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E230 (9.96%) (e230-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: E230 (9.96%) (e230-il)
Reynolds number: 200,000
Max Cl/Cd: 38.7 at α=5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e230-il-200000-n5.txt
Download as CSV file: xf-e230-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: E230  (9.96%)                                   
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -13.000  -0.8474   0.11284   0.10950   0.0344   1.0000   0.0113
 -12.750  -0.8805   0.09823   0.09482   0.0256   1.0000   0.0109
 -12.500  -0.9093   0.08594   0.08238   0.0170   1.0000   0.0106
 -12.250  -0.9357   0.07564   0.07189   0.0092   1.0000   0.0104
 -12.000  -0.9593   0.06742   0.06347   0.0033   1.0000   0.0102
 -11.750  -0.9767   0.06160   0.05745  -0.0003   1.0000   0.0103
 -11.500  -0.9956   0.05639   0.05200  -0.0022   1.0000   0.0102
 -11.250  -1.0122   0.05221   0.04758  -0.0024   1.0000   0.0102
 -11.000  -1.0254   0.04880   0.04392  -0.0011   1.0000   0.0103
 -10.750  -1.0357   0.04591   0.04078   0.0011   1.0000   0.0104
 -10.500  -1.0429   0.04319   0.03779   0.0040   1.0000   0.0105
 -10.250  -1.0449   0.04051   0.03479   0.0067   1.0000   0.0106
 -10.000  -1.0410   0.03787   0.03182   0.0088   1.0000   0.0106
  -9.750  -1.0328   0.03542   0.02905   0.0107   1.0000   0.0107
  -9.500  -1.0211   0.03321   0.02655   0.0124   1.0000   0.0107
  -9.250  -1.0068   0.03115   0.02424   0.0138   1.0000   0.0109
  -9.000  -0.9904   0.02934   0.02217   0.0152   1.0000   0.0110
  -8.750  -0.9729   0.02767   0.02031   0.0164   1.0000   0.0112
  -8.500  -0.9546   0.02616   0.01863   0.0176   1.0000   0.0114
  -8.250  -0.9357   0.02480   0.01712   0.0188   1.0000   0.0117
  -8.000  -0.9164   0.02357   0.01576   0.0199   1.0000   0.0119
  -7.750  -0.8980   0.02228   0.01437   0.0211   1.0000   0.0122
  -7.500  -0.8793   0.02108   0.01307   0.0223   1.0000   0.0126
  -7.250  -0.8588   0.02012   0.01203   0.0233   1.0000   0.0133
  -7.000  -0.8370   0.01931   0.01113   0.0241   1.0000   0.0145
  -6.750  -0.8147   0.01855   0.01026   0.0249   1.0000   0.0156
  -6.500  -0.7924   0.01774   0.00935   0.0258   1.0000   0.0167
  -6.250  -0.7696   0.01699   0.00852   0.0265   1.0000   0.0183
  -6.000  -0.7460   0.01633   0.00778   0.0272   1.0000   0.0212
  -5.750  -0.7233   0.01556   0.00705   0.0280   1.0000   0.0309
  -5.500  -0.7013   0.01473   0.00639   0.0288   1.0000   0.0605
  -5.250  -0.6796   0.01389   0.00585   0.0295   1.0000   0.1085
  -5.000  -0.6569   0.01324   0.00541   0.0301   1.0000   0.1517
  -4.750  -0.6336   0.01271   0.00504   0.0307   1.0000   0.1905
  -4.500  -0.6116   0.01211   0.00471   0.0314   1.0000   0.2442
  -4.250  -0.5896   0.01161   0.00443   0.0322   1.0000   0.2945
  -4.000  -0.5644   0.01119   0.00418   0.0324   0.9899   0.3390
  -3.500  -0.4992   0.01054   0.00376   0.0300   0.9570   0.4195
  -3.250  -0.4707   0.01027   0.00358   0.0299   0.9416   0.4582
  -3.000  -0.4452   0.01004   0.00345   0.0305   0.9259   0.4959
  -2.750  -0.4213   0.00983   0.00333   0.0315   0.9106   0.5322
  -2.500  -0.3983   0.00962   0.00322   0.0328   0.8956   0.5679
  -2.250  -0.3754   0.00944   0.00312   0.0341   0.8808   0.6034
  -2.000  -0.3526   0.00926   0.00304   0.0355   0.8663   0.6389
  -1.750  -0.3293   0.00909   0.00297   0.0368   0.8519   0.6748
  -1.500  -0.3053   0.00895   0.00289   0.0380   0.8375   0.7097
  -1.250  -0.2802   0.00883   0.00285   0.0390   0.8229   0.7432
  -1.000  -0.2538   0.00874   0.00282   0.0398   0.8081   0.7752
