1606   0.8945   0.0151
  -9.000  -0.2229   0.05054   0.04611  -0.1532   0.8839   0.0151
  -8.750  -0.2419   0.04648   0.04180  -0.1521   0.8791   0.0150
  -8.500  -0.2704   0.04509   0.04028  -0.1450   0.8681   0.0148
  -8.250  -0.2748   0.04082   0.03560  -0.1442   0.8645   0.0149
  -8.000  -0.2911   0.03917   0.03373  -0.1385   0.8554   0.0148
  -7.750  -0.2857   0.03622   0.03037  -0.1371   0.8516   0.0149
  -7.500  -0.2696   0.03332   0.02702  -0.1371   0.8498   0.0150
  -7.250  -0.2476   0.03094   0.02423  -0.1376   0.8487   0.0152
  -7.000  -0.2536   0.03051   0.02363  -0.1323   0.8398   0.0153
  -6.750  -0.2312   0.02901   0.02177  -0.1322   0.8377   0.0162
  -6.500  -0.2053   0.02772   0.02013  -0.1326   0.8363   0.0167
  -6.250  -0.1791   0.02631   0.01857  -0.1330   0.8353   0.0171
  -6.000  -0.1515   0.02519   0.01734  -0.1336   0.8345   0.0174
  -5.750  -0.1459   0.02512   0.01722  -0.1302   0.8285   0.0177
  -5.500  -0.1255   0.02455   0.01656  -0.1295   0.8255   0.0180
  -5.250  -0.0991   0.02383   0.01577  -0.1298   0.8238   0.0186
  -5.000  -0.0708   0.02315   0.01501  -0.1304   0.8226   0.0193
  -4.750  -0.0414   0.02252   0.01430  -0.1313   0.8217   0.0201
  -4.250   0.0202   0.02140   0.01305  -0.1336   0.8203   0.0232
  -4.000   0.0258   0.02190   0.01352  -0.1303   0.8133   0.0248
  -3.750   0.0535   0.02161   0.01318  -0.1309   0.8116   0.0276
  -3.500   0.0835   0.02126   0.01280  -0.1318   0.8103   0.0327
  -3.250   0.1155   0.02079   0.01240  -0.1332   0.8093   0.0513
  -3.000   0.1486   0.02029   0.01209  -0.1349   0.8085   0.0987
  -2.750   0.1836   0.01962   0.01182  -0.1374   0.8078   0.1916
  -2.500   0.2226   0.01870   0.01162  -0.1411   0.8074   0.3747
  -2.000   0.2618   0.01881   0.01268  -0.1393   0.7998   0.6169
  -1.750   0.2811   0.01898   0.01303  -0.1372   0.7977   0.6777
  -1.500   0.3072   0.01910   0.01312  -0.1366   0.7964   0.7157
  -1.250   0.3352   0.01916   0.01312  -0.1365   0.7953   0.7374
  -1.000   0.3642   0.01920   0.01308  -0.1365   0.7945   0.7571
  -0.750   0.3729   0.02006   0.01393  -0.1332   0.7889   0.7720
  -0.500   0.3919   0.02041   0.01424  -0.1314   0.7857   0.7851
  -0.250   0.4212   0.02045   0.01421  -0.1318   0.7841   0.7950
   0.000   0.4471   0.02039   0.01411  -0.1313   0.7828   0.8001
   0.250   0.4779   0.02025   0.01391  -0.1318   0.7818   0.8066
   0.500   0.5089   0.02007   0.01368  -0.1324   0.7810   0.8128
   0.750   0.5384   0.01985   0.01343  -0.1324   0.7802   0.8191
   1.750   0.6351   0.02035   0.01386  -0.1308   0.7675   0.8382
   2.000   0.6715   0.02005   0.01354  -0.1326   0.7666   0.8416
   2.250   0.7055   0.01966   0.01314  -0.1337   0.7658   0.8440
   2.500   0.7428   0.01922   0.01269  -0.1355   0.7650   0.8465
   3.000   0.7771   0.02003   0.01354  -0.1325   0.7529   0.8537
   3.250   0.8161   0.01963   0.01315  -0.1348   0.7517   0.8563
   3.500   0.8550   0.01908   0.01262  -0.1367   0.7504   0.8582
   4.000   0.8920   0.01950   0.01312  -0.1338   0.7376   0.8647
   4.250   0.9342   0.01892   0.01256  -0.1365   0.7355   0.8673
