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BOEING 106 AIRFOIL (boe106-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: BOEING 106 AIRFOIL (boe106-il)
Reynolds number: 200,000
Max Cl/Cd: 72.1 at α=7.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-boe106-il-200000.txt
Download as CSV file: xf-boe106-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.2951   0.09062   0.08733  -0.0453   1.0000   0.0762
  -9.750  -0.2946   0.08868   0.08543  -0.0434   1.0000   0.0776
  -9.500  -0.3951   0.08793   0.08445  -0.0477   1.0000   0.0757
  -9.250  -0.3871   0.08603   0.08258  -0.0463   1.0000   0.0772
  -9.000  -0.3906   0.08355   0.08016  -0.0457   1.0000   0.0789
  -8.750  -0.4083   0.08130   0.07801  -0.0441   1.0000   0.0801
  -8.500  -0.4422   0.08010   0.07693  -0.0398   1.0000   0.0801
  -8.250  -0.4666   0.07654   0.07342  -0.0420   0.9964   0.0809
  -8.000  -0.4759   0.06221   0.05864  -0.0620   0.9829   0.0874
  -7.750  -0.4486   0.06003   0.05653  -0.0628   0.9781   0.0892
  -7.500  -0.4738   0.04013   0.03507  -0.0684   0.9642   0.0618
  -7.250  -0.4511   0.03535   0.02989  -0.0700   0.9586   0.0604
  -7.000  -0.4215   0.03099   0.02496  -0.0721   0.9555   0.0596
  -6.750  -0.3995   0.02869   0.02224  -0.0716   0.9472   0.0608
  -6.500  -0.3658   0.02642   0.01952  -0.0732   0.9433   0.0618
  -6.250  -0.3289   0.02467   0.01737  -0.0751   0.9404   0.0627
  -6.000  -0.3048   0.02273   0.01526  -0.0748   0.9328   0.0645
  -5.750  -0.2713   0.02156   0.01404  -0.0760   0.9280   0.0667
  -5.500  -0.2352   0.02043   0.01278  -0.0775   0.9245   0.0686
  -5.250  -0.2102   0.01965   0.01190  -0.0768   0.9161   0.0706
  -5.000  -0.1781   0.01894   0.01104  -0.0773   0.9107   0.0733
  -4.750  -0.1493   0.01782   0.00993  -0.0774   0.9051   0.0763
  -4.500  -0.1239   0.01722   0.00934  -0.0767   0.8969   0.0794
  -4.250  -0.0937   0.01660   0.00867  -0.0768   0.8918   0.0838
  -4.000  -0.0714   0.01604   0.00814  -0.0756   0.8824   0.0890
  -3.750  -0.0434   0.01555   0.00764  -0.0753   0.8764   0.0967
  -3.500  -0.0206   0.01506   0.00721  -0.0742   0.8674   0.1069
  -3.250   0.0056   0.01451   0.00670  -0.0735   0.8606   0.1292
  -3.000   0.0271   0.01386   0.00629  -0.0723   0.8515   0.1728
  -2.750   0.0510   0.01317   0.00591  -0.0714   0.8443   0.2413
  -2.500   0.0707   0.01251   0.00575  -0.0700   0.8348   0.3642
  -2.250   0.0902   0.01169   0.00554  -0.0681   0.8274   0.5204
  -2.000   0.1067   0.01116   0.00561  -0.0653   0.8171   0.6829
  -1.750   0.1317   0.01083   0.00554  -0.0635   0.8100   0.7837
  -1.500   0.1598   0.01079   0.00564  -0.0623   0.7993   0.8600
  -1.250   0.1978   0.01088   0.00569  -0.0630   0.7910   0.9109
  -1.000   0.2365   0.01100   0.00570  -0.0643   0.7813   0.9403
  -0.750   0.2790   0.01107   0.00565  -0.0668   0.7718   0.9562
  -0.500   0.3299   0.01110   0.00551  -0.0710   0.7630   0.9708
  -0.250   0.3819   0.01110   0.00540  -0.0758   0.7521   0.9843
   0.000   0.4351   0.01101   0.00518  -0.0810   0.7422   0.9961
   0.250   0.4695   0.01093   0.00499  -0.0826   0.7312   1.0000
   0.500   0.4928   0.01092   0.00491  -0.0820   0.7196   1.0000
   0.750   0.5166   0.01092   0.00481  -0.0813   0.7093   1.0000
   1.000   0.5403   0.01094   0.00473  -0.0806   0.6986   1.0000
   1.250   0.5634   0.01098   0.00472  -0.0798   0.6869   1.0000
   1.500   0.5869   0.01104   0.00470  -0.0790   0.6760   1.0000
   1.750   0.6109   0.01110   0.00466  -0.0783   0.6657   1.0000
   2.000   0.6339   0.01119   0.00472  -0.0774   0.6540   1.0000
   2.250   0.6574   0.01130   0.00477  -0.0766   0.6433   1.0000
   2.500   0.6817   0.01141   0.00477  -0.0759   0.6334   1.0000
   2.750   0.7043   0.01153   0.00488  -0.0749   0.6215   1.0000
   3.000   0.7276   0.01168   0.00498  -0.0740   0.6104   1.0000
   3.250   0.7516   0.01183   0.00505  -0.0732   0.6003   1.0000
   3.500   0.7744   0.01200   0.00520  -0.0723   0.5891   1.0000
   3.750   0.7975   0.01219   0.00536  -0.0713   0.5782   1.0000
