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EPPLER 580 AIRFOIL (e580-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 580 AIRFOIL (e580-il)
Reynolds number: 200,000
Max Cl/Cd: 76.08 at α=6.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e580-il-200000-n5.txt
Download as CSV file: xf-e580-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 580 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
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.3402   0.09259   0.08900  -0.0701   0.9893   0.0190
 -10.750  -0.3522   0.08102   0.07742  -0.0785   0.9862   0.0186
 -10.500  -0.3788   0.06820   0.06444  -0.0903   0.9814   0.0183
 -10.250  -0.3969   0.06012   0.05616  -0.0985   0.9743   0.0181
 -10.000  -0.4133   0.05395   0.04977  -0.1041   0.9651   0.0180
  -9.750  -0.4255   0.04902   0.04459  -0.1082   0.9550   0.0180
  -9.500  -0.4342   0.04493   0.04023  -0.1109   0.9437   0.0180
  -9.250  -0.4318   0.04086   0.03582  -0.1137   0.9335   0.0180
  -9.000  -0.4269   0.03775   0.03233  -0.1143   0.9233   0.0185
  -8.750  -0.4075   0.03464   0.02874  -0.1167   0.9187   0.0189
  -8.500  -0.3937   0.03246   0.02620  -0.1165   0.9097   0.0192
  -8.250  -0.3677   0.03018   0.02359  -0.1181   0.9056   0.0192
  -8.000  -0.3440   0.02828   0.02143  -0.1187   0.8997   0.0194
  -7.750  -0.3190   0.02635   0.01934  -0.1193   0.8938   0.0196
  -7.500  -0.2870   0.02473   0.01758  -0.1209   0.8904   0.0199
  -7.250  -0.2598   0.02347   0.01621  -0.1215   0.8841   0.0202
  -7.000  -0.2296   0.02234   0.01499  -0.1225   0.8784   0.0206
  -6.750  -0.1928   0.02121   0.01378  -0.1248   0.8748   0.0211
  -6.500  -0.1653   0.02033   0.01282  -0.1252   0.8671   0.0216
  -6.250  -0.1312   0.01942   0.01183  -0.1270   0.8613   0.0224
  -6.000  -0.0990   0.01868   0.01101  -0.1284   0.8545   0.0236
  -5.750  -0.0670   0.01796   0.01022  -0.1298   0.8471   0.0245
  -5.500  -0.0348   0.01707   0.00928  -0.1316   0.8396   0.0254
  -5.250  -0.0030   0.01639   0.00853  -0.1331   0.8313   0.0264
  -5.000   0.0288   0.01583   0.00788  -0.1345   0.8230   0.0277
  -4.750   0.0615   0.01533   0.00725  -0.1360   0.8146   0.0294
  -4.500   0.0917   0.01488   0.00672  -0.1370   0.8056   0.0318
  -4.250   0.1247   0.01447   0.00622  -0.1384   0.7975   0.0372
  -4.000   0.1540   0.01392   0.00578  -0.1394   0.7881   0.0620
  -3.750   0.1874   0.01297   0.00521  -0.1419   0.7799   0.1718
  -3.500   0.2201   0.01169   0.00498  -0.1448   0.7708   0.4410
  -3.250   0.2499   0.01186   0.00517  -0.1450   0.7624   0.5022
  -3.000   0.2783   0.01226   0.00552  -0.1447   0.7535   0.5412
  -2.750   0.3048   0.01276   0.00600  -0.1439   0.7449   0.5657
  -2.500   0.3339   0.01293   0.00603  -0.1440   0.7366   0.5764
  -2.250   0.3618   0.01293   0.00593  -0.1440   0.7282   0.5792
  -2.000   0.3905   0.01295   0.00583  -0.1442   0.7202   0.5815
  -1.750   0.4180   0.01296   0.00576  -0.1442   0.7119   0.5842
  -1.500   0.4472   0.01298   0.00565  -0.1445   0.7042   0.5871
  -1.250   0.4752   0.01298   0.00556  -0.1447   0.6960   0.5901
  -1.000   0.5048   0.01301   0.00543  -0.1452   0.6887   0.5935
  -0.750   0.5315   0.01303   0.00542  -0.1451   0.6807   0.5954
  -0.500   0.5596   0.01308   0.00539  -0.1452   0.6735   0.5973
  -0.250   0.5867   0.01312   0.00540  -0.1451   0.6659   0.5997
   0.000   0.6147   0.01318   0.00538  -0.1452   0.6588   0.6025
   0.250   0.6424   0.01324   0.00538  -0.1453   0.6515   0.6053
   0.500   0.6706   0.01330   0.00536  -0.1456   0.6444   0.6080
   0.750   0.6981   0.01336   0.00538  -0.1456   0.6375   0.6103
   1.000   0.7248   0.01343   0.00544  -0.1455   0.6303   0.6125
   1.250   0.7520   0.01353   0.00550  -0.1454   0.6238   0.6149
