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EPPLER E662 AIRFOIL (e662-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: EPPLER E662 AIRFOIL (e662-il)
Reynolds number: 500,000
Max Cl/Cd: 111.09 at α=4°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e662-il-500000-n5.txt
Download as CSV file: xf-e662-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER E662 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.250  -0.2847   0.04985   0.04621  -0.1572   0.8278   0.0104
 -12.000  -0.3360   0.04066   0.03669  -0.1624   0.8251   0.0102
 -11.750  -0.3522   0.03732   0.03318  -0.1622   0.8233   0.0104
 -11.500  -0.3692   0.03427   0.02993  -0.1608   0.8213   0.0104
 -11.250  -0.3862   0.03140   0.02681  -0.1583   0.8190   0.0105
 -11.000  -0.3904   0.02965   0.02487  -0.1559   0.8170   0.0109
 -10.750  -0.3933   0.02808   0.02310  -0.1532   0.8152   0.0110
 -10.500  -0.3964   0.02675   0.02153  -0.1499   0.8136   0.0113
 -10.250  -0.3894   0.02561   0.02017  -0.1478   0.8123   0.0115
 -10.000  -0.3794   0.02443   0.01876  -0.1461   0.8111   0.0116
  -9.500  -0.3542   0.02184   0.01588  -0.1433   0.8088   0.0121
  -9.250  -0.3367   0.02103   0.01499  -0.1424   0.8076   0.0123
  -9.000  -0.3178   0.02030   0.01417  -0.1415   0.8063   0.0126
  -8.750  -0.2979   0.01959   0.01336  -0.1408   0.8053   0.0128
  -8.500  -0.2772   0.01888   0.01255  -0.1402   0.8042   0.0131
  -8.250  -0.2557   0.01822   0.01179  -0.1396   0.8031   0.0135
  -8.000  -0.2334   0.01765   0.01113  -0.1391   0.8021   0.0140
  -7.750  -0.2106   0.01709   0.01047  -0.1387   0.8009   0.0144
  -7.500  -0.1873   0.01657   0.00985  -0.1383   0.7998   0.0148
  -7.250  -0.1635   0.01610   0.00928  -0.1379   0.7987   0.0151
  -7.000  -0.1407   0.01547   0.00858  -0.1374   0.7978   0.0154
  -6.750  -0.1182   0.01483   0.00791  -0.1369   0.7968   0.0159
  -6.500  -0.0943   0.01438   0.00742  -0.1366   0.7959   0.0163
  -6.250  -0.0697   0.01400   0.00699  -0.1365   0.7948   0.0168
  -6.000  -0.0456   0.01365   0.00662  -0.1361   0.7938   0.0173
  -5.750  -0.0213   0.01332   0.00627  -0.1358   0.7928   0.0178
  -5.500   0.0036   0.01305   0.00598  -0.1356   0.7916   0.0186
  -5.250   0.0287   0.01279   0.00568  -0.1354   0.7904   0.0193
  -5.000   0.0538   0.01249   0.00536  -0.1352   0.7891   0.0200
  -4.750   0.0792   0.01220   0.00505  -0.1351   0.7878   0.0210
  -4.500   0.1053   0.01197   0.00481  -0.1350   0.7865   0.0221
  -4.250   0.1319   0.01177   0.00459  -0.1351   0.7852   0.0236
  -4.000   0.1588   0.01160   0.00439  -0.1352   0.7840   0.0255
  -3.750   0.1858   0.01138   0.00420  -0.1353   0.7828   0.0316
  -3.500   0.2127   0.01111   0.00403  -0.1355   0.7816   0.0533
  -3.250   0.2401   0.01089   0.00389  -0.1358   0.7805   0.0791
  -3.000   0.2678   0.01068   0.00378  -0.1362   0.7793   0.1118
  -2.750   0.2933   0.01043   0.00370  -0.1361   0.7778   0.1560
  -2.500   0.3191   0.01014   0.00362  -0.1362   0.7760   0.2126
  -2.250   0.3451   0.00964   0.00352  -0.1366   0.7740   0.3249
  -2.000   0.3724   0.00906   0.00339  -0.1374   0.7720   0.4610
  -1.750   0.4005   0.00843   0.00333  -0.1381   0.7701   0.6270
  -1.500   0.4269   0.00843   0.00359  -0.1377   0.7683   0.7179
  -1.250   0.4558   0.00851   0.00365  -0.1379   0.7666   0.7423
  -1.000   0.4855   0.00857   0.00366  -0.1384   0.7650   0.7535
  -0.750   0.5125   0.00865   0.00375  -0.1382   0.7628   0.7617
  -0.500   0.5396   0.00872   0.00380  -0.1382   0.7599   0.7713
  -0.250   0.5652   0.00883   0.00393  -0.1377   0.7571   0.7793
   0.000   0.5930   0.00891   0.00400  -0.1377   0.7545   0.7881
   0.250   0.6197   0.00899   0.00408  -0.1374   0.7522   0.7935
   0.500   0.6487   0.00901   0.00407  -0.1377   0.7500   0.7977
   0.750   0.6757   0.00903   0.00409  -0.1377   0.7467   0.8010
   1.000   0.7022   0.00902   0.00409  -0.1376   0.7428   0.8030
   1.250   0.7292   0.00900   0.00407  -0.1376   0.7391   0.8043
   1.500   0.7574   0.00896   0.00401  -0.1378   0.7359   0.8057
   1.750   0.7830   0.00897   0.00405  -0.1375   0.7313   0.8071
   2.000   0.8089   0.00896   0.00407  -0.1373   0.7262   0.8087
   2.250   0.8366   0.00893   0.00402  -0.1374   0.7217   0.8101
