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

NASA SC(2)-0518 AIRFOIL (sc20518-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: NASA SC(2)-0518 AIRFOIL (sc20518-il)
Reynolds number: 1,000,000
Max Cl/Cd: 78.06 at α=8°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-sc20518-il-1000000-n5.txt
Download as CSV file: xf-sc20518-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NASA SC(2)-0518 AIRFOIL                         
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -19.750  -1.3481   0.07068   0.06587  -0.0561   1.0000   0.0332
 -19.500  -1.3485   0.06753   0.06265  -0.0572   1.0000   0.0335
 -19.250  -1.3487   0.06443   0.05950  -0.0582   1.0000   0.0339
 -19.000  -1.3462   0.06170   0.05672  -0.0590   1.0000   0.0344
 -18.750  -1.3428   0.05915   0.05412  -0.0597   1.0000   0.0349
 -18.500  -1.3379   0.05680   0.05172  -0.0602   1.0000   0.0354
 -18.250  -1.3320   0.05459   0.04946  -0.0607   1.0000   0.0359
 -18.000  -1.3244   0.05257   0.04741  -0.0611   1.0000   0.0364
 -17.750  -1.3173   0.05054   0.04532  -0.0615   1.0000   0.0369
 -17.500  -1.3078   0.04880   0.04354  -0.0618   1.0000   0.0374
 -17.250  -1.2998   0.04694   0.04163  -0.0620   1.0000   0.0378
 -17.000  -1.2914   0.04512   0.03978  -0.0622   1.0000   0.0384
 -16.750  -1.2815   0.04350   0.03814  -0.0623   1.0000   0.0390
 -16.500  -1.2717   0.04187   0.03648  -0.0625   1.0000   0.0396
 -16.250  -1.2603   0.04044   0.03502  -0.0625   1.0000   0.0403
 -16.000  -1.2482   0.03908   0.03363  -0.0625   1.0000   0.0409
 -15.750  -1.2363   0.03771   0.03222  -0.0625   1.0000   0.0415
 -15.500  -1.2233   0.03648   0.03096  -0.0624   1.0000   0.0420
 -15.250  -1.2106   0.03527   0.02972  -0.0622   1.0000   0.0425
 -15.000  -1.1989   0.03397   0.02841  -0.0620   1.0000   0.0432
 -14.750  -1.1863   0.03280   0.02722  -0.0617   1.0000   0.0439
 -14.500  -1.1728   0.03175   0.02615  -0.0614   1.0000   0.0446
 -14.250  -1.1598   0.03071   0.02509  -0.0609   1.0000   0.0453
 -14.000  -1.1468   0.02972   0.02409  -0.0604   1.0000   0.0460
 -13.750  -1.1337   0.02886   0.02320  -0.0596   1.0000   0.0466
 -13.500  -1.1220   0.02802   0.02234  -0.0585   1.0000   0.0472
 -13.250  -1.1137   0.02710   0.02141  -0.0570   1.0000   0.0478
 -13.000  -1.1065   0.02628   0.02058  -0.0552   1.0000   0.0485
 -12.750  -1.0885   0.02537   0.01967  -0.0553   0.9987   0.0493
 -12.500  -1.0649   0.02446   0.01875  -0.0565   0.9964   0.0502
 -12.250  -1.0399   0.02365   0.01792  -0.0578   0.9940   0.0510
 -12.000  -1.0134   0.02287   0.01713  -0.0592   0.9919   0.0518
 -11.750  -0.9888   0.02212   0.01635  -0.0602   0.9884   0.0524
 -11.500  -0.9644   0.02133   0.01556  -0.0612   0.9835   0.0532
 -11.250  -0.9379   0.02055   0.01478  -0.0626   0.9791   0.0543
 -11.000  -0.9145   0.01983   0.01406  -0.0632   0.9728   0.0554
 -10.750  -0.8913   0.01915   0.01337  -0.0637   0.9658   0.0565
 -10.500  -0.8690   0.01852   0.01273  -0.0639   0.9586   0.0574
 -10.250  -0.8480   0.01794   0.01212  -0.0638   0.9491   0.0581
 -10.000  -0.8281   0.01735   0.01151  -0.0635   0.9396   0.0591
  -9.750  -0.8056   0.01676   0.01090  -0.0637   0.9304   0.0604
  -9.500  -0.7819   0.01623   0.01036  -0.0640   0.9218   0.0617
  -9.250  -0.7572   0.01574   0.00983  -0.0644   0.9135   0.0630
  -9.000  -0.7314   0.01529   0.00936  -0.0650   0.9061   0.0643
  -8.750  -0.7050   0.01483   0.00889  -0.0656   0.8978   0.0658
  -8.500  -0.6780   0.01436   0.00840  -0.0664   0.8904   0.0676
  -8.250  -0.6500   0.01395   0.00798  -0.0673   0.8832   0.0695
