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E209 (13.72%) (e209-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: E209 (13.72%) (e209-il)
Reynolds number: 200,000
Max Cl/Cd: 71.76 at α=8°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e209-il-200000.txt
Download as CSV file: xf-e209-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: E209  (13.72%)                                  
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -11.500  -0.5378   0.08253   0.07892  -0.0489   1.0000   0.0352
 -11.250  -0.5612   0.07420   0.07056  -0.0542   1.0000   0.0342
 -11.000  -0.5926   0.06596   0.06222  -0.0602   1.0000   0.0336
 -10.750  -0.6218   0.05964   0.05579  -0.0642   1.0000   0.0327
 -10.500  -0.6527   0.05469   0.05068  -0.0657   1.0000   0.0323
 -10.250  -0.6907   0.05066   0.04644  -0.0631   1.0000   0.0312
 -10.000  -0.7456   0.04606   0.04111  -0.0563   1.0000   0.0290
  -9.750  -0.7450   0.04464   0.03948  -0.0535   1.0000   0.0287
  -9.500  -0.7489   0.04157   0.03615  -0.0505   1.0000   0.0286
  -9.250  -0.7514   0.03881   0.03310  -0.0473   1.0000   0.0287
  -9.000  -0.7501   0.03590   0.02989  -0.0445   1.0000   0.0287
  -8.750  -0.7472   0.03244   0.02619  -0.0418   1.0000   0.0294
  -8.500  -0.7370   0.03092   0.02465  -0.0399   1.0000   0.0308
  -8.250  -0.7261   0.02950   0.02311  -0.0376   1.0000   0.0317
  -8.000  -0.7153   0.02797   0.02140  -0.0352   1.0000   0.0326
  -7.750  -0.7040   0.02645   0.01969  -0.0327   1.0000   0.0333
  -7.500  -0.6923   0.02514   0.01821  -0.0303   1.0000   0.0344
  -7.250  -0.6621   0.02385   0.01666  -0.0312   0.9968   0.0360
  -7.000  -0.6248   0.02185   0.01466  -0.0340   0.9916   0.0396
  -6.750  -0.5839   0.02070   0.01343  -0.0370   0.9854   0.0436
  -6.500  -0.5467   0.01922   0.01191  -0.0394   0.9783   0.0481
  -6.250  -0.5055   0.01827   0.01093  -0.0424   0.9717   0.0553
  -6.000  -0.4707   0.01701   0.00970  -0.0443   0.9619   0.0656
  -5.750  -0.4332   0.01568   0.00849  -0.0468   0.9543   0.0932
  -5.500  -0.3980   0.01441   0.00755  -0.0490   0.9447   0.1488
  -5.250  -0.3642   0.01339   0.00686  -0.0508   0.9340   0.2168
  -5.000  -0.3303   0.01246   0.00628  -0.0524   0.9234   0.3016
  -4.750  -0.2956   0.01187   0.00603  -0.0539   0.9126   0.3948
  -4.500  -0.2619   0.01170   0.00587  -0.0548   0.8984   0.4492
  -4.250  -0.2289   0.01158   0.00567  -0.0555   0.8832   0.4802
  -4.000  -0.1984   0.01150   0.00553  -0.0556   0.8663   0.5024
  -3.750  -0.1698   0.01147   0.00539  -0.0554   0.8485   0.5227
  -3.500  -0.1424   0.01148   0.00526  -0.0549   0.8313   0.5414
  -3.250  -0.1155   0.01149   0.00517  -0.0544   0.8151   0.5577
  -3.000  -0.0889   0.01150   0.00508  -0.0539   0.7999   0.5726
  -2.750  -0.0623   0.01151   0.00499  -0.0534   0.7858   0.5863
  -2.500  -0.0358   0.01151   0.00492  -0.0529   0.7727   0.5990
  -2.250  -0.0090   0.01151   0.00484  -0.0524   0.7608   0.6116
  -2.000   0.0172   0.01151   0.00478  -0.0519   0.7484   0.6241
  -1.750   0.0437   0.01152   0.00472  -0.0515   0.7370   0.6366
  -1.500   0.0705   0.01154   0.00466  -0.0512   0.7270   0.6494
  -1.250   0.0971   0.01153   0.00462  -0.0508   0.7171   0.6612
  -1.000   0.1236   0.01153   0.00461  -0.0504   0.7071   0.6734
  -0.750   0.1505   0.01154   0.00458  -0.0501   0.6987   0.6862
  -0.500   0.1769   0.01153   0.00457  -0.0497   0.6893   0.6994
  -0.250   0.2036   0.01155   0.00457  -0.0494   0.6811   0.7134
   0.000   0.2302   0.01154   0.00458  -0.0490   0.6728   0.7282
   0.250   0.2565   0.01155   0.00461  -0.0486   0.6650   0.7439
   0.500   0.2828   0.01155   0.00464  -0.0482   0.6573   0.7610
   0.750   0.3085   0.01156   0.00471  -0.0476   0.6498   0.7803
   1.000   0.3343   0.01157   0.00476  -0.0470   0.6424   0.8031
   1.250   0.3595   0.01159   0.00487  -0.0462   0.6355   0.8275
   1.500   0.3849   0.01161   0.00496  -0.0454   0.6282   0.8563
   1.750   0.4132   0.01169   0.00509  -0.0451   0.6218   0.8873
   2.000   0.4472   0.01178   0.00524  -0.0461   0.6140   0.9176
   2.250   0.4880   0.01194   0.00535  -0.0485   0.6075   0.9438
