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EPPLER EC 86(-3)-914 AIRFOIL (ec863914-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: EPPLER EC 86(-3)-914 AIRFOIL (ec863914-il)
Reynolds number: 200,000
Max Cl/Cd: 62.62 at α=4.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-ec863914-il-200000.txt
Download as CSV file: xf-ec863914-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER EC 86(-3)-914 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.750  -0.3652   0.15159   0.14858  -0.0294   1.0000   0.0493
 -12.500  -0.3702   0.14871   0.14572  -0.0304   1.0000   0.0495
  -7.000  -0.6578   0.03972   0.03421  -0.0651   0.9996   0.0255
  -6.750  -0.6237   0.03493   0.02880  -0.0687   0.9985   0.0224
  -6.500  -0.5855   0.03271   0.02600  -0.0711   0.9964   0.0203
  -6.250  -0.5475   0.03204   0.02510  -0.0734   0.9942   0.0197
  -6.000  -0.5186   0.03080   0.02374  -0.0742   0.9916   0.0196
  -5.750  -0.4828   0.02877   0.02166  -0.0766   0.9880   0.0204
  -5.500  -0.4391   0.02804   0.02093  -0.0806   0.9846   0.0216
  -5.250  -0.3827   0.02723   0.02002  -0.0867   0.9736   0.0224
  -5.000  -0.3214   0.02646   0.01909  -0.0938   0.9617   0.0228
  -4.750  -0.2704   0.02625   0.01868  -0.0988   0.9581   0.0237
  -4.500  -0.2338   0.02577   0.01804  -0.1008   0.9502   0.0252
  -4.250  -0.1915   0.02557   0.01769  -0.1039   0.9465   0.0296
  -4.000  -0.1372   0.02449   0.01748  -0.1108   0.9450   0.1935
  -3.750  -0.1043   0.02446   0.01748  -0.1122   0.9385   0.2256
  -3.500  -0.0672   0.02448   0.01753  -0.1144   0.9340   0.2485
  -3.250  -0.0246   0.02464   0.01767  -0.1176   0.9313   0.2675
  -3.000   0.0054   0.02456   0.01762  -0.1185   0.9246   0.2853
  -2.750   0.0451   0.02446   0.01771  -0.1214   0.9206   0.3264
  -2.500   0.0900   0.02440   0.01781  -0.1252   0.9182   0.3648
  -2.250   0.1311   0.02411   0.01793  -0.1286   0.9143   0.4459
  -2.000   0.1574   0.02407   0.01864  -0.1280   0.9078   0.5824
  -1.750   0.1940   0.02455   0.01912  -0.1289   0.9045   0.6419
  -1.500   0.2175   0.02487   0.01936  -0.1278   0.8964   0.6665
  -1.250   0.2503   0.02518   0.01964  -0.1280   0.8922   0.6823
  -1.000   0.2775   0.02543   0.01985  -0.1274   0.8859   0.6955
  -0.750   0.3027   0.02558   0.02001  -0.1260   0.8798   0.7042
  -0.500   0.3401   0.02560   0.02001  -0.1267   0.8770   0.7147
  -0.250   0.3630   0.02557   0.01996  -0.1255   0.8673   0.7252
   0.000   0.3970   0.02532   0.01971  -0.1253   0.8640   0.7321
   0.250   0.4211   0.02523   0.01961  -0.1243   0.8549   0.7406
   0.500   0.4537   0.02488   0.01927  -0.1240   0.8513   0.7475
   0.750   0.4955   0.02434   0.01872  -0.1257   0.8493   0.7557
   1.000   0.5127   0.02410   0.01851  -0.1230   0.8385   0.7620
   1.250   0.5566   0.02331   0.01771  -0.1251   0.8361   0.7694
   1.500   0.5739   0.02301   0.01746  -0.1224   0.8254   0.7747
   1.750   0.6157   0.02222   0.01668  -0.1242   0.8228   0.7831
   2.000   0.6296   0.02196   0.01647  -0.1207   0.8121   0.7902
   2.250   0.6649   0.02114   0.01568  -0.1209   0.8092   0.7990
   2.500   0.6838   0.02081   0.01541  -0.1186   0.7985   0.8069
   2.750   0.7155   0.01987   0.01451  -0.1180   0.7949   0.8147
   3.000   0.7389   0.01953   0.01422  -0.1168   0.7832   0.8225
   3.250   0.7620   0.01899   0.01374  -0.1151   0.7719   0.8284
   3.500   0.7937   0.01833   0.01310  -0.1152   0.7600   0.8341