  -8.000  -0.6213   0.01358   0.00758  -0.0683   0.8765   0.0713
  -7.750  -0.5919   0.01318   0.00717  -0.0694   0.8708   0.0733
  -7.500  -0.5619   0.01279   0.00680  -0.0706   0.8645   0.0759
  -7.250  -0.5314   0.01246   0.00645  -0.0718   0.8578   0.0785
  -7.000  -0.5004   0.01211   0.00611  -0.0731   0.8518   0.0818
  -6.750  -0.4688   0.01179   0.00580  -0.0745   0.8460   0.0854
  -6.500  -0.4370   0.01147   0.00549  -0.0759   0.8399   0.0901
  -6.250  -0.4052   0.01121   0.00523  -0.0772   0.8338   0.0951
  -6.000  -0.3729   0.01093   0.00497  -0.0786   0.8281   0.0999
  -5.750  -0.3409   0.01070   0.00475  -0.0798   0.8212   0.1048
  -5.500  -0.3089   0.01047   0.00452  -0.0810   0.8141   0.1106
  -5.000  -0.2439   0.01003   0.00412  -0.0835   0.8016   0.1249
  -4.750  -0.2112   0.00980   0.00392  -0.0848   0.7949   0.1349
  -4.500  -0.1779   0.00955   0.00373  -0.0862   0.7894   0.1483
  -4.250  -0.1440   0.00928   0.00354  -0.0878   0.7838   0.1682
  -4.000  -0.1094   0.00897   0.00334  -0.0896   0.7778   0.1926
  -3.500  -0.0387   0.00834   0.00295  -0.0936   0.7667   0.2586
  -3.250  -0.0028   0.00803   0.00277  -0.0956   0.7602   0.2953
  -3.000   0.0349   0.00762   0.00254  -0.0983   0.7503   0.3516
  -2.750   0.0744   0.00715   0.00229  -0.1013   0.7346   0.4226
  -2.500   0.1118   0.00686   0.00217  -0.1037   0.7145   0.4898
  -2.250   0.1443   0.00685   0.00216  -0.1046   0.6963   0.5158
  -2.000   0.1756   0.00691   0.00217  -0.1052   0.6764   0.5288
  -1.750   0.2067   0.00697   0.00218  -0.1057   0.6585   0.5369
  -1.500   0.2380   0.00703   0.00221  -0.1063   0.6443   0.5468
  -1.250   0.2682   0.00716   0.00223  -0.1066   0.6220   0.5523
  -1.000   0.2986   0.00729   0.00228  -0.1070   0.5969   0.5576
  -0.750   0.3288   0.00743   0.00234  -0.1073   0.5684   0.5637
  -0.500   0.3569   0.00779   0.00245  -0.1073   0.5105   0.5699
  -0.250   0.3842   0.00826   0.00262  -0.1072   0.4377   0.5752
   0.000   0.4115   0.00872   0.00282  -0.1072   0.3732   0.5798
   0.250   0.4398   0.00906   0.00297  -0.1072   0.3295   0.5834
   0.500   0.4680   0.00940   0.00312  -0.1073   0.2891   0.5856
   0.750   0.4964   0.00970   0.00325  -0.1074   0.2542   0.5871
   1.000   0.5249   0.00997   0.00338  -0.1074   0.2243   0.5884
   1.250   0.5535   0.01023   0.00352  -0.1075   0.1985   0.5896
   1.500   0.5822   0.01048   0.00365  -0.1076   0.1787   0.5910
   1.750   0.6111   0.01069   0.00378  -0.1077   0.1644   0.5921
   2.000   0.6400   0.01088   0.00391  -0.1078   0.1516   0.5939
   2.250   0.6687   0.01108   0.00405  -0.1079   0.1396   0.5954
   2.500   0.6973   0.01130   0.00420  -0.1079   0.1274   0.5971
   3.000   0.7546   0.01168   0.00452  -0.1080   0.1127   0.6007
   3.250   0.7829   0.01190   0.00469  -0.1080   0.1064   0.6023
   3.500   0.8112   0.01210   0.00485  -0.1080   0.1013   0.6037
   3.750   0.8394   0.01230   0.00503  -0.1079   0.0971   0.6051
   4.000   0.8676   0.01249   0.00519  -0.1079   0.0924   0.6064
   4.250   0.8954   0.01272   0.00538  -0.1077   0.0880   0.6078
   4.500   0.9232   0.01293   0.00557  -0.1076   0.0842   0.6090
   4.750   0.9506   0.01317   0.00577  -0.1074   0.0810   0.6102
   5.000   0.9782   0.01337   0.00596  -0.1072   0.0787   0.6112
   5.250   1.0054   0.01361   0.00617  -0.1070   0.0761   0.6123
   5.500   1.0322   0.01386   0.00641  -0.1067   0.0736   0.6142
   5.750   1.0594   0.01406   0.00663  -0.1065   0.0720   0.6160
   6.000   1.0862   0.01429   0.00687  -0.1062   0.0703   0.6179
