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BOEING 106 AIRFOIL (boe106-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: BOEING 106 AIRFOIL (boe106-il)
Reynolds number: 500,000
Max Cl/Cd: 98.8 at α=6°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-boe106-il-500000.txt
Download as CSV file: xf-boe106-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: BOEING 106 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.7283   0.04296   0.04005  -0.0699   1.0000   0.0242
 -10.750  -0.7433   0.03967   0.03652  -0.0678   0.9971   0.0245
 -10.500  -0.7308   0.03531   0.03174  -0.0705   0.9918   0.0254
 -10.250  -0.7166   0.03115   0.02699  -0.0723   0.9859   0.0265
 -10.000  -0.6949   0.02764   0.02300  -0.0743   0.9828   0.0275
  -9.750  -0.6672   0.02650   0.02181  -0.0754   0.9781   0.0282
  -9.500  -0.6363   0.02566   0.02093  -0.0769   0.9743   0.0289
  -9.250  -0.6054   0.02452   0.01964  -0.0784   0.9709   0.0298
  -9.000  -0.5803   0.02337   0.01827  -0.0785   0.9637   0.0310
  -8.750  -0.5532   0.02256   0.01719  -0.0787   0.9571   0.0319
  -8.500  -0.5332   0.02052   0.01495  -0.0780   0.9483   0.0329
  -8.250  -0.5085   0.01971   0.01410  -0.0776   0.9410   0.0337
  -8.000  -0.4854   0.01910   0.01341  -0.0769   0.9324   0.0346
  -7.750  -0.4610   0.01854   0.01275  -0.0762   0.9251   0.0357
  -7.500  -0.4373   0.01795   0.01204  -0.0754   0.9166   0.0368
  -7.250  -0.4127   0.01742   0.01135  -0.0747   0.9092   0.0376
  -7.000  -0.3890   0.01646   0.01025  -0.0740   0.9011   0.0384
  -6.750  -0.3654   0.01547   0.00922  -0.0733   0.8937   0.0396
  -6.500  -0.3403   0.01501   0.00874  -0.0728   0.8861   0.0408
  -6.250  -0.3150   0.01456   0.00822  -0.0723   0.8785   0.0420
  -6.000  -0.2894   0.01408   0.00767  -0.0717   0.8713   0.0431
  -5.750  -0.2637   0.01367   0.00718  -0.0712   0.8635   0.0441
  -5.500  -0.2371   0.01344   0.00685  -0.0708   0.8565   0.0450
  -5.250  -0.2139   0.01252   0.00592  -0.0700   0.8485   0.0469
  -5.000  -0.1882   0.01213   0.00548  -0.0696   0.8418   0.0484
  -4.750  -0.1625   0.01179   0.00513  -0.0691   0.8337   0.0500
  -4.500  -0.1363   0.01151   0.00476  -0.0686   0.8268   0.0518
  -4.250  -0.1098   0.01128   0.00450  -0.0683   0.8188   0.0534
  -4.000  -0.0850   0.01080   0.00398  -0.0677   0.8115   0.0569
  -3.750  -0.0588   0.01055   0.00371  -0.0673   0.8035   0.0601
  -3.500  -0.0323   0.01031   0.00342  -0.0668   0.7959   0.0642
  -3.250  -0.0063   0.01003   0.00317  -0.0664   0.7876   0.0725
  -3.000   0.0195   0.00973   0.00295  -0.0659   0.7790   0.0961
  -2.750   0.0453   0.00946   0.00280  -0.0655   0.7691   0.1331
  -2.500   0.0716   0.00927   0.00264  -0.0651   0.7601   0.1591
  -2.250   0.0974   0.00902   0.00250  -0.0647   0.7504   0.1928
  -2.000   0.1219   0.00863   0.00239  -0.0642   0.7418   0.2779
  -1.750   0.1462   0.00826   0.00230  -0.0636   0.7327   0.3685
  -1.500   0.1699   0.00786   0.00222  -0.0629   0.7238   0.4677
  -1.250   0.1907   0.00737   0.00217  -0.0614   0.7146   0.6075
  -1.000   0.2127   0.00707   0.00219  -0.0600   0.7048   0.7113
  -0.750   0.2361   0.00690   0.00220  -0.0588   0.6955   0.7787
  -0.500   0.2607   0.00678   0.00224  -0.0577   0.6855   0.8389
  -0.250   0.2881   0.00677   0.00232  -0.0571   0.6756   0.8924
   0.250   0.3517   0.00696   0.00244  -0.0581   0.6538   0.9423
   0.500   0.3848   0.00707   0.00249  -0.0589   0.6428   0.9565
   0.750   0.4197   0.00721   0.00254  -0.0603   0.6320   0.9677
   1.000   0.4614   0.00732   0.00258  -0.0631   0.6202   0.9741
   1.250   0.4999   0.00745   0.00263  -0.0654   0.6085   0.9825
   1.500   0.5456   0.00755   0.00265  -0.0692   0.5965   0.9877
   1.750   0.5890   0.00767   0.00268  -0.0726   0.5845   0.9943
   2.000   0.6345   0.00774   0.00269  -0.0765   0.5725   0.9993
   2.250   0.6622   0.00782   0.00272  -0.0767   0.5622   1.0000
   2.500   0.6860   0.00793   0.00276  -0.0760   0.5525   1.0000
   2.750   0.7098   0.00802   0.00282  -0.0753   0.5415   1.0000
   3.000   0.7333   0.00814   0.00289  -0.0745   0.5297   1.0000
