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EPPLER 434 AIRFOIL (e434-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 434 AIRFOIL (e434-il)
Reynolds number: 100,000
Max Cl/Cd: 52.1 at α=9.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e434-il-100000.txt
Download as CSV file: xf-e434-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 434 AIRFOIL                              
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.2941   0.11126   0.10702  -0.0523   0.9821   0.0768
  -8.750  -0.3015   0.10839   0.10420  -0.0612   0.9742   0.0786
  -8.500  -0.3155   0.10546   0.10132  -0.0692   0.9649   0.0790
  -8.250  -0.2681   0.09941   0.09521  -0.0630   0.9662   0.0826
  -8.000  -0.2545   0.09589   0.09170  -0.0659   0.9612   0.0864
  -7.750  -0.2539   0.09265   0.08847  -0.0702   0.9546   0.0897
  -7.500  -0.2750   0.08942   0.08525  -0.0791   0.9442   0.0921
  -7.250  -0.3006   0.08760   0.08327  -0.0823   0.9319   0.0928
  -7.000  -0.2689   0.08212   0.07797  -0.0802   0.9313   0.0955
  -6.750  -0.2515   0.07897   0.07481  -0.0812   0.9277   0.1001
  -6.500  -0.2634   0.07700   0.07282  -0.0801   0.9183   0.1030
  -6.250  -0.2951   0.07687   0.07215  -0.0828   0.9068   0.1076
  -6.000  -0.2731   0.07111   0.06675  -0.0814   0.9043   0.1105
  -5.750  -0.2552   0.06816   0.06376  -0.0822   0.9003   0.1164
  -5.500  -0.2676   0.06619   0.06147  -0.0818   0.8921   0.1241
  -5.250  -0.2541   0.06348   0.05891  -0.0800   0.8877   0.1291
  -5.000  -0.2365   0.06027   0.05548  -0.0823   0.8837   0.1418
  -4.750  -0.2412   0.05927   0.05427  -0.0797   0.8764   0.1554
  -4.500  -0.2269   0.05695   0.05206  -0.0783   0.8718   0.1643
  -3.750  -0.1534   0.04246   0.03515  -0.0786   0.8584   0.0679
  -3.500  -0.1233   0.03948   0.03178  -0.0787   0.8549   0.0598
  -3.250  -0.0829   0.03709   0.02853  -0.0794   0.8522   0.0542
  -3.000  -0.0656   0.03590   0.02711  -0.0778   0.8469   0.0536
  -2.750  -0.0446   0.03489   0.02580  -0.0764   0.8418   0.0542
  -2.500  -0.0118   0.03345   0.02434  -0.0773   0.8383   0.0598
  -2.250   0.0289   0.03218   0.02294  -0.0788   0.8357   0.0677
  -2.000   0.0324   0.03217   0.02301  -0.0753   0.8285   0.0741
  -1.750   0.0581   0.03132   0.02229  -0.0749   0.8240   0.0995
  -1.500   0.0779   0.02791   0.02155  -0.0733   0.8213   0.5957
  -1.250   0.2576   0.02845   0.02197  -0.0948   0.8244   1.0000
  -1.000   0.2949   0.02845   0.02171  -0.0968   0.8210   1.0000
  -0.750   0.2613   0.02945   0.02272  -0.0874   0.8105   1.0000
  -0.500   0.2908   0.02958   0.02265  -0.0880   0.8061   1.0000
  -0.250   0.2711   0.03038   0.02341  -0.0809   0.7970   1.0000
   0.000   0.2907   0.03064   0.02351  -0.0798   0.7915   1.0000
   0.250   0.3345   0.03064   0.02331  -0.0825   0.7886   1.0000
   0.500   0.2973   0.03164   0.02432  -0.0728   0.7770   1.0000
   0.750   0.3376   0.03170   0.02420  -0.0747   0.7736   1.0000
   1.000   0.3198   0.03269   0.02515  -0.0684   0.7631   1.0000
   1.250   0.3566   0.03281   0.02513  -0.0699   0.7589   1.0000
   1.500   0.3574   0.03374   0.02599  -0.0666   0.7497   1.0000
   1.750   0.3897   0.03394   0.02608  -0.0674   0.7444   1.0000
   2.000   0.4250   0.03414   0.02619  -0.0686   0.7401   1.0000
   2.250   0.4291   0.03508   0.02708  -0.0660   0.7299   1.0000
   2.500   0.4733   0.03494   0.02687  -0.0681   0.7267   1.0000
   2.750   0.4726   0.03617   0.02806  -0.0651   0.7152   1.0000
   3.000   0.5158   0.03596   0.02780  -0.0670   0.7117   1.0000
   3.250   0.5188   0.03715   0.02897  -0.0645   0.7003   1.0000
   3.500   0.5615   0.03686   0.02866  -0.0662   0.6966   1.0000
   3.750   0.5669   0.03804   0.02983  -0.0640   0.6853   1.0000
   4.000   0.6094   0.03764   0.02942  -0.0655   0.6815   1.0000
   4.250   0.6160   0.03883   0.03060  -0.0635   0.6701   1.0000
   4.500   0.6593   0.03825   0.03004  -0.0650   0.6663   1.0000