   4.000   0.8208   0.01238   0.00548  -0.0704   0.5670   1.0000
   4.250   0.8435   0.01256   0.00559  -0.0694   0.5546   1.0000
   4.500   0.8653   0.01274   0.00577  -0.0682   0.5415   1.0000
   4.750   0.8876   0.01296   0.00597  -0.0671   0.5296   1.0000
   5.000   0.9105   0.01320   0.00615  -0.0662   0.5191   1.0000
   5.250   0.9327   0.01342   0.00634  -0.0651   0.5075   1.0000
   5.500   0.9542   0.01364   0.00659  -0.0639   0.4956   1.0000
   5.750   0.9764   0.01389   0.00681  -0.0628   0.4846   1.0000
   6.000   0.9986   0.01413   0.00699  -0.0618   0.4734   1.0000
   6.250   1.0194   0.01433   0.00725  -0.0605   0.4609   1.0000
   6.500   1.0403   0.01456   0.00749  -0.0592   0.4484   1.0000
   6.750   1.0615   0.01480   0.00773  -0.0580   0.4364   1.0000
   7.000   1.0829   0.01507   0.00798  -0.0569   0.4253   1.0000
   7.250   1.1036   0.01532   0.00828  -0.0556   0.4130   1.0000
   7.500   1.1240   0.01559   0.00859  -0.0544   0.4004   1.0000
   7.750   1.1439   0.01588   0.00890  -0.0530   0.3870   1.0000
   8.000   1.1631   0.01620   0.00924  -0.0516   0.3729   1.0000
   8.250   1.1814   0.01655   0.00961  -0.0501   0.3576   1.0000
   8.500   1.1984   0.01694   0.01000  -0.0483   0.3401   1.0000
   8.750   1.2132   0.01741   0.01044  -0.0463   0.3197   1.0000
   9.000   1.2260   0.01795   0.01097  -0.0440   0.2938   1.0000
   9.250   1.2342   0.01866   0.01158  -0.0410   0.2604   1.0000
   9.500   1.2367   0.01965   0.01237  -0.0373   0.2236   1.0000
   9.750   1.2377   0.02091   0.01343  -0.0338   0.1955   1.0000
  10.000   1.2403   0.02226   0.01464  -0.0308   0.1771   1.0000
  10.250   1.2439   0.02366   0.01598  -0.0281   0.1636   1.0000
  10.500   1.2473   0.02516   0.01740  -0.0257   0.1531   1.0000
  10.750   1.2540   0.02653   0.01877  -0.0237   0.1437   1.0000
  11.000   1.2611   0.02794   0.02020  -0.0218   0.1360   1.0000
  11.250   1.2684   0.02937   0.02162  -0.0202   0.1292   1.0000
  11.500   1.2766   0.03079   0.02308  -0.0186   0.1228   1.0000
  11.750   1.2849   0.03217   0.02451  -0.0173   0.1168   1.0000
  12.000   1.2918   0.03375   0.02607  -0.0159   0.1113   1.0000
  12.250   1.3002   0.03516   0.02760  -0.0150   0.1057   1.0000
  12.500   1.3056   0.03688   0.02927  -0.0138   0.1009   1.0000
  12.750   1.3137   0.03844   0.03096  -0.0128   0.0968   1.0000
  13.000   1.3208   0.04009   0.03272  -0.0120   0.0927   1.0000
  13.250   1.3259   0.04194   0.03456  -0.0111   0.0891   1.0000
  13.500   1.3319   0.04377   0.03648  -0.0102   0.0856   1.0000
  13.750   1.3372   0.04570   0.03855  -0.0096   0.0819   1.0000
  14.000   1.3405   0.04782   0.04072  -0.0091   0.0786   1.0000
  14.250   1.3438   0.04998   0.04289  -0.0084   0.0751   1.0000
  14.500   1.3461   0.05239   0.04549  -0.0082   0.0716   1.0000
  14.750   1.3471   0.05497   0.04815  -0.0081   0.0682   1.0000
  15.000   1.3475   0.05758   0.05076  -0.0077   0.0646   1.0000
  15.250   1.3463   0.06065   0.05403  -0.0080   0.0609   1.0000
  15.500   1.3443   0.06381   0.05721  -0.0084   0.0576   1.0000
  15.750   1.3412   0.06713   0.06062  -0.0085   0.0540   1.0000
  16.000   1.3378   0.07071   0.06432  -0.0092   0.0505   1.0000
  16.250   1.3350   0.07397   0.06752  -0.0094   0.0476   1.0000
  16.500   1.3303   0.07792   0.07168  -0.0102   0.0450   1.0000
  16.750   1.3272   0.08162   0.07548  -0.0110   0.0426   1.0000
  17.000   1.3250   0.08506   0.07892  -0.0117   0.0407   1.0000
  17.250   1.3221   0.08861   0.08258  -0.0121   0.0390   1.0000
  17.500   1.3174   0.09275   0.08689  -0.0133   0.0374   1.0000
  17.750   1.3139   0.09668   0.09093  -0.0145   0.0360   1.0000
  18.000   1.3122   0.10028   0.09456  -0.0156   0.0347   1.0000
  18.250   1.3131   0.10312   0.09736  -0.0158   0.0334   1.0000
  18.500   1.3048   0.10811   0.10259  -0.0178   0.0326   1.0000
  18.750   1.2969   0.11307   0.10774  -0.0198   0.0318   1.0000
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