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NACA 2.5411 (naca2411-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: NACA 2.5411 (naca2411-il)
Reynolds number: 100,000
Max Cl/Cd: 52.24 at α=5.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca2411-il-100000-n5.txt
Download as CSV file: xf-naca2411-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 2.5411                                     
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.5748   0.06609   0.06065  -0.0586   1.0000   0.0380
 -10.000  -0.6064   0.05974   0.05427  -0.0624   1.0000   0.0377
  -9.750  -0.6382   0.05567   0.05010  -0.0608   1.0000   0.0376
  -9.500  -0.6631   0.05147   0.04570  -0.0589   1.0000   0.0375
  -9.250  -0.6828   0.04738   0.04130  -0.0563   1.0000   0.0376
  -9.000  -0.6959   0.04351   0.03700  -0.0534   1.0000   0.0379
  -8.750  -0.6981   0.04058   0.03378  -0.0508   1.0000   0.0383
  -8.500  -0.6922   0.03862   0.03167  -0.0487   1.0000   0.0388
  -8.250  -0.6838   0.03701   0.02992  -0.0466   1.0000   0.0397
  -8.000  -0.6745   0.03539   0.02811  -0.0445   1.0000   0.0407
  -7.750  -0.6643   0.03371   0.02618  -0.0425   1.0000   0.0423
  -7.500  -0.6535   0.03178   0.02388  -0.0404   1.0000   0.0439
  -7.250  -0.6409   0.02984   0.02148  -0.0384   1.0000   0.0453
  -7.000  -0.6260   0.02838   0.01989  -0.0367   1.0000   0.0465
  -6.750  -0.6098   0.02733   0.01878  -0.0352   1.0000   0.0479
  -6.500  -0.5852   0.02629   0.01757  -0.0352   0.9978   0.0505
  -6.250  -0.5524   0.02510   0.01600  -0.0366   0.9935   0.0543
  -6.000  -0.5214   0.02408   0.01502  -0.0379   0.9886   0.0575
  -5.750  -0.4876   0.02320   0.01398  -0.0395   0.9841   0.0620
  -5.500  -0.4568   0.02234   0.01304  -0.0404   0.9785   0.0672
  -5.250  -0.4232   0.02167   0.01228  -0.0419   0.9733   0.0737
  -5.000  -0.3912   0.02098   0.01157  -0.0431   0.9677   0.0809
  -4.750  -0.3591   0.02035   0.01086  -0.0441   0.9613   0.0898
  -4.500  -0.3224   0.01980   0.01028  -0.0461   0.9567   0.1011
  -4.250  -0.2945   0.01926   0.00977  -0.0463   0.9484   0.1128
  -4.000  -0.2582   0.01874   0.00926  -0.0481   0.9432   0.1290
  -3.750  -0.2293   0.01828   0.00884  -0.0485   0.9350   0.1464
  -3.500  -0.1944   0.01779   0.00845  -0.0500   0.9291   0.1698
  -3.250  -0.1642   0.01738   0.00812  -0.0505   0.9215   0.1959
  -3.000  -0.1309   0.01696   0.00781  -0.0516   0.9148   0.2285
  -2.750  -0.0976   0.01656   0.00752  -0.0527   0.9085   0.2674
  -2.500  -0.0676   0.01617   0.00728  -0.0531   0.9003   0.3096
  -2.250  -0.0321   0.01571   0.00700  -0.0546   0.8950   0.3638
  -2.000  -0.0062   0.01529   0.00684  -0.0541   0.8849   0.4237
  -1.750   0.0261   0.01476   0.00667  -0.0547   0.8783   0.5160
  -1.500   0.0530   0.01430   0.00659  -0.0540   0.8686   0.6196
  -1.250   0.0841   0.01389   0.00655  -0.0537   0.8609   0.7301
  -1.000   0.1281   0.01365   0.00655  -0.0558   0.8533   0.8382
  -0.750   0.1928   0.01352   0.00642  -0.0624   0.8489   0.9142
  -0.500   0.2449   0.01349   0.00631  -0.0669   0.8386   0.9562
  -0.250   0.2995   0.01339   0.00611  -0.0721   0.8294   0.9829
   0.000   0.3510   0.01327   0.00589  -0.0769   0.8185   1.0000
   0.250   0.3765   0.01322   0.00574  -0.0763   0.8037   1.0000
   0.500   0.4020   0.01319   0.00561  -0.0757   0.7887   1.0000
   0.750   0.4274   0.01318   0.00552  -0.0750   0.7734   1.0000
   1.000   0.4526   0.01319   0.00544  -0.0743   0.7579   1.0000
   1.250   0.4775   0.01323   0.00540  -0.0735   0.7423   1.0000
   1.500   0.5022   0.01329   0.00539  -0.0726   0.7265   1.0000
   1.750   0.5266   0.01337   0.00539  -0.0717   0.7105   1.0000
   2.000   0.5507   0.01348   0.00543  -0.0707   0.6947   1.0000