   1.500   0.7786   0.01361   0.00558  -0.1453   0.6165   0.6173
   2.000   0.8329   0.01380   0.00571  -0.1454   0.6028   0.6227
   2.250   0.8602   0.01391   0.00577  -0.1454   0.5961   0.6256
   2.500   0.8861   0.01401   0.00592  -0.1451   0.5891   0.6278
   2.750   0.9123   0.01413   0.00604  -0.1449   0.5822   0.6302
   3.000   0.9385   0.01425   0.00617  -0.1447   0.5754   0.6327
   3.250   0.9645   0.01438   0.00631  -0.1445   0.5682   0.6355
   3.500   0.9908   0.01452   0.00644  -0.1444   0.5615   0.6386
   3.750   1.0163   0.01466   0.00660  -0.1441   0.5539   0.6416
   4.000   1.0417   0.01481   0.00676  -0.1437   0.5471   0.6441
   4.250   1.0661   0.01495   0.00698  -0.1432   0.5390   0.6468
   4.500   1.0912   0.01512   0.00715  -0.1429   0.5319   0.6498
   4.750   1.1154   0.01528   0.00736  -0.1423   0.5235   0.6529
   5.000   1.1400   0.01547   0.00756  -0.1419   0.5159   0.6563
   5.250   1.1629   0.01564   0.00781  -0.1411   0.5071   0.6592
   5.500   1.1861   0.01584   0.00804  -0.1404   0.4990   0.6625
   5.750   1.2085   0.01604   0.00829  -0.1395   0.4897   0.6661
   6.000   1.2308   0.01626   0.00857  -0.1386   0.4805   0.6699
   6.250   1.2523   0.01650   0.00882  -0.1376   0.4710   0.6734
   6.500   1.2727   0.01673   0.00913  -0.1364   0.4604   0.6766
   6.750   1.2926   0.01699   0.00944  -0.1351   0.4502   0.6804
   7.000   1.3107   0.01728   0.00976  -0.1335   0.4397   0.6849
   7.250   1.3281   0.01757   0.01011  -0.1317   0.4283   0.6894
   7.500   1.3448   0.01789   0.01050  -0.1299   0.4169   0.6937
   7.750   1.3610   0.01828   0.01092  -0.1280   0.4053   0.6986
   8.250   1.3912   0.01917   0.01189  -0.1240   0.3805   0.7085
   8.500   1.4057   0.01967   0.01244  -0.1220   0.3675   0.7142
   8.750   1.4194   0.02023   0.01303  -0.1199   0.3543   0.7203
   9.000   1.4319   0.02083   0.01370  -0.1177   0.3410   0.7265
   9.250   1.4436   0.02151   0.01441  -0.1155   0.3274   0.7342
   9.500   1.4539   0.02226   0.01520  -0.1131   0.3135   0.7417
  10.000   1.4706   0.02404   0.01705  -0.1081   0.2835   0.7598
  10.250   1.4768   0.02511   0.01814  -0.1055   0.2670   0.7704
  10.500   1.4813   0.02632   0.01938  -0.1028   0.2501   0.7830
  10.750   1.4845   0.02765   0.02073  -0.1002   0.2334   0.7981
  11.000   1.4855   0.02916   0.02226  -0.0974   0.2164   0.8182
  11.500   1.4789   0.03223   0.02545  -0.0909   0.1856   1.0000
  11.750   1.4801   0.03427   0.02746  -0.0892   0.1690   1.0000
  12.000   1.4801   0.03650   0.02964  -0.0875   0.1530   1.0000
  12.250   1.4801   0.03884   0.03195  -0.0861   0.1388   1.0000
  12.500   1.4799   0.04131   0.03440  -0.0848   0.1255   1.0000
  12.750   1.4793   0.04392   0.03701  -0.0837   0.1135   1.0000
  13.000   1.4783   0.04667   0.03975  -0.0827   0.1026   1.0000
  13.250   1.4775   0.04950   0.04258  -0.0820   0.0919   1.0000
  13.500   1.4772   0.05237   0.04548  -0.0814   0.0823   1.0000
  13.750   1.4763   0.05540   0.04853  -0.0809   0.0739   1.0000
  14.000   1.4745   0.05863   0.05178  -0.0806   0.0664   1.0000
  14.250   1.4742   0.06177   0.05498  -0.0805   0.0595   1.0000
  14.500   1.4728   0.06514   0.05840  -0.0805   0.0534   1.0000
  14.750   1.4696   0.06880   0.06209  -0.0806   0.0471   1.0000
  15.000   1.4676   0.07242   0.06578  -0.0808   0.0410   1.0000
  15.250   1.4637   0.07638   0.06979  -0.0813   0.0354   1.0000
  15.500   1.4587   0.08058   0.07404  -0.0819   0.0304   1.0000
  15.750   1.4546   0.08475   0.07828  -0.0826   0.0258   1.0000
  16.000   1.4495   0.08915   0.08276  -0.0835   0.0221   1.0000
  16.250   1.4435   0.09380   0.08747  -0.0846   0.0192   1.0000
  16.500   1.4392   0.09826   0.09205  -0.0858   0.0170   1.0000
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