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EPPLER 502 AIRFOIL (e502-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 502 AIRFOIL (e502-il)
Reynolds number: 200,000
Max Cl/Cd: 58 at α=7°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e502-il-200000-n5.txt
Download as CSV file: xf-e502-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 502 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.750  -0.5188   0.09040   0.08708  -0.0531   1.0000   0.0077
 -12.500  -0.5678   0.07241   0.06893  -0.0643   1.0000   0.0074
 -12.250  -0.5929   0.06553   0.06191  -0.0678   1.0000   0.0071
 -12.000  -0.6164   0.05820   0.05429  -0.0723   0.9340   0.0070
 -11.750  -0.6375   0.05093   0.04651  -0.0760   0.9005   0.0071
 -11.500  -0.6532   0.04640   0.04155  -0.0757   0.8767   0.0070
 -11.250  -0.6675   0.04268   0.03741  -0.0737   0.8603   0.0071
 -11.000  -0.6747   0.03972   0.03407  -0.0714   0.8483   0.0071
 -10.750  -0.6784   0.03699   0.03095  -0.0688   0.8387   0.0073
 -10.500  -0.6770   0.03445   0.02803  -0.0664   0.8303   0.0074
 -10.250  -0.6696   0.03233   0.02556  -0.0645   0.8236   0.0076
 -10.000  -0.6574   0.03029   0.02313  -0.0629   0.8175   0.0082
  -9.750  -0.6425   0.02876   0.02136  -0.0616   0.8126   0.0082
  -9.500  -0.6268   0.02731   0.01972  -0.0604   0.8077   0.0088
  -9.250  -0.6115   0.02652   0.01885  -0.0593   0.8028   0.0095
  -9.000  -0.5948   0.02597   0.01816  -0.0581   0.7987   0.0109
  -8.750  -0.5746   0.02496   0.01696  -0.0574   0.7945   0.0117
  -8.500  -0.5554   0.02375   0.01559  -0.0564   0.7903   0.0126
  -8.250  -0.5381   0.02287   0.01463  -0.0552   0.7865   0.0136
  -8.000  -0.5199   0.02211   0.01377  -0.0540   0.7834   0.0153
  -7.750  -0.5016   0.02133   0.01286  -0.0528   0.7797   0.0173
  -7.500  -0.4841   0.02070   0.01224  -0.0517   0.7762   0.0207
  -7.250  -0.4653   0.02016   0.01157  -0.0505   0.7730   0.0242
  -7.000  -0.4492   0.01950   0.01091  -0.0490   0.7701   0.0289
  -6.750  -0.4307   0.01906   0.01034  -0.0477   0.7670   0.0330
  -6.500  -0.4161   0.01844   0.00974  -0.0459   0.7635   0.0381
  -6.250  -0.3985   0.01807   0.00928  -0.0444   0.7606   0.0434
  -6.000  -0.3841   0.01756   0.00876  -0.0423   0.7579   0.0492
  -5.750  -0.3670   0.01719   0.00829  -0.0407   0.7556   0.0561
  -5.500  -0.3506   0.01672   0.00786  -0.0390   0.7528   0.0675
  -5.250  -0.3340   0.01626   0.00746  -0.0373   0.7497   0.0850
  -5.000  -0.3187   0.01575   0.00706  -0.0355   0.7468   0.1164
  -4.750  -0.3061   0.01511   0.00667  -0.0332   0.7443   0.1741
  -4.500  -0.2975   0.01432   0.00626  -0.0303   0.7421   0.2633
  -4.250  -0.2934   0.01339   0.00582  -0.0265   0.7399   0.3775
  -4.000  -0.2953   0.01232   0.00566  -0.0212   0.7367   0.5490
  -3.750  -0.2738   0.01266   0.00644  -0.0190   0.7341   0.6725
  -3.500  -0.2509   0.01286   0.00652  -0.0179   0.7316   0.7015
  -3.250  -0.2269   0.01313   0.00668  -0.0170   0.7295   0.7224
