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EPPLER 858 AIRFOIL (e858-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 858 AIRFOIL (e858-il)
Reynolds number: 200,000
Max Cl/Cd: 48.72 at α=8.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e858-il-200000.txt
Download as CSV file: xf-e858-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 858 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
  ------ -------- --------- --------- -------- -------- --------
 -16.250  -0.6380   0.08927   0.08419  -0.0790   1.0000   0.0314
 -16.000  -0.6640   0.08264   0.07733  -0.0823   1.0000   0.0313
 -15.750  -0.6774   0.07812   0.07268  -0.0839   1.0000   0.0314
 -15.500  -0.6754   0.07587   0.07045  -0.0841   1.0000   0.0318
 -15.250  -0.6833   0.07239   0.06688  -0.0849   1.0000   0.0320
 -15.000  -0.6861   0.06978   0.06425  -0.0852   1.0000   0.0326
 -14.750  -0.6948   0.06658   0.06095  -0.0856   1.0000   0.0328
 -14.500  -0.7023   0.06367   0.05794  -0.0857   1.0000   0.0331
 -14.250  -0.7119   0.06079   0.05496  -0.0858   1.0000   0.0337
 -14.000  -0.7203   0.05815   0.05221  -0.0855   1.0000   0.0340
 -13.750  -0.7286   0.05567   0.04961  -0.0847   1.0000   0.0343
 -13.500  -0.7404   0.05322   0.04701  -0.0839   1.0000   0.0347
 -13.250  -0.7480   0.05132   0.04503  -0.0823   1.0000   0.0351
 -13.000  -0.7428   0.05057   0.04441  -0.0800   1.0000   0.0357
 -12.750  -0.7473   0.04947   0.04335  -0.0778   0.9999   0.0362
 -12.500  -0.7169   0.04743   0.04125  -0.0821   0.9951   0.0375
 -12.250  -0.6894   0.04519   0.03885  -0.0863   0.9898   0.0389
 -12.000  -0.6563   0.04379   0.03754  -0.0891   0.9843   0.0406
 -11.750  -0.6265   0.04187   0.03557  -0.0929   0.9788   0.0427
 -11.500  -0.5988   0.04001   0.03372  -0.0959   0.9713   0.0449
 -11.250  -0.5748   0.03803   0.03173  -0.0986   0.9615   0.0474
 -11.000  -0.5544   0.03593   0.02965  -0.1010   0.9500   0.0504
 -10.750  -0.5356   0.03373   0.02740  -0.1033   0.9374   0.0544
 -10.500  -0.5165   0.03162   0.02532  -0.1056   0.9250   0.0582
 -10.250  -0.4980   0.02931   0.02301  -0.1080   0.9135   0.0632
 -10.000  -0.4812   0.02706   0.02073  -0.1102   0.9001   0.0685
  -9.750  -0.4617   0.02515   0.01878  -0.1120   0.8845   0.0754
  -9.500  -0.4288   0.02340   0.01697  -0.1154   0.8696   0.0859
  -9.250  -0.3868   0.02164   0.01522  -0.1206   0.8545   0.0990
  -9.000  -0.3357   0.02016   0.01371  -0.1272   0.8373   0.1167
  -8.750  -0.2952   0.01909   0.01255  -0.1312   0.8165   0.1356
  -8.500  -0.2687   0.01818   0.01163  -0.1325   0.7952   0.1540
  -8.250  -0.2466   0.01751   0.01089  -0.1324   0.7753   0.1747
  -8.000  -0.2280   0.01683   0.01022  -0.1316   0.7574   0.1986
  -7.750  -0.2136   0.01629   0.00973  -0.1297   0.7401   0.2266
  -7.500  -0.1969   0.01591   0.00943  -0.1281   0.7245   0.2605
  -7.250  -0.1745   0.01579   0.00927  -0.1273   0.7104   0.2938
  -7.000  -0.1533   0.01584   0.00929  -0.1259   0.6958   0.3180
  -6.750  -0.1303   0.01599   0.00935  -0.1248   0.6825   0.3371
  -6.500  -0.1045   0.01620   0.00940  -0.1241   0.6702   0.3529
  -6.250  -0.0829   0.01638   0.00940  -0.1228   0.6579   0.3667
  -6.000  -0.0547   0.01672   0.00969  -0.1224   0.6471   0.3770
  -5.750  -0.0334   0.01685   0.00969  -0.1210   0.6356   0.3879
  -5.500  -0.0052   0.01721   0.01000  -0.1206   0.6253   0.3963
  -5.250   0.0167   0.01736   0.01003  -0.1193   0.6146   0.4059
  -5.000   0.0433   0.01755   0.01015  -0.1187   0.6050   0.4129
  -4.750   0.0682   0.01780   0.01036  -0.1178   0.5955   0.4202
  -4.500   0.0918   0.01790   0.01025  -0.1169   0.5865   0.4285
  -4.250   0.1198   0.01803   0.01035  -0.1167   0.5784   0.4342
  -4.000   0.1434   0.01817   0.01050  -0.1155   0.5697   0.4402
  -3.750   0.1693   0.01829   0.01044  -0.1151   0.5620   0.4475
  -3.500   0.1942   0.01830   0.01035  -0.1145   0.5542   0.4535
