Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

NACA 2418 (naca2418-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: NACA 2418 (naca2418-il)
Reynolds number: 200,000
Max Cl/Cd: 58.6 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca2418-il-200000-n5.txt
Download as CSV file: xf-naca2418-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 2418                                       
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -18.500  -0.9321   0.10184   0.09609  -0.0527   1.0000   0.0487
 -18.250  -0.9387   0.09722   0.09142  -0.0551   1.0000   0.0491
 -18.000  -0.9434   0.09301   0.08716  -0.0572   1.0000   0.0497
 -17.750  -0.9507   0.08837   0.08246  -0.0596   1.0000   0.0502
 -17.500  -0.9593   0.08357   0.07757  -0.0620   1.0000   0.0508
 -17.250  -0.9684   0.07877   0.07267  -0.0645   1.0000   0.0514
 -17.000  -0.9772   0.07412   0.06790  -0.0668   1.0000   0.0520
 -16.750  -0.9851   0.06970   0.06335  -0.0689   1.0000   0.0527
 -16.500  -0.9924   0.06548   0.05899  -0.0709   1.0000   0.0534
 -16.250  -0.9986   0.06152   0.05488  -0.0726   1.0000   0.0541
 -16.000  -1.0011   0.05827   0.05161  -0.0738   1.0000   0.0546
 -15.750  -1.0036   0.05505   0.04834  -0.0750   1.0000   0.0553
 -15.500  -1.0057   0.05195   0.04516  -0.0761   1.0000   0.0559
 -15.250  -1.0069   0.04902   0.04215  -0.0770   1.0000   0.0567
 -15.000  -1.0073   0.04629   0.03933  -0.0776   1.0000   0.0576
 -14.750  -1.0067   0.04377   0.03671  -0.0780   1.0000   0.0586
 -14.500  -1.0049   0.04147   0.03428  -0.0781   1.0000   0.0597
 -14.250  -1.0041   0.03928   0.03205  -0.0780   1.0000   0.0606
 -14.000  -1.0027   0.03730   0.03004  -0.0776   1.0000   0.0615
 -13.750  -1.0006   0.03557   0.02825  -0.0768   1.0000   0.0627
 -13.500  -0.9983   0.03404   0.02665  -0.0755   1.0000   0.0640
 -13.250  -0.9964   0.03270   0.02522  -0.0737   1.0000   0.0653
 -13.000  -0.9964   0.03147   0.02394  -0.0714   1.0000   0.0665
 -12.750  -0.9988   0.03038   0.02284  -0.0684   1.0000   0.0675
 -12.500  -1.0021   0.02948   0.02191  -0.0648   1.0000   0.0687
 -12.250  -1.0074   0.02874   0.02113  -0.0605   1.0000   0.0699
 -12.000  -1.0154   0.02814   0.02047  -0.0554   1.0000   0.0710
 -11.750  -1.0259   0.02767   0.01994  -0.0495   1.0000   0.0722
 -11.500  -1.0200   0.02700   0.01924  -0.0467   0.9985   0.0738
 -11.250  -0.9940   0.02619   0.01840  -0.0477   0.9947   0.0764
 -11.000  -0.9660   0.02549   0.01761  -0.0487   0.9913   0.0796
 -10.750  -0.9405   0.02474   0.01686  -0.0492   0.9866   0.0824
 -10.500  -0.9117   0.02409   0.01616  -0.0503   0.9827   0.0857
 -10.250  -0.8807   0.02346   0.01547  -0.0517   0.9799   0.0892
 -10.000  -0.8570   0.02286   0.01487  -0.0516   0.9740   0.0925
  -9.750  -0.8267   0.02233   0.01426  -0.0527   0.9700   0.0966
  -9.500  -0.7952   0.02171   0.01365  -0.0541   0.9671   0.1005
  -9.250  -0.7692   0.02122   0.01313  -0.0542   0.9612   0.1046
  -9.000  -0.7393   0.02069   0.01258  -0.0550   0.9565   0.1089
  -8.750  -0.7056   0.02014   0.01202  -0.0566   0.9530   0.1139
  -8.500  -0.6780   0.01968   0.01152  -0.0568   0.9462   0.1187
  -8.250  -0.6491   0.01915   0.01102  -0.0574   0.9398   0.1239
  -8.000  -0.6157   0.01869   0.01051  -0.0587   0.9357   0.1298