   3.750   0.8380   0.01761   0.01240  -0.1179   0.7456   0.8387
   4.000   0.8777   0.01676   0.01154  -0.1193   0.7279   0.8411
   4.250   0.9221   0.01612   0.01084  -0.1219   0.7023   0.8429
   4.500   0.9650   0.01579   0.01036  -0.1244   0.6667   0.8448
   4.750   0.9963   0.01591   0.01027  -0.1250   0.6219   0.8465
   5.000   1.0190   0.01634   0.01045  -0.1243   0.5726   0.8482
   5.250   1.0373   0.01697   0.01082  -0.1229   0.5241   0.8503
   5.500   1.0545   0.01771   0.01132  -0.1215   0.4791   0.8518
   5.750   1.0704   0.01846   0.01186  -0.1199   0.4387   0.8530
   6.000   1.0838   0.01915   0.01236  -0.1177   0.4053   0.8545
   6.250   1.0994   0.01984   0.01290  -0.1160   0.3764   0.8563
   6.500   1.1181   0.02052   0.01348  -0.1149   0.3519   0.8577
   6.750   1.1383   0.02123   0.01407  -0.1142   0.3323   0.8590
   7.000   1.1606   0.02192   0.01469  -0.1138   0.3164   0.8602
   7.250   1.1844   0.02255   0.01530  -0.1137   0.3028   0.8616
   7.500   1.2093   0.02315   0.01592  -0.1137   0.2912   0.8634
   7.750   1.2354   0.02380   0.01657  -0.1140   0.2810   0.8650
   8.000   1.2630   0.02450   0.01721  -0.1146   0.2720   0.8662
   8.250   1.2834   0.02501   0.01783  -0.1138   0.2620   0.8675
   8.500   1.3016   0.02559   0.01849  -0.1127   0.2508   0.8688
   8.750   1.3186   0.02621   0.01915  -0.1116   0.2397   0.8703
   9.000   1.3356   0.02690   0.01983  -0.1104   0.2289   0.8719
   9.250   1.3482   0.02760   0.02059  -0.1087   0.2149   0.8740
   9.500   1.3613   0.02827   0.02138  -0.1072   0.1960   0.8760
   9.750   1.3745   0.02919   0.02227  -0.1059   0.1731   0.8778
  10.000   1.3785   0.03118   0.02372  -0.1036   0.0842   0.8792
  10.250   1.3671   0.03501   0.02698  -0.0996   0.0255   0.8801
  10.500   1.3713   0.03717   0.02925  -0.0972   0.0195   0.8815
  10.750   1.3796   0.03889   0.03114  -0.0953   0.0172   0.8830
  11.000   1.3860   0.04081   0.03327  -0.0935   0.0156   0.8846
  11.250   1.3889   0.04309   0.03574  -0.0915   0.0146   0.8863
  11.500   1.3877   0.04582   0.03864  -0.0895   0.0139   0.8881
  11.750   1.3823   0.04908   0.04208  -0.0875   0.0134   0.8900
  12.000   1.3743   0.05286   0.04603  -0.0857   0.0131   0.8916
  12.250   1.3696   0.05653   0.04984  -0.0845   0.0128   0.8931
  12.500   1.3696   0.05974   0.05320  -0.0836   0.0127   0.8947
  12.750   1.3691   0.06305   0.05666  -0.0829   0.0125   0.8962
  13.000   1.3691   0.06647   0.06023  -0.0823   0.0123   0.8978
  13.250   1.3698   0.06993   0.06383  -0.0819   0.0122   0.8995
  13.500   1.3718   0.07339   0.06743  -0.0816   0.0121   0.9012
  13.750   1.3749   0.07683   0.07101  -0.0814   0.0120   0.9029
  14.000   1.3789   0.08028   0.07461  -0.0813   0.0119   0.9046
  14.250   1.3828   0.08387   0.07837  -0.0813   0.0119   0.9063
  14.500   1.3854   0.08760   0.08228  -0.0814   0.0119   0.9079
  14.750   1.3861   0.09154   0.08645  -0.0816   0.0120   0.9097
  15.000   1.3844   0.09596   0.09109  -0.0822   0.0120   0.9117
  15.250   1.3807   0.10075   0.09610  -0.0832   0.0121   0.9138
  15.500   1.3750   0.10597   0.10155  -0.0848   0.0122   0.9160
  15.750   1.3674   0.11171   0.10753  -0.0869   0.0124   0.9181
  16.000   1.3583   0.11776   0.11381  -0.0899   0.0124   0.9204
  16.250   1.3472   0.12403   0.12030  -0.0932   0.0124   0.9229
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