  -3.000  -0.2013   0.01359   0.00708  -0.0159   0.7278   0.7422
  -2.750  -0.1724   0.01427   0.00773  -0.0151   0.7261   0.7598
  -2.500  -0.1460   0.01470   0.00813  -0.0143   0.7234   0.7718
  -2.250  -0.1186   0.01491   0.00829  -0.0141   0.7208   0.7782
  -2.000  -0.0966   0.01477   0.00803  -0.0134   0.7184   0.7830
  -1.750  -0.0686   0.01475   0.00793  -0.0137   0.7164   0.7845
  -1.500  -0.0409   0.01471   0.00782  -0.0138   0.7144   0.7860
  -1.250  -0.0133   0.01467   0.00770  -0.0140   0.7126   0.7877
  -1.000   0.0128   0.01464   0.00762  -0.0140   0.7103   0.7895
  -0.750   0.0381   0.01461   0.00755  -0.0139   0.7077   0.7916
  -0.500   0.0634   0.01455   0.00745  -0.0139   0.7051   0.7937
  -0.250   0.0886   0.01447   0.00731  -0.0138   0.7027   0.7961
   0.000   0.1152   0.01441   0.00720  -0.0139   0.7006   0.7978
   0.250   0.1432   0.01439   0.00714  -0.0142   0.6989   0.7988
   0.500   0.1705   0.01440   0.00713  -0.0144   0.6968   0.8000
   0.750   0.1959   0.01444   0.00720  -0.0143   0.6936   0.8015
   1.000   0.2221   0.01445   0.00722  -0.0144   0.6907   0.8029
   1.250   0.2488   0.01444   0.00720  -0.0145   0.6881   0.8043
   1.500   0.2761   0.01441   0.00716  -0.0147   0.6858   0.8057
   1.750   0.3040   0.01438   0.00711  -0.0150   0.6838   0.8075
   2.000   0.3283   0.01443   0.00720  -0.0148   0.6800   0.8095
   2.250   0.3536   0.01443   0.00722  -0.0147   0.6761   0.8112
   2.500   0.3808   0.01440   0.00722  -0.0149   0.6729   0.8123
   2.750   0.4094   0.01435   0.00718  -0.0152   0.6701   0.8134
   3.000   0.4344   0.01439   0.00729  -0.0150   0.6658   0.8146
   3.250   0.4599   0.01439   0.00736  -0.0148   0.6609   0.8160
   3.500   0.4878   0.01431   0.00731  -0.0150   0.6570   0.8175
   3.750   0.5136   0.01430   0.00735  -0.0148   0.6522   0.8194
   4.000   0.5383   0.01429   0.00741  -0.0145   0.6463   0.8212
   4.250   0.5667   0.01416   0.00732  -0.0148   0.6416   0.8228
   4.500   0.5898   0.01417   0.00743  -0.0142   0.6345   0.8247
   4.750   0.6169   0.01406   0.00736  -0.0142   0.6284   0.8263
   5.000   0.6404   0.01405   0.00749  -0.0136   0.6205   0.8277
   5.250   0.6673   0.01392   0.00740  -0.0135   0.6130   0.8292
   5.500   0.6896   0.01390   0.00751  -0.0126   0.6020   0.8310
   5.750   0.7129   0.01386   0.00756  -0.0119   0.5904   0.8331
   6.000   0.7358   0.01381   0.00761  -0.0112   0.5769   0.8355
   6.250   0.7583   0.01377   0.00763  -0.0103   0.5604   0.8380
   6.500   0.7798   0.01375   0.00764  -0.0093   0.5391   0.8405
   6.750   0.7990   0.01379   0.00765  -0.0077   0.5080   0.8424
   7.000   0.8126   0.01401   0.00770  -0.0051   0.4640   0.8449
   7.250   0.8184   0.01450   0.00796  -0.0014   0.4165   0.8482
   7.500   0.8193   0.01511   0.00838   0.0030   0.3746   0.8523
   7.750   0.8170   0.01577   0.00892   0.0078   0.3384   0.8564
   8.000   0.8162   0.01658   0.00962   0.0120   0.3048   0.8608