  -0.750  -0.2256   0.00869   0.00281   0.0402   0.7928   0.8051
  -0.500  -0.1953   0.00868   0.00281   0.0401   0.7769   0.8320
  -0.250  -0.1628   0.00871   0.00283   0.0396   0.7601   0.8552
   0.000  -0.1287   0.00878   0.00286   0.0387   0.7426   0.8748
   0.250  -0.0934   0.00887   0.00291   0.0375   0.7244   0.8909
   0.500  -0.0585   0.00898   0.00296   0.0364   0.7048   0.9047
   0.750  -0.0248   0.00909   0.00302   0.0355   0.6843   0.9174
   1.000   0.0119   0.00922   0.00307   0.0339   0.6628   0.9265
   1.250   0.0463   0.00936   0.00314   0.0327   0.6396   0.9358
   1.500   0.0775   0.00951   0.00322   0.0323   0.6160   0.9459
   1.750   0.1141   0.00967   0.00330   0.0306   0.5895   0.9522
   2.000   0.1462   0.00983   0.00338   0.0298   0.5626   0.9607
   2.250   0.1820   0.00999   0.00347   0.0282   0.5331   0.9668
   2.500   0.2150   0.01017   0.00356   0.0271   0.5034   0.9738
   2.750   0.2509   0.01034   0.00364   0.0253   0.4705   0.9792
   3.000   0.2846   0.01054   0.00377   0.0240   0.4362   0.9851
   3.250   0.3214   0.01072   0.00386   0.0219   0.4000   0.9895
   3.500   0.3565   0.01096   0.00399   0.0202   0.3619   0.9943
   3.750   0.3926   0.01121   0.00413   0.0181   0.3183   0.9982
   4.000   0.4223   0.01155   0.00429   0.0173   0.2692   1.0000
   4.250   0.4461   0.01197   0.00449   0.0176   0.2163   1.0000
   4.500   0.4698   0.01240   0.00475   0.0180   0.1725   1.0000
   4.750   0.4935   0.01280   0.00505   0.0185   0.1407   1.0000
   5.000   0.5167   0.01335   0.00540   0.0189   0.1002   1.0000
   5.250   0.5395   0.01396   0.00582   0.0194   0.0659   1.0000
   5.500   0.5622   0.01458   0.00635   0.0200   0.0401   1.0000
   5.750   0.5847   0.01525   0.00697   0.0207   0.0272   1.0000
   6.000   0.6073   0.01585   0.00763   0.0215   0.0232   1.0000
   6.250   0.6294   0.01649   0.00832   0.0223   0.0211   1.0000
   6.500   0.6510   0.01722   0.00914   0.0231   0.0198   1.0000
   6.750   0.6724   0.01789   0.00994   0.0241   0.0184   1.0000
   7.000   0.6932   0.01860   0.01073   0.0250   0.0172   1.0000
   7.250   0.7132   0.01943   0.01164   0.0260   0.0163   1.0000
   7.500   0.7318   0.02046   0.01274   0.0271   0.0157   1.0000
   7.750   0.7490   0.02169   0.01404   0.0285   0.0153   1.0000
   8.000   0.7672   0.02276   0.01523   0.0298   0.0150   1.0000
   8.250   0.7848   0.02393   0.01656   0.0311   0.0148   1.0000
   8.500   0.8016   0.02524   0.01802   0.0325   0.0145   1.0000
   8.750   0.8178   0.02666   0.01961   0.0340   0.0143   1.0000
   9.000   0.8329   0.02823   0.02137   0.0355   0.0141   1.0000
   9.250   0.8464   0.03002   0.02339   0.0370   0.0139   1.0000
   9.500   0.8579   0.03195   0.02556   0.0387   0.0138   1.0000
   9.750   0.8672   0.03395   0.02785   0.0404   0.0136   1.0000
  10.000   0.8736   0.03602   0.03018   0.0422   0.0133   1.0000
  10.250   0.8772   0.03812   0.03252   0.0441   0.0130   1.0000
  10.500   0.8783   0.04011   0.03469   0.0460   0.0126   1.0000
  10.750   0.8705   0.04255   0.03736   0.0484   0.0126   1.0000
  11.000   0.8576   0.04513   0.04014   0.0504   0.0126   1.0000
  11.250   0.8476   0.04793   0.04309   0.0507   0.0124   1.0000
  11.500   0.8339   0.05181   0.04715   0.0495   0.0123   1.0000
  11.750   0.8177   0.05680   0.05235   0.0467   0.0123   1.0000
  12.000   0.7929   0.06427   0.06005   0.0413   0.0125   1.0000
  12.250   0.7522   0.07667   0.07273   0.0318   0.0130   1.0000
  12.500   0.6906   0.09683   0.09304   0.0189   0.0140   1.0000
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