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EPPLER 553 AIRFOIL (e553-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 553 AIRFOIL (e553-il)
Reynolds number: 50,000
Max Cl/Cd: 17.88 at α=5.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e553-il-50000-n5.txt
Download as CSV file: xf-e553-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 553 AIRFOIL                              
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -13.500  -0.4541   0.10692   0.09949  -0.0630   1.0000   0.0447
 -13.250  -0.4791   0.09821   0.09072  -0.0673   1.0000   0.0440
 -13.000  -0.5054   0.09035   0.08274  -0.0711   1.0000   0.0433
 -12.750  -0.5298   0.08368   0.07593  -0.0741   1.0000   0.0430
 -12.500  -0.5494   0.07822   0.07033  -0.0762   1.0000   0.0429
 -12.250  -0.5660   0.07356   0.06551  -0.0775   1.0000   0.0432
 -12.000  -0.5787   0.06955   0.06134  -0.0780   1.0000   0.0437
 -11.750  -0.5879   0.06610   0.05772  -0.0780   1.0000   0.0443
 -11.500  -0.5934   0.06305   0.05449  -0.0774   1.0000   0.0450
 -11.250  -0.5971   0.06032   0.05151  -0.0765   1.0000   0.0461
 -11.000  -0.5915   0.05858   0.04978  -0.0749   1.0000   0.0479
 -10.750  -0.5890   0.05703   0.04825  -0.0733   1.0000   0.0503
 -10.500  -0.5854   0.05549   0.04661  -0.0712   1.0000   0.0528
 -10.250  -0.5807   0.05413   0.04502  -0.0688   1.0000   0.0555
 -10.000  -0.5769   0.05322   0.04429  -0.0661   1.0000   0.0584
  -9.750  -0.5796   0.05221   0.04329  -0.0631   1.0000   0.0615
  -9.500  -0.5830   0.05131   0.04227  -0.0597   1.0000   0.0652
  -9.250  -0.5901   0.05052   0.04162  -0.0561   1.0000   0.0677
  -9.000  -0.6016   0.04971   0.04088  -0.0523   1.0000   0.0702
  -8.750  -0.6041   0.04866   0.03979  -0.0500   0.9979   0.0752
  -8.500  -0.5855   0.04676   0.03795  -0.0521   0.9881   0.0853
  -8.250  -0.5734   0.04468   0.03594  -0.0538   0.9768   0.0974
  -8.000  -0.5650   0.04240   0.03371  -0.0555   0.9646   0.1114
  -7.750  -0.5575   0.03966   0.03110  -0.0578   0.9523   0.1323
  -7.500  -0.5526   0.03655   0.02829  -0.0602   0.9401   0.1639
  -7.250  -0.5466   0.03375   0.02625  -0.0618   0.9286   0.2315
  -7.000  -0.5223   0.03517   0.02837  -0.0596   0.9186   0.3427
  -6.750  -0.4860   0.03596   0.02881  -0.0615   0.9115   0.3983
  -6.500  -0.4635   0.03686   0.02943  -0.0605   0.9006   0.4264
  -6.250  -0.4223   0.03846   0.03075  -0.0609   0.8953   0.4515
  -6.000  -0.4001   0.03943   0.03154  -0.0588   0.8849   0.4679
  -5.750  -0.3605   0.04032   0.03217  -0.0593   0.8798   0.4849
  -5.500  -0.3367   0.04110   0.03281  -0.0572   0.8702   0.4951
  -5.250  -0.3022   0.04084   0.03229  -0.0586   0.8643   0.5077
  -5.000  -0.2826   0.04057   0.03183  -0.0578   0.8545   0.5168
  -4.750  -0.2496   0.04005   0.03108  -0.0592   0.8484   0.5246
  -4.500  -0.2296   0.03966   0.03053  -0.0585   0.8390   0.5313
  -4.250  -0.2007   0.03869   0.02931  -0.0604   0.8322   0.5392
  -4.000  -0.1794   0.03848   0.02898  -0.0595   0.8233   0.5437
  -3.750  -0.1506   0.03765   0.02792  -0.0611   0.8164   0.5506
  -3.500  -0.1297   0.03705   0.02715  -0.0613   0.8075   0.5560
  -3.250  -0.1008   0.03671   0.02668  -0.0616   0.8007   0.5600
  -3.000  -0.0763   0.03621   0.02602  -0.0621   0.7929   0.5653
  -2.750  -0.0508   0.03548   0.02509  -0.0635   0.7850   0.5714
  -2.500  -0.0190   0.03517   0.02466  -0.0642   0.7794   0.5747
  -2.250  -0.0014   0.03503   0.02443  -0.0632   0.7698   0.5788
  -2.000   0.0352   0.03436   0.02357  -0.0656   0.7651   0.5846
  -1.750   0.0500   0.03425   0.02338  -0.0646   0.7548   0.5889
  -1.500   0.0834   0.03392   0.02296  -0.0656   0.7497   0.5925
  -1.250   0.0999   0.03394   0.02291  -0.0645   0.7402   0.5968
  -1.000   0.1334   0.03349   0.02230  -0.0665   0.7346   0.6026
  -0.750   0.1536   0.03351   0.02228  -0.0658   0.7264   0.6063
  -0.500   0.1799   0.03340   0.02212  -0.0658   0.7197   0.6101
  -0.250   0.2159   0.03304   0.02165  -0.0675   0.7153   0.6151
   0.000   0.2302   0.03327   0.02183  -0.0667   0.7052   0.6206
   0.250   0.2635   0.03304   0.02156  -0.0674   0.7007   0.6243