   3.250   0.7563   0.00827   0.00296  -0.0736   0.5179   1.0000
   3.500   0.7791   0.00843   0.00305  -0.0727   0.5063   1.0000
   3.750   0.8023   0.00854   0.00315  -0.0718   0.4947   1.0000
   4.000   0.8252   0.00868   0.00326  -0.0709   0.4842   1.0000
   4.500   0.8706   0.00899   0.00350  -0.0690   0.4627   1.0000
   4.750   0.8930   0.00915   0.00363  -0.0680   0.4513   1.0000
   5.000   0.9150   0.00934   0.00377  -0.0668   0.4395   1.0000
   5.250   0.9364   0.00954   0.00392  -0.0657   0.4258   1.0000
   5.500   0.9580   0.00974   0.00408  -0.0645   0.4116   1.0000
   5.750   0.9800   0.00993   0.00425  -0.0634   0.3993   1.0000
   6.000   1.0018   0.01014   0.00444  -0.0623   0.3883   1.0000
   6.250   1.0230   0.01038   0.00464  -0.0611   0.3771   1.0000
   6.500   1.0444   0.01061   0.00485  -0.0600   0.3658   1.0000
   6.750   1.0665   0.01083   0.00507  -0.0590   0.3552   1.0000
   7.000   1.0880   0.01109   0.00531  -0.0579   0.3443   1.0000
   7.250   1.1089   0.01139   0.00557  -0.0567   0.3319   1.0000
   7.500   1.1300   0.01168   0.00584  -0.0556   0.3181   1.0000
   7.750   1.1510   0.01199   0.00612  -0.0545   0.3031   1.0000
   8.000   1.1713   0.01235   0.00644  -0.0533   0.2856   1.0000
   8.250   1.1906   0.01277   0.00679  -0.0520   0.2609   1.0000
   8.500   1.2053   0.01345   0.00727  -0.0501   0.2215   1.0000
   8.750   1.2156   0.01440   0.00795  -0.0475   0.1805   1.0000
   9.000   1.2279   0.01517   0.00861  -0.0452   0.1601   1.0000
   9.250   1.2411   0.01584   0.00922  -0.0431   0.1465   1.0000
   9.500   1.2549   0.01649   0.00984  -0.0411   0.1347   1.0000
   9.750   1.2683   0.01718   0.01050  -0.0392   0.1238   1.0000
  10.250   1.2960   0.01859   0.01187  -0.0357   0.1049   1.0000
  10.500   1.3090   0.01938   0.01265  -0.0340   0.0975   1.0000
  10.750   1.3222   0.02018   0.01345  -0.0325   0.0911   1.0000
  11.000   1.3346   0.02106   0.01435  -0.0309   0.0857   1.0000
  11.250   1.3478   0.02190   0.01522  -0.0295   0.0809   1.0000
  11.500   1.3568   0.02307   0.01638  -0.0279   0.0766   1.0000
  11.750   1.3705   0.02394   0.01733  -0.0267   0.0737   1.0000
  12.000   1.3824   0.02498   0.01840  -0.0255   0.0704   1.0000
  12.250   1.3907   0.02630   0.01974  -0.0242   0.0671   1.0000
  12.500   1.4003   0.02758   0.02108  -0.0230   0.0644   1.0000
  12.750   1.4122   0.02871   0.02229  -0.0221   0.0618   1.0000
  13.000   1.4210   0.03012   0.02373  -0.0211   0.0591   1.0000
  13.250   1.4247   0.03201   0.02564  -0.0199   0.0563   1.0000
  13.500   1.4358   0.03330   0.02703  -0.0192   0.0540   1.0000
  13.750   1.4448   0.03480   0.02860  -0.0185   0.0511   1.0000
  14.000   1.4483   0.03685   0.03067  -0.0177   0.0481   1.0000
  14.250   1.4567   0.03848   0.03239  -0.0172   0.0450   1.0000
  14.500   1.4611   0.04054   0.03447  -0.0166   0.0413   1.0000
  14.750   1.4652   0.04268   0.03666  -0.0161   0.0372   1.0000
  15.000   1.4644   0.04539   0.03939  -0.0157   0.0331   1.0000
  15.250   1.4643   0.04812   0.04217  -0.0154   0.0294   1.0000
  15.500   1.4612   0.05127   0.04538  -0.0152   0.0268   1.0000
  15.750   1.4575   0.05457   0.04874  -0.0152   0.0247   1.0000
  16.000   1.4505   0.05840   0.05261  -0.0154   0.0233   1.0000
  16.250   1.4477   0.06178   0.05611  -0.0157   0.0221   1.0000
  16.500   1.4428   0.06551   0.05992  -0.0162   0.0211   1.0000
  16.750   1.4355   0.06963   0.06412  -0.0169   0.0203   1.0000
  17.000   1.4248   0.07431   0.06888  -0.0177   0.0196   1.0000
  17.250   1.4174   0.07858   0.07325  -0.0186   0.0191   1.0000
  17.500   1.4113   0.08273   0.07752  -0.0196   0.0185   1.0000
  17.750   1.4043   0.08711   0.08201  -0.0207   0.0180   1.0000
  18.000   1.3964   0.09167   0.08666  -0.0219   0.0176   1.0000
  18.250   1.3875   0.09641   0.09151  -0.0233   0.0172   1.0000
  18.500   1.3774   0.10141   0.09660  -0.0249   0.0169   1.0000
  18.750   1.3661   0.10669   0.10195  -0.0267   0.0165   1.0000
  19.000   1.3540   0.11213   0.10748  -0.0287   0.0162   1.0000
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