   8.250   0.8153   0.01755   0.01046   0.0158   0.2709   0.8666
   8.500   0.8165   0.01854   0.01136   0.0190   0.2393   0.8722
   8.750   0.8191   0.01957   0.01231   0.0218   0.2104   0.8785
   9.000   0.8230   0.02069   0.01333   0.0242   0.1816   0.8852
   9.250   0.8289   0.02180   0.01438   0.0261   0.1558   0.8929
   9.500   0.8360   0.02296   0.01548   0.0277   0.1321   0.9020
   9.750   0.8446   0.02418   0.01664   0.0289   0.1078   0.9136
  10.000   0.8582   0.02544   0.01790   0.0290   0.0868   0.9282
  10.250   0.8767   0.02687   0.01931   0.0278   0.0680   0.9476
  10.500   0.8962   0.02829   0.02072   0.0263   0.0526   1.0000
  10.750   0.9038   0.02959   0.02197   0.0275   0.0434   1.0000
  11.000   0.9122   0.03089   0.02327   0.0285   0.0357   1.0000
  11.250   0.9206   0.03220   0.02461   0.0296   0.0301   1.0000
  11.500   0.9266   0.03374   0.02613   0.0307   0.0252   1.0000
  11.750   0.9349   0.03513   0.02760   0.0316   0.0210   1.0000
  12.000   0.9409   0.03674   0.02925   0.0326   0.0185   1.0000
  12.250   0.9462   0.03844   0.03103   0.0336   0.0162   1.0000
  12.500   0.9533   0.04004   0.03271   0.0343   0.0140   1.0000
  12.750   0.9570   0.04197   0.03468   0.0351   0.0124   1.0000
  13.000   0.9605   0.04400   0.03681   0.0358   0.0117   1.0000
  13.250   0.9643   0.04606   0.03900   0.0365   0.0109   1.0000
  13.500   0.9676   0.04822   0.04127   0.0370   0.0101   1.0000
  13.750   0.9706   0.05048   0.04362   0.0374   0.0094   1.0000
  14.000   0.9703   0.05313   0.04632   0.0376   0.0082   1.0000
  14.250   0.9733   0.05555   0.04888   0.0378   0.0078   1.0000
  14.500   0.9716   0.05850   0.05192   0.0379   0.0082   1.0000
  14.750   0.9765   0.06086   0.05446   0.0378   0.0074   1.0000
  15.000   0.9793   0.06352   0.05724   0.0374   0.0066   1.0000
  15.250   0.9776   0.06679   0.06068   0.0370   0.0065   1.0000
  15.500   0.9770   0.07003   0.06403   0.0363   0.0061   1.0000
  15.750   0.9744   0.07362   0.06776   0.0355   0.0060   1.0000
  16.000   0.9714   0.07739   0.07166   0.0344   0.0059   1.0000
  16.250   0.9660   0.08164   0.07604   0.0331   0.0058   1.0000
  16.500   0.9569   0.08657   0.08110   0.0314   0.0056   1.0000
  16.750   0.9517   0.09106   0.08573   0.0297   0.0056   1.0000
  17.000   0.9429   0.09638   0.09124   0.0276   0.0054   1.0000
  17.250   0.9351   0.10164   0.09667   0.0253   0.0054   1.0000
  17.500   0.9269   0.10717   0.10235   0.0226   0.0054   1.0000
  17.750   0.9179   0.11294   0.10826   0.0197   0.0055   1.0000
  18.000   0.9041   0.12007   0.11560   0.0160   0.0053   1.0000
  18.250   0.8951   0.12626   0.12192   0.0126   0.0054   1.0000
  18.500   0.8797   0.13423   0.13007   0.0081   0.0053   1.0000
  18.750   0.8676   0.14157   0.13755   0.0040   0.0054   1.0000
  19.000   0.8525   0.15010   0.14622  -0.0009   0.0054   1.0000
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