  -7.750  -0.5935   0.01825   0.01011  -0.0578   0.9271   0.1351
  -7.500  -0.5637   0.01786   0.00967  -0.0583   0.9214   0.1415
  -7.250  -0.5351   0.01739   0.00925  -0.0586   0.9159   0.1483
  -6.750  -0.4818   0.01663   0.00850  -0.0583   0.9013   0.1635
  -6.500  -0.4567   0.01630   0.00819  -0.0578   0.8929   0.1720
  -6.250  -0.4295   0.01596   0.00786  -0.0576   0.8851   0.1822
  -6.000  -0.4018   0.01561   0.00755  -0.0576   0.8779   0.1930
  -5.750  -0.3766   0.01534   0.00729  -0.0571   0.8684   0.2042
  -5.500  -0.3469   0.01505   0.00698  -0.0573   0.8614   0.2167
  -5.250  -0.3227   0.01481   0.00679  -0.0566   0.8507   0.2285
  -5.000  -0.2942   0.01454   0.00651  -0.0566   0.8426   0.2404
  -4.750  -0.2686   0.01436   0.00632  -0.0560   0.8319   0.2522
  -4.500  -0.2407   0.01411   0.00607  -0.0559   0.8228   0.2643
  -4.250  -0.2151   0.01392   0.00590  -0.0553   0.8117   0.2754
  -4.000  -0.1870   0.01374   0.00567  -0.0552   0.8021   0.2877
  -3.750  -0.1616   0.01355   0.00552  -0.0546   0.7903   0.2995
  -3.500  -0.1344   0.01338   0.00533  -0.0543   0.7798   0.3119
  -3.250  -0.1081   0.01323   0.00518  -0.0539   0.7681   0.3254
  -3.000  -0.0818   0.01307   0.00504  -0.0534   0.7568   0.3392
  -2.750  -0.0553   0.01293   0.00490  -0.0530   0.7451   0.3543
  -2.500  -0.0293   0.01281   0.00479  -0.0525   0.7331   0.3710
  -2.250  -0.0029   0.01268   0.00467  -0.0521   0.7217   0.3904
  -2.000   0.0224   0.01254   0.00461  -0.0515   0.7092   0.4128
  -1.750   0.0479   0.01242   0.00454  -0.0509   0.6974   0.4384
  -1.500   0.0734   0.01232   0.00449  -0.0502   0.6852   0.4652
  -1.000   0.1246   0.01217   0.00442  -0.0490   0.6616   0.5168
  -0.750   0.1501   0.01211   0.00443  -0.0484   0.6493   0.5417
  -0.500   0.1758   0.01207   0.00442  -0.0478   0.6380   0.5662
  -0.250   0.2016   0.01205   0.00443  -0.0472   0.6263   0.5897
   0.000   0.2274   0.01203   0.00445  -0.0466   0.6153   0.6124
   0.250   0.2531   0.01204   0.00447  -0.0459   0.6042   0.6350
   0.500   0.2789   0.01204   0.00452  -0.0453   0.5934   0.6575
   0.750   0.3046   0.01207   0.00456  -0.0446   0.5833   0.6795
   1.000   0.3303   0.01209   0.00464  -0.0440   0.5726   0.7019
   1.500   0.3808   0.01220   0.00481  -0.0424   0.5501   0.7480
   1.750   0.4060   0.01228   0.00491  -0.0416   0.5388   0.7706
   2.000   0.4314   0.01237   0.00504  -0.0409   0.5280   0.7936
   2.250   0.4573   0.01249   0.00518  -0.0402   0.5189   0.8161
   2.500   0.4835   0.01261   0.00533  -0.0395   0.5093   0.8379
   2.750   0.5101   0.01277   0.00548  -0.0390   0.5004   0.8586
   3.000   0.5377   0.01293   0.00566  -0.0387   0.4909   0.8791
   3.250   0.5663   0.01314   0.00584  -0.0385   0.4823   0.8993
   3.500   0.5969   0.01332   0.00605  -0.0389   0.4723   0.9181
   3.750   0.6279   0.01356   0.00624  -0.0393   0.4629   0.9342
   4.000   0.6604   0.01375   0.00645  -0.0402   0.4529   0.9472
   4.250   0.6953   0.01400   0.00664  -0.0417   0.4431   0.9565
   4.500   0.7282   0.01420   0.00684  -0.0427   0.4321   0.9665
   4.750   0.7642   0.01445   0.00704  -0.0445   0.4214   0.9738
   5.000   0.7989   0.01469   0.00725  -0.0461   0.4087   0.9811
   5.250   0.8351   0.01495   0.00746  -0.0481   0.3939   0.9872