   6.250   1.1126   0.01455   0.00712  -0.1058   0.0685   0.6198
   6.500   1.1383   0.01484   0.00740  -0.1053   0.0665   0.6218
   6.750   1.1645   0.01507   0.00765  -0.1049   0.0651   0.6237
   7.000   1.1902   0.01533   0.00791  -0.1044   0.0635   0.6256
   7.250   1.2154   0.01562   0.00819  -0.1038   0.0619   0.6273
   7.500   1.2399   0.01593   0.00850  -0.1031   0.0603   0.6289
   7.750   1.2645   0.01622   0.00880  -0.1024   0.0592   0.6305
   8.000   1.2887   0.01651   0.00909  -0.1017   0.0578   0.6318
   8.250   1.3123   0.01682   0.00941  -0.1008   0.0563   0.6334
   8.500   1.3350   0.01717   0.00976  -0.0999   0.0548   0.6358
   8.750   1.3573   0.01751   0.01012  -0.0988   0.0536   0.6381
   9.000   1.3791   0.01784   0.01048  -0.0976   0.0525   0.6403
   9.250   1.3999   0.01819   0.01085  -0.0963   0.0514   0.6426
   9.500   1.4182   0.01857   0.01125  -0.0945   0.0503   0.6449
   9.750   1.4345   0.01900   0.01169  -0.0924   0.0492   0.6472
  10.000   1.4529   0.01946   0.01216  -0.0908   0.0483   0.6494
  10.250   1.4721   0.01990   0.01263  -0.0893   0.0474   0.6514
  10.500   1.4908   0.02038   0.01314  -0.0878   0.0465   0.6532
  10.750   1.5092   0.02090   0.01368  -0.0863   0.0454   0.6557
  11.000   1.5268   0.02147   0.01427  -0.0848   0.0443   0.6589
  11.250   1.5438   0.02209   0.01492  -0.0832   0.0434   0.6621
  11.500   1.5614   0.02267   0.01554  -0.0817   0.0428   0.6653
  11.750   1.5786   0.02328   0.01620  -0.0802   0.0421   0.6683
  12.000   1.5950   0.02395   0.01691  -0.0787   0.0414   0.6711
  12.250   1.6110   0.02467   0.01765  -0.0772   0.0407   0.6736
  12.750   1.6409   0.02628   0.01934  -0.0741   0.0393   0.6797
  13.000   1.6546   0.02720   0.02030  -0.0725   0.0386   0.6832
  13.250   1.6692   0.02807   0.02122  -0.0711   0.0382   0.6867
  13.500   1.6833   0.02899   0.02219  -0.0696   0.0378   0.6902
  13.750   1.6968   0.02997   0.02323  -0.0682   0.0373   0.6934
  14.000   1.7096   0.03102   0.02432  -0.0668   0.0368   0.6963
  14.250   1.7215   0.03215   0.02550  -0.0654   0.0363   0.6995
  14.500   1.7331   0.03334   0.02674  -0.0641   0.0357   0.7036
  14.750   1.7434   0.03466   0.02812  -0.0627   0.0352   0.7076
  15.000   1.7531   0.03606   0.02957  -0.0614   0.0347   0.7115
  15.250   1.7611   0.03761   0.03117  -0.0600   0.0342   0.7149
  15.500   1.7702   0.03909   0.03272  -0.0588   0.0340   0.7180
  15.750   1.7793   0.04061   0.03431  -0.0577   0.0337   0.7207
  16.000   1.7873   0.04228   0.03605  -0.0567   0.0334   0.7244
  16.250   1.7946   0.04404   0.03789  -0.0557   0.0331   0.7282
  16.500   1.8013   0.04589   0.03982  -0.0548   0.0328   0.7318
  16.750   1.8068   0.04792   0.04192  -0.0539   0.0325   0.7354
  17.000   1.8115   0.05009   0.04417  -0.0532   0.0322   0.7386
  17.250   1.8155   0.05239   0.04653  -0.0526   0.0319   0.7414
  17.500   1.8185   0.05484   0.04906  -0.0521   0.0316   0.7445
  17.750   1.8201   0.05751   0.05181  -0.0517   0.0314   0.7479
  18.000   1.8203   0.06041   0.05480  -0.0514   0.0311   0.7513
  18.250   1.8191   0.06354   0.05801  -0.0514   0.0308   0.7546
  18.500   1.8164   0.06694   0.06150  -0.0515   0.0306   0.7577
  18.750   1.8117   0.07067   0.06533  -0.0518   0.0303   0.7604
  19.000   1.8049   0.07476   0.06951  -0.0523   0.0301   0.7626
  19.250   1.7997   0.07873   0.07359  -0.0530   0.0299   0.7651
<< Back to NASA SC(2)-0518 AIRFOIL (sc20518-il)

Polar data table (+)

Polar graphs


<< Back to NASA SC(2)-0518 AIRFOIL (sc20518-il)