   4.750   0.7087   0.03730   0.02913  -0.0670   0.6642   1.0000
   5.000   0.7118   0.03859   0.03044  -0.0646   0.6513   1.0000
   5.250   0.7596   0.03751   0.02941  -0.0662   0.6487   1.0000
   5.500   0.7669   0.03859   0.03051  -0.0641   0.6363   1.0000
   5.750   0.7768   0.03958   0.03156  -0.0624   0.6243   1.0000
   6.000   0.8250   0.03814   0.03021  -0.0637   0.6215   1.0000
   6.250   0.8808   0.03602   0.02820  -0.0655   0.6202   1.0000
   6.500   0.9432   0.03365   0.02595  -0.0684   0.6192   1.0000
   6.750   0.9028   0.03756   0.02986  -0.0618   0.5960   1.0000
   7.000   0.9574   0.03516   0.02761  -0.0632   0.5938   1.0000
   7.250   1.0239   0.03228   0.02488  -0.0663   0.5919   1.0000
   7.500   1.1059   0.02908   0.02187  -0.0720   0.5895   1.0000
   7.750   1.1196   0.02908   0.02197  -0.0695   0.5767   1.0000
   8.000   1.1433   0.02861   0.02162  -0.0683   0.5645   1.0000
   8.250   1.1816   0.02750   0.02062  -0.0688   0.5525   1.0000
   8.500   1.2187   0.02649   0.01970  -0.0693   0.5385   1.0000
   8.750   1.2462   0.02590   0.01920  -0.0684   0.5223   1.0000
   9.000   1.2705   0.02547   0.01881  -0.0672   0.5043   1.0000
   9.250   1.3003   0.02496   0.01828  -0.0668   0.4842   1.0000
   9.500   1.3038   0.02543   0.01881  -0.0629   0.4637   1.0000
   9.750   1.3178   0.02565   0.01900  -0.0606   0.4415   1.0000
  10.000   1.3245   0.02626   0.01959  -0.0575   0.4189   1.0000
  10.250   1.3331   0.02691   0.02016  -0.0547   0.3955   1.0000
  10.500   1.3350   0.02793   0.02115  -0.0515   0.3726   1.0000
  10.750   1.3404   0.02893   0.02204  -0.0488   0.3495   1.0000
  11.000   1.3391   0.03031   0.02342  -0.0456   0.3272   1.0000
  11.250   1.3404   0.03169   0.02468  -0.0429   0.3055   1.0000
  11.500   1.3390   0.03333   0.02629  -0.0402   0.2843   1.0000
  11.750   1.3373   0.03507   0.02798  -0.0377   0.2640   1.0000
  12.000   1.3375   0.03685   0.02961  -0.0355   0.2444   1.0000
  12.250   1.3344   0.03892   0.03171  -0.0334   0.2257   1.0000
  12.500   1.3321   0.04105   0.03381  -0.0314   0.2078   1.0000
  12.750   1.3301   0.04327   0.03599  -0.0297   0.1909   1.0000
  13.000   1.3286   0.04556   0.03822  -0.0281   0.1749   1.0000
  13.250   1.3274   0.04795   0.04054  -0.0267   0.1599   1.0000
  13.500   1.3265   0.05042   0.04298  -0.0255   0.1460   1.0000
  13.750   1.3248   0.05304   0.04561  -0.0244   0.1331   1.0000
  14.000   1.3242   0.05570   0.04832  -0.0234   0.1214   1.0000
  14.250   1.3247   0.05841   0.05107  -0.0225   0.1107   1.0000
  14.500   1.3269   0.06107   0.05374  -0.0217   0.1010   1.0000
  14.750   1.3333   0.06346   0.05605  -0.0211   0.0917   1.0000
  15.000   1.3309   0.06659   0.05940  -0.0206   0.0850   1.0000
  15.250   1.3374   0.06925   0.06209  -0.0200   0.0780   1.0000
  15.500   1.3383   0.07221   0.06516  -0.0197   0.0724   1.0000
  15.750   1.3440   0.07519   0.06824  -0.0192   0.0670   1.0000
  16.000   1.3394   0.07886   0.07215  -0.0192   0.0632   1.0000
  16.250   1.3500   0.08149   0.07472  -0.0189   0.0582   1.0000
  16.500   1.3381   0.08613   0.07972  -0.0194   0.0561   1.0000
  16.750   1.3294   0.09055   0.08439  -0.0200   0.0537   1.0000
  17.000   1.3431   0.09302   0.08673  -0.0198   0.0492   1.0000
  17.250   1.3249   0.09862   0.09269  -0.0212   0.0486   1.0000
  17.500   1.3056   0.10470   0.09911  -0.0232   0.0479   1.0000
  17.750   1.2857   0.11127   0.10598  -0.0258   0.0474   1.0000
  18.000   1.2645   0.11840   0.11337  -0.0290   0.0471   1.0000
  18.250   1.2419   0.12618   0.12141  -0.0330   0.0471   1.0000
  18.500   1.2176   0.13474   0.13020  -0.0379   0.0475   1.0000
  18.750   1.1927   0.14400   0.13966  -0.0434   0.0482   1.0000
  19.000   1.1681   0.15382   0.14961  -0.0495   0.0488   1.0000
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