   5.500   0.8696   0.01523   0.00769  -0.0498   0.3794   0.9935
   5.750   0.9049   0.01553   0.00793  -0.0516   0.3661   0.9990
   6.000   0.9224   0.01574   0.00811  -0.0499   0.3551   1.0000
   6.250   0.9353   0.01597   0.00830  -0.0471   0.3453   1.0000
   6.500   0.9478   0.01621   0.00850  -0.0444   0.3349   1.0000
   6.750   0.9612   0.01646   0.00873  -0.0417   0.3251   1.0000
   7.000   0.9729   0.01676   0.00897  -0.0388   0.3150   1.0000
   7.250   0.9865   0.01703   0.00923  -0.0362   0.3048   1.0000
   7.500   0.9982   0.01739   0.00953  -0.0334   0.2951   1.0000
   7.750   1.0113   0.01771   0.00984  -0.0308   0.2845   1.0000
   8.000   1.0225   0.01809   0.01018  -0.0279   0.2748   1.0000
   8.250   1.0344   0.01851   0.01056  -0.0253   0.2642   1.0000
   8.500   1.0479   0.01896   0.01099  -0.0230   0.2539   1.0000
   8.750   1.0598   0.01951   0.01148  -0.0206   0.2441   1.0000
   9.000   1.0742   0.02002   0.01200  -0.0187   0.2339   1.0000
   9.250   1.0872   0.02064   0.01258  -0.0167   0.2248   1.0000
   9.500   1.1002   0.02129   0.01321  -0.0148   0.2152   1.0000
   9.750   1.1138   0.02196   0.01388  -0.0130   0.2063   1.0000
  10.000   1.1251   0.02276   0.01464  -0.0111   0.1974   1.0000
  10.250   1.1391   0.02349   0.01539  -0.0096   0.1883   1.0000
  10.500   1.1501   0.02439   0.01627  -0.0079   0.1799   1.0000
  10.750   1.1624   0.02527   0.01716  -0.0064   0.1709   1.0000
  11.000   1.1735   0.02625   0.01814  -0.0049   0.1628   1.0000
  11.250   1.1830   0.02737   0.01925  -0.0034   0.1548   1.0000
  11.500   1.1937   0.02847   0.02036  -0.0021   0.1473   1.0000
  11.750   1.2014   0.02980   0.02169  -0.0007   0.1406   1.0000
  12.000   1.2110   0.03107   0.02299   0.0004   0.1339   1.0000
  12.250   1.2173   0.03261   0.02453   0.0016   0.1284   1.0000
  12.500   1.2257   0.03406   0.02602   0.0026   0.1227   1.0000
  12.750   1.2300   0.03588   0.02784   0.0037   0.1179   1.0000
  13.000   1.2377   0.03748   0.02951   0.0045   0.1132   1.0000
  13.250   1.2419   0.03943   0.03148   0.0052   0.1089   1.0000
  13.500   1.2467   0.04140   0.03350   0.0059   0.1051   1.0000
  13.750   1.2514   0.04342   0.03558   0.0064   0.1012   1.0000
  14.000   1.2527   0.04583   0.03802   0.0068   0.0978   1.0000
  14.250   1.2573   0.04800   0.04027   0.0071   0.0944   1.0000
  14.500   1.2598   0.05045   0.04277   0.0073   0.0911   1.0000
  15.000   1.2625   0.05573   0.04817   0.0074   0.0853   1.0000
  15.250   1.2631   0.05856   0.05106   0.0072   0.0826   1.0000
  15.500   1.2613   0.06173   0.05428   0.0069   0.0804   1.0000
  15.750   1.2624   0.06460   0.05723   0.0066   0.0781   1.0000
  16.000   1.2623   0.06764   0.06036   0.0062   0.0759   1.0000
  16.250   1.2604   0.07098   0.06375   0.0056   0.0740   1.0000
  16.500   1.2569   0.07456   0.06736   0.0049   0.0724   1.0000
  16.750   1.2570   0.07771   0.07062   0.0043   0.0705   1.0000
  17.000   1.2557   0.08108   0.07408   0.0035   0.0688   1.0000
  17.250   1.2529   0.08471   0.07777   0.0026   0.0672   1.0000
  17.500   1.2488   0.08854   0.08163   0.0016   0.0659   1.0000
<< Back to NACA 2418 (naca2418-il)

Polar data table (+)

Polar graphs


<< Back to NACA 2418 (naca2418-il)