  -3.250   0.2182   0.01837   0.01046  -0.1135   0.5462   0.4585
  -3.000   0.2456   0.01854   0.01050  -0.1132   0.5394   0.4646
  -2.750   0.2701   0.01863   0.01048  -0.1126   0.5326   0.4714
  -2.500   0.2939   0.01856   0.01036  -0.1118   0.5258   0.4767
  -2.250   0.3206   0.01861   0.01036  -0.1114   0.5198   0.4810
  -2.000   0.3482   0.01875   0.01041  -0.1114   0.5140   0.4858
  -1.750   0.3712   0.01873   0.01036  -0.1105   0.5079   0.4907
  -1.500   0.3964   0.01872   0.01022  -0.1100   0.5022   0.4954
  -1.250   0.4247   0.01871   0.01007  -0.1102   0.4968   0.4996
  -1.000   0.4491   0.01875   0.01013  -0.1096   0.4916   0.5034
  -0.750   0.4728   0.01876   0.01015  -0.1088   0.4864   0.5072
  -0.500   0.4985   0.01880   0.01012  -0.1084   0.4816   0.5117
  -0.250   0.5268   0.01892   0.01009  -0.1086   0.4773   0.5169
   0.000   0.5550   0.01908   0.01014  -0.1088   0.4731   0.5213
   0.250   0.5769   0.01905   0.01019  -0.1077   0.4687   0.5250
   0.500   0.6011   0.01910   0.01025  -0.1071   0.4643   0.5289
   0.750   0.6270   0.01918   0.01028  -0.1067   0.4602   0.5334
   1.000   0.6562   0.01937   0.01033  -0.1071   0.4564   0.5389
   1.250   0.6834   0.01962   0.01050  -0.1072   0.4528   0.5438
   1.500   0.7046   0.01964   0.01062  -0.1060   0.4492   0.5480
   1.750   0.7280   0.01976   0.01078  -0.1053   0.4456   0.5524
   2.000   0.7533   0.01990   0.01090  -0.1049   0.4422   0.5575
   2.250   0.7805   0.02006   0.01099  -0.1049   0.4391   0.5631
   2.500   0.8109   0.02031   0.01113  -0.1056   0.4359   0.5687
   2.750   0.8351   0.02056   0.01145  -0.1051   0.4328   0.5740
   3.000   0.8542   0.02072   0.01169  -0.1036   0.4297   0.5795
   3.250   0.8762   0.02092   0.01191  -0.1026   0.4265   0.5855
   3.500   0.9001   0.02111   0.01209  -0.1021   0.4236   0.5913
   3.750   0.9254   0.02127   0.01229  -0.1018   0.4210   0.5973
   4.000   0.9532   0.02152   0.01250  -0.1020   0.4185   0.6048
   4.250   0.9858   0.02197   0.01285  -0.1032   0.4158   0.6129
   4.500   1.0053   0.02226   0.01327  -0.1019   0.4134   0.6196
   4.750   1.0208   0.02249   0.01363  -0.0998   0.4107   0.6272
   5.000   1.0392   0.02277   0.01395  -0.0983   0.4079   0.6357
   5.250   1.0591   0.02299   0.01428  -0.0971   0.4053   0.6444
   5.500   1.0820   0.02327   0.01458  -0.0964   0.4029   0.6554
   5.750   1.1070   0.02351   0.01487  -0.0961   0.4007   0.6664
   6.250   1.1685   0.02440   0.01576  -0.0979   0.3962   0.6945
   6.500   1.1797   0.02474   0.01628  -0.0952   0.3942   0.7099
   6.750   1.1887   0.02507   0.01681  -0.0921   0.3919   0.7294
   7.000   1.1967   0.02535   0.01730  -0.0888   0.3895   0.7544
   7.250   1.2070   0.02563   0.01777  -0.0859   0.3873   0.7921
   7.500   1.2359   0.02582   0.01831  -0.0864   0.3850   0.9123
   7.750   1.2644   0.02625   0.01869  -0.0872   0.3829   1.0000
   8.000   1.2922   0.02669   0.01905  -0.0878   0.3809   1.0000
   8.250   1.3262   0.02722   0.01949  -0.0894   0.3790   1.0000
   8.500   1.3509   0.02807   0.02031  -0.0896   0.3767   1.0000
   8.750   1.3451   0.02873   0.02110  -0.0843   0.3749   1.0000
   9.000   1.3431   0.02950   0.02199  -0.0799   0.3727   1.0000
   9.250   1.3448   0.03035   0.02292  -0.0763   0.3705   1.0000
   9.500   1.3491   0.03119   0.02383  -0.0733   0.3684   1.0000
   9.750   1.3578   0.03198   0.02467  -0.0710   0.3664   1.0000
  10.000   1.3715   0.03266   0.02537  -0.0694   0.3646   1.0000
  10.250   1.3952   0.03312   0.02580  -0.0693   0.3628   1.0000
  10.500   1.4298   0.03346   0.02608  -0.0708   0.3609   1.0000
  10.750   1.4604   0.03438   0.02696  -0.0720   0.3589   1.0000
  11.000   1.4187   0.03637   0.02920  -0.0632   0.3569   1.0000
  11.250   1.3543   0.04004   0.03317  -0.0537   0.3540   1.0000
  11.500   0.7177   0.11129   0.10556  -0.0459   0.3091   1.0000
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