   0.500   0.2760   0.03342   0.02195  -0.0658   0.6911   0.6285
   0.750   0.3089   0.03321   0.02167  -0.0671   0.6859   0.6341
   1.000   0.3282   0.03348   0.02192  -0.0666   0.6780   0.6388
   1.250   0.3522   0.03358   0.02204  -0.0662   0.6714   0.6433
   1.500   0.3896   0.03329   0.02169  -0.0678   0.6675   0.6490
   1.750   0.3983   0.03402   0.02244  -0.0662   0.6572   0.6542
   2.000   0.4306   0.03388   0.02231  -0.0667   0.6528   0.6590
   2.250   0.4424   0.03456   0.02302  -0.0653   0.6438   0.6645
   2.500   0.4723   0.03461   0.02306  -0.0661   0.6383   0.6709
   2.750   0.5086   0.03435   0.02282  -0.0671   0.6349   0.6764
   3.000   0.5105   0.03551   0.02404  -0.0646   0.6240   0.6822
   3.250   0.5461   0.03532   0.02388  -0.0657   0.6201   0.6889
   3.500   0.5483   0.03651   0.02515  -0.0631   0.6103   0.6946
   3.750   0.5809   0.03652   0.02518  -0.0641   0.6055   0.7027
   4.250   0.6100   0.03792   0.02673  -0.0616   0.5909   0.7166
   4.500   0.6470   0.03764   0.02653  -0.0626   0.5875   0.7248
   4.750   0.6384   0.03946   0.02844  -0.0592   0.5764   0.7326
   5.000   0.6711   0.03931   0.02840  -0.0597   0.5725   0.7418
   5.500   0.6950   0.04120   0.03049  -0.0569   0.5574   0.7616
   5.750   0.7299   0.04083   0.03024  -0.0574   0.5539   0.7738
   6.000   0.7178   0.04328   0.03282  -0.0543   0.5420   0.7855
   6.250   0.7543   0.04262   0.03230  -0.0546   0.5391   0.8012
   6.500   0.7378   0.04550   0.03532  -0.0516   0.5265   0.8163
   6.750   0.7707   0.04474   0.03476  -0.0510   0.5234   0.8383
   7.000   0.7543   0.04774   0.03793  -0.0483   0.5107   0.8658
   7.250   0.7896   0.04668   0.03709  -0.0482   0.5074   0.9654
   7.750   0.8271   0.04925   0.03975  -0.0496   0.4913   1.0000
   8.250   0.8487   0.05287   0.04345  -0.0495   0.4731   1.0000
   8.750   0.8899   0.05445   0.04517  -0.0493   0.4584   1.0000
   9.000   0.8809   0.05803   0.04881  -0.0488   0.4451   1.0000
   9.500   0.9128   0.06022   0.05116  -0.0480   0.4285   1.0000
  10.000   0.9355   0.06325   0.05437  -0.0471   0.4099   1.0000
  10.250   0.9357   0.06602   0.05722  -0.0468   0.3980   1.0000
  10.750   0.9698   0.06750   0.05892  -0.0457   0.3811   1.0000
  11.250   0.9581   0.07472   0.06631  -0.0456   0.3548   1.0000
  11.500   0.9979   0.07225   0.06401  -0.0443   0.3502   1.0000
  11.750   0.9904   0.07612   0.06796  -0.0444   0.3366   1.0000
  12.250   1.0315   0.07607   0.06818  -0.0428   0.3191   1.0000
  12.500   1.0235   0.08010   0.07230  -0.0432   0.3055   1.0000
  12.750   1.0199   0.08366   0.07594  -0.0435   0.2929   1.0000
  13.250   1.0640   0.08279   0.07531  -0.0416   0.2741   1.0000
  13.500   1.0589   0.08663   0.07925  -0.0421   0.2613   1.0000
  13.750   1.0627   0.08911   0.08182  -0.0423   0.2496   1.0000
  14.000   1.0907   0.08757   0.08037  -0.0409   0.2395   1.0000
  14.250   1.1139   0.08683   0.07966  -0.0398   0.2279   1.0000
  14.500   1.1041   0.09161   0.08454  -0.0409   0.2157   1.0000
  14.750   1.1029   0.09506   0.08806  -0.0416   0.2042   1.0000
  15.000   1.1128   0.09658   0.08960  -0.0414   0.1929   1.0000
  15.250   1.1279   0.09716   0.09016  -0.0409   0.1815   1.0000
  15.500   1.1243   0.10116   0.09424  -0.0420   0.1709   1.0000
  15.750   1.1165   0.10604   0.09921  -0.0436   0.1614   1.0000
  16.000   1.1258   0.10775   0.10088  -0.0437   0.1516   1.0000
  16.250   1.1242   0.11155   0.10474  -0.0450   0.1425   1.0000
  16.500   1.1156   0.11689   0.11018  -0.0471   0.1349   1.0000
  16.750   1.1309   0.11736   0.11052  -0.0467   0.1259   1.0000
  17.000   1.1069   0.12609   0.11953  -0.0510   0.1202   1.0000
  17.250   1.1243   0.12609   0.11939  -0.0504   0.1122   1.0000
  17.500   1.0944   0.13649   0.13009  -0.0559   0.1078   1.0000
  17.750   1.1208   0.13445   0.12791  -0.0543   0.1002   1.0000
  18.000   1.0840   0.14690   0.14062  -0.0613   0.0972   1.0000
  18.250   1.0282   0.16551   0.15933  -0.0721   0.0937   1.0000
  18.500   1.0903   0.15352   0.14729  -0.0647   0.0870   1.0000
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