   4.500   0.9806   0.01831   0.01198  -0.1400   0.7335   0.8694
   4.750   0.9725   0.01937   0.01312  -0.1340   0.7218   0.8731
   5.000   1.0112   0.01890   0.01269  -0.1360   0.7189   0.8748
   5.500   1.0441   0.01948   0.01341  -0.1326   0.7029   0.8799
   5.750   1.0421   0.02055   0.01457  -0.1280   0.6897   0.8831
   6.250   1.0610   0.02190   0.01607  -0.1228   0.6659   0.8875
   6.500   1.0849   0.02183   0.01607  -0.1223   0.6559   0.8896
   6.750   1.1110   0.02164   0.01592  -0.1221   0.6427   0.8916
   7.000   1.1405   0.02133   0.01562  -0.1224   0.6269   0.8933
   7.250   1.1732   0.02094   0.01522  -0.1232   0.6085   0.8949
   7.500   1.2066   0.02059   0.01480  -0.1242   0.5857   0.8963
   7.750   1.2314   0.02072   0.01483  -0.1239   0.5577   0.8980
   8.000   1.2497   0.02115   0.01514  -0.1226   0.5283   0.8999
   8.250   1.2619   0.02181   0.01571  -0.1203   0.4992   0.9022
   8.500   1.2692   0.02276   0.01652  -0.1174   0.4673   0.9047
   8.750   1.2734   0.02395   0.01756  -0.1142   0.4326   0.9070
   9.000   1.2736   0.02544   0.01886  -0.1106   0.3945   0.9093
   9.250   1.2740   0.02706   0.02028  -0.1073   0.3556   0.9116
   9.500   1.2726   0.02883   0.02185  -0.1039   0.3161   0.9139
   9.750   1.2724   0.03058   0.02343  -0.1008   0.2770   0.9161
  10.000   1.2744   0.03230   0.02499  -0.0981   0.2467   0.9188
  10.250   1.2802   0.03387   0.02647  -0.0961   0.2218   0.9217
  10.500   1.2872   0.03545   0.02796  -0.0943   0.1952   0.9246
  10.750   1.2922   0.03718   0.02956  -0.0924   0.1657   0.9272
  11.000   1.2959   0.03902   0.03125  -0.0903   0.1369   0.9299
  11.250   1.3007   0.04087   0.03299  -0.0886   0.1112   0.9328
  11.500   1.3052   0.04282   0.03481  -0.0869   0.0861   0.9359
  12.000   1.3171   0.04652   0.03840  -0.0839   0.0515   0.9434
  12.250   1.3210   0.04860   0.04042  -0.0823   0.0366   0.9485
  12.500   1.3252   0.05061   0.04244  -0.0808   0.0274   0.9560
  12.750   1.3287   0.05260   0.04447  -0.0793   0.0217   0.9776
  13.000   1.3355   0.05474   0.04670  -0.0784   0.0187   1.0000
  13.250   1.3428   0.05696   0.04901  -0.0777   0.0170   1.0000
  13.500   1.3501   0.05924   0.05139  -0.0771   0.0156   1.0000
  13.750   1.3554   0.06176   0.05400  -0.0765   0.0146   1.0000
  14.000   1.3608   0.06430   0.05667  -0.0760   0.0138   1.0000
  14.250   1.3660   0.06691   0.05942  -0.0755   0.0134   1.0000
  14.500   1.3697   0.06974   0.06238  -0.0751   0.0129   1.0000
  14.750   1.3728   0.07271   0.06550  -0.0748   0.0125   1.0000
  15.000   1.3748   0.07586   0.06878  -0.0747   0.0122   1.0000
  15.250   1.3759   0.07918   0.07224  -0.0746   0.0119   1.0000
  15.500   1.3759   0.08269   0.07588  -0.0746   0.0117   1.0000
  15.750   1.3746   0.08643   0.07973  -0.0748   0.0115   1.0000
  16.000   1.3724   0.09036   0.08378  -0.0752   0.0113   1.0000
  16.250   1.3708   0.09426   0.08779  -0.0757   0.0111   1.0000
  16.500   1.3712   0.09793   0.09161  -0.0763   0.0110   1.0000
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