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EPPLER 585 AIRFOIL (e585-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 585 AIRFOIL (e585-il)
Reynolds number: 500,000
Max Cl/Cd: 117.97 at α=6.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e585-il-500000.txt
Download as CSV file: xf-e585-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 585 AIRFOIL                              
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.0188   0.08491   0.08250  -0.1092   0.9172   0.0157
 -10.750  -0.0111   0.08106   0.07859  -0.1116   0.9049   0.0162
 -10.500  -0.0081   0.07688   0.07435  -0.1136   0.8935   0.0171
 -10.250  -0.0149   0.07075   0.06816  -0.1169   0.8839   0.0184
 -10.000  -0.0203   0.06525   0.06264  -0.1196   0.8744   0.0186
  -9.750  -0.0226   0.06050   0.05784  -0.1217   0.8661   0.0186
  -9.500  -0.0303   0.05435   0.05168  -0.1249   0.8583   0.0186
  -9.250  -0.0409   0.04701   0.04427  -0.1302   0.8517   0.0186
  -9.000  -0.0566   0.04207   0.03923  -0.1333   0.8436   0.0186
  -8.750  -0.0777   0.03816   0.03517  -0.1347   0.8357   0.0186
  -8.500  -0.0996   0.03532   0.03219  -0.1339   0.8276   0.0186
  -8.000  -0.1382   0.04340   0.03975  -0.1371   0.8262   0.0186
  -7.750  -0.1449   0.03885   0.03507  -0.1358   0.8202   0.0190
  -7.500  -0.1339   0.03719   0.03341  -0.1351   0.8147   0.0195
  -7.250  -0.1218   0.03573   0.03184  -0.1344   0.8098   0.0201
  -7.000  -0.1111   0.03363   0.02955  -0.1334   0.8049   0.0209
  -6.750  -0.1093   0.02993   0.02515  -0.1305   0.7996   0.0240
  -6.500  -0.1023   0.02243   0.01692  -0.1273   0.7955   0.0152
  -6.250  -0.0803   0.02039   0.01466  -0.1266   0.7918   0.0136
  -6.000  -0.0586   0.01866   0.01266  -0.1257   0.7876   0.0135
  -5.750  -0.0343   0.01761   0.01138  -0.1251   0.7838   0.0140
  -5.500  -0.0095   0.01631   0.00987  -0.1246   0.7804   0.0139
  -5.250   0.0157   0.01512   0.00850  -0.1241   0.7771   0.0136
  -5.000   0.0397   0.01418   0.00749  -0.1234   0.7733   0.0134
  -4.750   0.0642   0.01345   0.00668  -0.1229   0.7696   0.0135
  -4.500   0.0892   0.01284   0.00601  -0.1225   0.7662   0.0138
  -4.250   0.1151   0.01236   0.00543  -0.1223   0.7631   0.0143
  -4.000   0.1396   0.01178   0.00482  -0.1219   0.7596   0.0155
  -3.750   0.1655   0.01142   0.00444  -0.1217   0.7559   0.0182
  -3.500   0.1914   0.01087   0.00394  -0.1216   0.7526   0.0342
  -3.250   0.2175   0.01035   0.00367  -0.1217   0.7494   0.0979
  -3.000   0.2437   0.00983   0.00350  -0.1220   0.7462   0.1975
  -2.750   0.2676   0.00883   0.00328  -0.1224   0.7427   0.4172
  -2.500   0.2915   0.00807   0.00340  -0.1221   0.7391   0.6785
  -2.250   0.3194   0.00818   0.00348  -0.1220   0.7358   0.7161
  -2.000   0.3483   0.00833   0.00353  -0.1221   0.7327   0.7353
  -1.750   0.3755   0.00847   0.00365  -0.1219   0.7292   0.7504
  -1.500   0.4021   0.00859   0.00377  -0.1215   0.7253   0.7617
  -1.250   0.4297   0.00870   0.00382  -0.1213   0.7216   0.7714
  -1.000   0.4576   0.00882   0.00388  -0.1213   0.7184   0.7796
  -0.750   0.4849   0.00895   0.00397  -0.1211   0.7150   0.7871
  -0.500   0.5108   0.00910   0.00413  -0.1205   0.7112   0.7979
  -0.250   0.5351   0.00924   0.00429  -0.1194   0.7074   0.8072
   0.000   0.5628   0.00934   0.00434  -0.1194   0.7040   0.8152
   0.250   0.5900   0.00940   0.00436  -0.1193   0.7006   0.8184
   0.500   0.6165   0.00940   0.00438  -0.1191   0.6965   0.8213
   0.750   0.6445   0.00941   0.00435  -0.1193   0.6922   0.8241
   1.000   0.6736   0.00942   0.00430  -0.1198   0.6883   0.8267
   1.250   0.7025   0.00946   0.00431  -0.1203   0.6841   0.8292
   1.500   0.7291   0.00942   0.00429  -0.1202   0.6794   0.8311
   1.750   0.7566   0.00942   0.00427  -0.1203   0.6750   0.8329
   2.000   0.7853   0.00947   0.00428  -0.1206   0.6710   0.8350
   2.250   0.8112   0.00946   0.00431  -0.1204   0.6659   0.8372
   2.500   0.8387   0.00946   0.00431  -0.1206   0.6607   0.8394
   2.750   0.8677   0.00951   0.00430  -0.1210   0.6560   0.8416