   2.250   0.5746   0.01360   0.00549  -0.0697   0.6788   1.0000
   2.500   0.5982   0.01375   0.00557  -0.0687   0.6631   1.0000
   2.750   0.6216   0.01391   0.00568  -0.0676   0.6474   1.0000
   3.000   0.6448   0.01408   0.00582  -0.0665   0.6318   1.0000
   3.250   0.6679   0.01428   0.00596  -0.0654   0.6162   1.0000
   3.500   0.6907   0.01448   0.00613  -0.0642   0.6006   1.0000
   3.750   0.7134   0.01470   0.00631  -0.0630   0.5847   1.0000
   4.000   0.7358   0.01493   0.00653  -0.0618   0.5686   1.0000
   4.250   0.7581   0.01517   0.00674  -0.0605   0.5523   1.0000
   4.500   0.7801   0.01543   0.00697  -0.0592   0.5355   1.0000
   4.750   0.8017   0.01569   0.00721  -0.0578   0.5178   1.0000
   5.000   0.8226   0.01597   0.00748  -0.0563   0.4986   1.0000
   5.250   0.8430   0.01625   0.00776  -0.0548   0.4781   1.0000
   5.500   0.8630   0.01657   0.00803  -0.0531   0.4566   1.0000
   5.750   0.8824   0.01689   0.00835  -0.0514   0.4333   1.0000
   6.000   0.9009   0.01725   0.00866  -0.0496   0.4079   1.0000
   6.250   0.9191   0.01763   0.00901  -0.0478   0.3799   1.0000
   6.500   0.9362   0.01808   0.00940  -0.0458   0.3490   1.0000
   6.750   0.9522   0.01861   0.00982  -0.0437   0.3161   1.0000
   7.000   0.9673   0.01923   0.01032  -0.0415   0.2805   1.0000
   7.250   0.9810   0.01997   0.01090  -0.0393   0.2436   1.0000
   7.500   0.9935   0.02083   0.01157  -0.0369   0.2077   1.0000
   7.750   1.0055   0.02175   0.01235  -0.0345   0.1749   1.0000
   8.000   1.0167   0.02273   0.01319  -0.0321   0.1474   1.0000
   8.250   1.0276   0.02374   0.01409  -0.0297   0.1259   1.0000
   8.500   1.0371   0.02479   0.01504  -0.0271   0.1099   1.0000
   8.750   1.0459   0.02578   0.01603  -0.0243   0.0976   1.0000
   9.000   1.0546   0.02679   0.01705  -0.0216   0.0878   1.0000
   9.250   1.0621   0.02789   0.01815  -0.0189   0.0798   1.0000
   9.500   1.0692   0.02904   0.01932  -0.0163   0.0737   1.0000
   9.750   1.0769   0.03023   0.02056  -0.0139   0.0681   1.0000
  10.000   1.0842   0.03146   0.02184  -0.0116   0.0635   1.0000
  10.250   1.0900   0.03288   0.02329  -0.0093   0.0598   1.0000
  10.500   1.0982   0.03421   0.02474  -0.0074   0.0561   1.0000
  10.750   1.1044   0.03567   0.02624  -0.0055   0.0530   1.0000
  11.000   1.1100   0.03734   0.02792  -0.0037   0.0508   1.0000
  11.250   1.1188   0.03890   0.02965  -0.0021   0.0484   1.0000
  11.500   1.1264   0.04054   0.03140  -0.0007   0.0461   1.0000
  11.750   1.1325   0.04227   0.03318   0.0006   0.0442   1.0000
  12.000   1.1386   0.04418   0.03510   0.0018   0.0426   1.0000
  12.250   1.1463   0.04608   0.03723   0.0030   0.0409   1.0000
  12.500   1.1533   0.04813   0.03945   0.0040   0.0395   1.0000
  12.750   1.1593   0.05028   0.04174   0.0049   0.0384   1.0000
  13.000   1.1646   0.05250   0.04408   0.0057   0.0375   1.0000
  13.250   1.1688   0.05478   0.04645   0.0064   0.0365   1.0000
  13.500   1.1739   0.05715   0.04885   0.0069   0.0356   1.0000
  13.750   1.1728   0.06021   0.05215   0.0073   0.0349   1.0000
  14.000   1.1676   0.06370   0.05594   0.0073   0.0341   1.0000
  14.250   1.1610   0.06746   0.05995   0.0070   0.0333   1.0000
  14.500   1.1530   0.07152   0.06424   0.0063   0.0328   1.0000
  14.750   1.1426   0.07605   0.06900   0.0051   0.0323   1.0000
  15.000   1.1303   0.08105   0.07423   0.0034   0.0320   1.0000
  15.250   1.1151   0.08675   0.08016   0.0011   0.0318   1.0000
  15.500   1.0967   0.09331   0.08695  -0.0021   0.0317   1.0000
  15.750   1.0733   0.10124   0.09512  -0.0064   0.0318   1.0000
  16.000   1.0428   0.11123   0.10537  -0.0124   0.0319   1.0000
  16.250   0.9885   0.12817   0.12259  -0.0235   0.0327   1.0000
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