   2.500   0.8620   0.00894   0.00407  -0.1371   0.7153   0.8117
   2.750   0.8883   0.00891   0.00404  -0.1369   0.7084   0.8133
   3.000   0.9138   0.00892   0.00405  -0.1367   0.7002   0.8147
   3.250   0.9395   0.00891   0.00401  -0.1364   0.6908   0.8163
   3.500   0.9641   0.00892   0.00401  -0.1359   0.6790   0.8177
   3.750   0.9866   0.00897   0.00401  -0.1350   0.6644   0.8186
   4.000   1.0076   0.00907   0.00406  -0.1337   0.6472   0.8196
   4.250   1.0264   0.00924   0.00416  -0.1320   0.6272   0.8209
   4.500   1.0423   0.00948   0.00431  -0.1297   0.6059   0.8224
   4.750   1.0547   0.00974   0.00449  -0.1268   0.5832   0.8239
   5.000   1.0643   0.01009   0.00473  -0.1233   0.5606   0.8255
   5.250   1.0743   0.01050   0.00505  -0.1200   0.5364   0.8272
   5.500   1.0835   0.01099   0.00544  -0.1167   0.5133   0.8289
   5.750   1.0938   0.01148   0.00585  -0.1137   0.4906   0.8308
   6.000   1.1028   0.01204   0.00631  -0.1106   0.4684   0.8326
   6.250   1.1124   0.01260   0.00680  -0.1077   0.4467   0.8339
   6.500   1.1207   0.01324   0.00737  -0.1046   0.4248   0.8353
   6.750   1.1297   0.01391   0.00798  -0.1018   0.4027   0.8367
   7.000   1.1396   0.01461   0.00861  -0.0993   0.3816   0.8382
   7.250   1.1489   0.01540   0.00931  -0.0967   0.3595   0.8398
   7.500   1.1596   0.01616   0.01000  -0.0945   0.3381   0.8413
   7.750   1.1705   0.01697   0.01073  -0.0924   0.3179   0.8431
   8.000   1.1823   0.01777   0.01147  -0.0905   0.2981   0.8449
   8.250   1.1936   0.01863   0.01225  -0.0886   0.2766   0.8465
   8.500   1.2049   0.01951   0.01304  -0.0867   0.2567   0.8479
   8.750   1.2162   0.02039   0.01385  -0.0848   0.2358   0.8492
   9.000   1.2263   0.02136   0.01473  -0.0829   0.2141   0.8506
   9.250   1.2380   0.02227   0.01559  -0.0812   0.1965   0.8520
   9.500   1.2504   0.02316   0.01644  -0.0797   0.1799   0.8535
   9.750   1.2620   0.02413   0.01735  -0.0781   0.1627   0.8551
  10.000   1.2730   0.02516   0.01831  -0.0765   0.1453   0.8567
  10.500   1.2945   0.02735   0.02038  -0.0735   0.1144   0.8600
  10.750   1.3058   0.02845   0.02143  -0.0721   0.1010   0.8618
  11.000   1.3157   0.02964   0.02258  -0.0706   0.0869   0.8634
  11.250   1.3265   0.03079   0.02370  -0.0692   0.0768   0.8651
  11.500   1.3370   0.03198   0.02488  -0.0679   0.0665   0.8668
  11.750   1.3463   0.03330   0.02618  -0.0665   0.0564   0.8686
  12.000   1.3571   0.03453   0.02742  -0.0653   0.0493   0.8704
  12.250   1.3670   0.03588   0.02877  -0.0641   0.0434   0.8723
  12.500   1.3775   0.03721   0.03012  -0.0630   0.0381   0.8743
  12.750   1.3878   0.03859   0.03153  -0.0620   0.0339   0.8762
  13.000   1.3963   0.04013   0.03309  -0.0609   0.0291   0.8781
  13.250   1.4053   0.04163   0.03463  -0.0598   0.0250   0.8800
  13.500   1.4128   0.04332   0.03636  -0.0588   0.0214   0.8822
  13.750   1.4195   0.04513   0.03821  -0.0577   0.0171   0.8846
  14.000   1.4252   0.04709   0.04021  -0.0567   0.0133   0.8871
  14.250   1.4307   0.04914   0.04229  -0.0558   0.0106   0.8896
  14.750   1.4408   0.05340   0.04670  -0.0542   0.0079   0.8954
  15.000   1.4462   0.05556   0.04897  -0.0535   0.0072   0.8990
  15.250   1.4509   0.05788   0.05139  -0.0530   0.0067   0.9027
  15.750   1.4568   0.06306   0.05678  -0.0521   0.0060   0.9110
  16.000   1.4585   0.06588   0.05971  -0.0518   0.0057   0.9164
  16.250   1.4608   0.06862   0.06258  -0.0515   0.0056   0.9233
  16.750   1.4600   0.07449   0.06874  -0.0510   0.0052   1.0000
  17.000   1.4600   0.07795   0.07231  -0.0514   0.0050   1.0000
  17.250   1.4599   0.08147   0.07594  -0.0520   0.0049   1.0000
  17.500   1.4586   0.08525   0.07984  -0.0527   0.0047   1.0000
  17.750   1.4561   0.08928   0.08398  -0.0536   0.0046   1.0000
  18.000   1.4526   0.09353   0.08835  -0.0548   0.0045   1.0000
  18.250   1.4480   0.09803   0.09297  -0.0561   0.0044   1.0000
  18.500   1.4416   0.10289   0.09795  -0.0577   0.0042   1.0000
  18.750   1.4345   0.10796   0.10316  -0.0595   0.0041   1.0000
  19.000   1.4264   0.11331   0.10863  -0.0616   0.0041   1.0000
  19.250   1.4166   0.11902   0.11448  -0.0641   0.0040   1.0000
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