   3.000   0.8942   0.00952   0.00436  -0.1210   0.6502   0.8442
   3.250   0.9207   0.00951   0.00435  -0.1209   0.6446   0.8462
   3.500   0.9473   0.00955   0.00438  -0.1209   0.6392   0.8480
   3.750   0.9727   0.00956   0.00444  -0.1206   0.6327   0.8501
   4.000   0.9997   0.00961   0.00447  -0.1206   0.6269   0.8523
   4.250   1.0249   0.00964   0.00456  -0.1203   0.6197   0.8550
   4.500   1.0513   0.00970   0.00460  -0.1203   0.6128   0.8577
   4.750   1.0767   0.00975   0.00470  -0.1201   0.6048   0.8601
   5.000   1.1012   0.00981   0.00475  -0.1196   0.5970   0.8622
   5.250   1.1247   0.00986   0.00486  -0.1189   0.5876   0.8646
   5.500   1.1484   0.00995   0.00497  -0.1183   0.5784   0.8673
   5.750   1.1716   0.01007   0.00509  -0.1176   0.5680   0.8703
   6.000   1.1948   0.01019   0.00524  -0.1170   0.5568   0.8735
   6.250   1.2163   0.01032   0.00539  -0.1160   0.5450   0.8764
   6.500   1.2363   0.01048   0.00556  -0.1147   0.5321   0.8795
   6.750   1.2554   0.01067   0.00575  -0.1132   0.5178   0.8830
   7.000   1.2735   0.01090   0.00598  -0.1116   0.5018   0.8868
   7.250   1.2884   0.01116   0.00622  -0.1094   0.4844   0.8908
   7.500   1.2992   0.01145   0.00649  -0.1063   0.4666   0.8956
   8.000   1.3201   0.01227   0.00724  -0.1004   0.4285   0.9073
   8.250   1.3282   0.01276   0.00771  -0.0971   0.4078   0.9144
   8.500   1.3340   0.01333   0.00824  -0.0935   0.3874   0.9231
   8.750   1.3400   0.01388   0.00878  -0.0901   0.3669   0.9354
   9.000   1.3458   0.01454   0.00942  -0.0868   0.3453   0.9682
   9.250   1.3561   0.01542   0.01022  -0.0850   0.3227   1.0000
   9.500   1.3649   0.01643   0.01114  -0.0829   0.3005   1.0000
   9.750   1.3728   0.01750   0.01214  -0.0808   0.2789   1.0000
  10.000   1.3799   0.01865   0.01321  -0.0787   0.2578   1.0000
  10.250   1.3859   0.01991   0.01439  -0.0765   0.2383   1.0000
  10.500   1.3931   0.02115   0.01557  -0.0746   0.2192   1.0000
  10.750   1.3992   0.02249   0.01684  -0.0727   0.2008   1.0000
  11.000   1.4045   0.02394   0.01822  -0.0707   0.1834   1.0000
  11.250   1.4096   0.02544   0.01967  -0.0689   0.1663   1.0000
  11.500   1.4152   0.02696   0.02114  -0.0672   0.1501   1.0000
  11.750   1.4198   0.02860   0.02272  -0.0656   0.1337   1.0000
  12.000   1.4241   0.03030   0.02437  -0.0640   0.1189   1.0000
  12.250   1.4282   0.03208   0.02610  -0.0625   0.1051   1.0000
  12.500   1.4312   0.03399   0.02795  -0.0610   0.0912   1.0000
  12.750   1.4332   0.03606   0.02995  -0.0596   0.0774   1.0000
  13.000   1.4362   0.03810   0.03197  -0.0584   0.0661   1.0000
  13.250   1.4375   0.04036   0.03417  -0.0572   0.0542   1.0000
  13.500   1.4407   0.04252   0.03632  -0.0562   0.0462   1.0000
  13.750   1.4423   0.04489   0.03867  -0.0553   0.0379   1.0000
  14.000   1.4462   0.04711   0.04092  -0.0545   0.0327   1.0000
  14.250   1.4482   0.04958   0.04340  -0.0538   0.0273   1.0000
  14.500   1.4493   0.05222   0.04606  -0.0532   0.0234   1.0000
  14.750   1.4527   0.05468   0.04858  -0.0528   0.0203   1.0000
  15.000   1.4540   0.05742   0.05137  -0.0525   0.0176   1.0000
  15.250   1.4557   0.06022   0.05425  -0.0522   0.0154   1.0000
  15.500   1.4560   0.06325   0.05734  -0.0521   0.0133   1.0000
  15.750   1.4564   0.06632   0.06048  -0.0521   0.0116   1.0000
  16.000   1.4551   0.06970   0.06394  -0.0522   0.0100   1.0000
  16.250   1.4542   0.07312   0.06745  -0.0525   0.0089   1.0000
  16.500   1.4509   0.07695   0.07137  -0.0529   0.0076   1.0000
  16.750   1.4482   0.08077   0.07528  -0.0535   0.0065   1.0000
  17.000   1.4415   0.08529   0.07991  -0.0543   0.0056   1.0000
  17.250   1.4384   0.08936   0.08409  -0.0552   0.0049   1.0000
  17.500   1.4286   0.09458   0.08941  -0.0566   0.0044   1.0000
  17.750   1.4216   0.09948   0.09445  -0.0580   0.0037   1.0000
  18.000   1.4157   0.10428   0.09938  -0.0596   0.0036   1.0000
  18.250   1.4074   0.10955   0.10476  -0.0614   0.0032   1.0000
  18.500   1.3955   0.11558   0.11093  -0.0638   0.0030   1.0000
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