   2.500   0.5324   0.01206   0.00551  -0.0520   0.5993   0.9645
   2.750   0.5800   0.01222   0.00560  -0.0561   0.5925   0.9796
   3.000   0.6291   0.01231   0.00573  -0.0608   0.5839   0.9929
   3.250   0.6676   0.01243   0.00578  -0.0634   0.5774   1.0000
   3.500   0.6853   0.01255   0.00594  -0.0618   0.5698   1.0000
   3.750   0.7075   0.01271   0.00603  -0.0608   0.5636   1.0000
   4.000   0.7275   0.01285   0.00624  -0.0595   0.5553   1.0000
   4.250   0.7512   0.01301   0.00631  -0.0587   0.5485   1.0000
   4.500   0.7722   0.01316   0.00655  -0.0575   0.5398   1.0000
   4.750   0.7966   0.01331   0.00663  -0.0568   0.5327   1.0000
   5.000   0.8179   0.01345   0.00685  -0.0556   0.5235   1.0000
   5.250   0.8417   0.01359   0.00699  -0.0547   0.5156   1.0000
   5.500   0.8644   0.01370   0.00715  -0.0537   0.5062   1.0000
   5.750   0.8872   0.01384   0.00733  -0.0527   0.4967   1.0000
   6.000   0.9115   0.01395   0.00741  -0.0520   0.4876   1.0000
   6.250   0.9335   0.01405   0.00760  -0.0508   0.4764   1.0000
   6.500   0.9560   0.01417   0.00779  -0.0498   0.4652   1.0000
   6.750   0.9785   0.01427   0.00793  -0.0487   0.4533   1.0000
   7.000   1.0008   0.01439   0.00808  -0.0476   0.4407   1.0000
   7.250   1.0224   0.01452   0.00825  -0.0464   0.4265   1.0000
   7.500   1.0432   0.01466   0.00847  -0.0451   0.4104   1.0000
   7.750   1.0634   0.01484   0.00871  -0.0437   0.3916   1.0000
   8.000   1.0821   0.01508   0.00894  -0.0421   0.3701   1.0000
   8.250   1.0994   0.01541   0.00926  -0.0403   0.3426   1.0000
   8.500   1.1140   0.01589   0.00967  -0.0381   0.3087   1.0000
   8.750   1.1251   0.01660   0.01022  -0.0356   0.2685   1.0000
   9.000   1.1326   0.01755   0.01096  -0.0326   0.2272   1.0000
   9.250   1.1376   0.01864   0.01185  -0.0294   0.1915   1.0000
   9.500   1.1404   0.01974   0.01280  -0.0258   0.1627   1.0000
   9.750   1.1404   0.02093   0.01384  -0.0219   0.1399   1.0000
  10.000   1.1424   0.02213   0.01497  -0.0186   0.1199   1.0000
  10.250   1.1429   0.02349   0.01626  -0.0155   0.1039   1.0000
  10.500   1.1428   0.02499   0.01774  -0.0126   0.0904   1.0000
  10.750   1.1429   0.02662   0.01936  -0.0101   0.0795   1.0000
  11.000   1.1410   0.02853   0.02125  -0.0079   0.0708   1.0000
  11.250   1.1392   0.03060   0.02330  -0.0061   0.0635   1.0000
  11.500   1.1411   0.03255   0.02533  -0.0047   0.0567   1.0000
  11.750   1.1372   0.03508   0.02782  -0.0034   0.0519   1.0000
  12.000   1.1409   0.03710   0.02996  -0.0025   0.0470   1.0000
  12.250   1.1423   0.03937   0.03226  -0.0018   0.0437   1.0000
  12.500   1.1401   0.04207   0.03495  -0.0008   0.0406   1.0000
  12.750   1.1449   0.04419   0.03721  -0.0004   0.0375   1.0000
  13.000   1.1473   0.04655   0.03962   0.0000   0.0351   1.0000
  13.250   1.1478   0.04916   0.04220   0.0009   0.0325   1.0000
  13.500   1.1526   0.05144   0.04465   0.0012   0.0308   1.0000
  13.750   1.1571   0.05379   0.04710   0.0016   0.0291   1.0000
  14.000   1.1615   0.05615   0.04952   0.0019   0.0277   1.0000
  14.250   1.1675   0.05844   0.05180   0.0024   0.0265   1.0000
  14.500   1.1739   0.06106   0.05454   0.0033   0.0253   1.0000
  14.750   1.1727   0.06418   0.05788   0.0028   0.0242   1.0000
  15.000   1.1735   0.06728   0.06115   0.0024   0.0234   1.0000
  15.250   1.1738   0.07048   0.06450   0.0020   0.0227   1.0000
  15.500   1.1728   0.07384   0.06798   0.0012   0.0220   1.0000
  15.750   1.1717   0.07736   0.07164   0.0004   0.0214   1.0000
  16.000   1.1704   0.08100   0.07538  -0.0004   0.0209   1.0000
  16.250   1.1674   0.08503   0.07955  -0.0014   0.0206   1.0000
  16.500   1.1612   0.08973   0.08441  -0.0027   0.0203   1.0000
  16.750   1.1507   0.09516   0.09004  -0.0047   0.0202   1.0000
  17.000   1.1364   0.10133   0.09643  -0.0074   0.0201   1.0000
  17.250   1.1219   0.10770   0.10301  -0.0107   0.0201   1.0000
  17.500   1.1056   0.11467   0.11018  -0.0145   0.0201   1.0000
  17.750   1.0880   0.12219   0.11791  -0.0190   0.0202   1.0000
  18.000   1.0677   0.13073   0.12667  -0.0245   0.0203   1.0000
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