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

GIII BL45 AIRFOIL (giiib-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: GIII BL45 AIRFOIL (giiib-il)
Reynolds number: 1,000,000
Max Cl/Cd: 70.33 at α=5.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-giiib-il-1000000-n5.txt
Download as CSV file: xf-giiib-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GIII BL45 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
  ------ -------- --------- --------- -------- -------- --------
 -15.500  -0.8804   0.12396   0.12223   0.0157   1.0000   0.0036
 -15.250  -1.1149   0.06705   0.06495  -0.0166   1.0000   0.0032
 -15.000  -1.1630   0.05279   0.05039  -0.0276   1.0000   0.0031
 -14.750  -1.1851   0.04655   0.04395  -0.0306   1.0000   0.0031
 -14.500  -1.1998   0.04220   0.03942  -0.0312   1.0000   0.0032
 -14.250  -1.2102   0.03883   0.03586  -0.0306   1.0000   0.0032
 -14.000  -1.2166   0.03615   0.03302  -0.0292   1.0000   0.0032
 -13.750  -1.2196   0.03394   0.03063  -0.0273   1.0000   0.0033
 -13.500  -1.2203   0.03203   0.02856  -0.0250   1.0000   0.0033
 -13.250  -1.2177   0.03041   0.02679  -0.0226   1.0000   0.0033
 -13.000  -1.2131   0.02894   0.02517  -0.0201   1.0000   0.0034
 -12.750  -1.2050   0.02762   0.02370  -0.0179   1.0000   0.0034
 -12.500  -1.1931   0.02638   0.02232  -0.0162   1.0000   0.0035
 -12.250  -1.1792   0.02524   0.02104  -0.0147   1.0000   0.0035
 -12.000  -1.1639   0.02418   0.01985  -0.0133   1.0000   0.0035
 -11.750  -1.1522   0.02262   0.01811  -0.0115   1.0000   0.0037
 -11.500  -1.1362   0.02147   0.01682  -0.0101   1.0000   0.0039
 -11.250  -1.1178   0.02056   0.01582  -0.0089   1.0000   0.0040
 -11.000  -1.0981   0.01980   0.01495  -0.0079   1.0000   0.0042
 -10.750  -1.0775   0.01910   0.01418  -0.0070   1.0000   0.0044
 -10.500  -1.0565   0.01846   0.01347  -0.0062   1.0000   0.0045
 -10.250  -1.0352   0.01784   0.01277  -0.0053   1.0000   0.0047
 -10.000  -1.0137   0.01724   0.01210  -0.0045   1.0000   0.0049
  -9.750  -0.9920   0.01666   0.01144  -0.0036   1.0000   0.0052
  -9.500  -0.9702   0.01611   0.01083  -0.0027   1.0000   0.0054
  -9.250  -0.9482   0.01560   0.01025  -0.0018   1.0000   0.0056
  -9.000  -0.9261   0.01516   0.00973  -0.0009   1.0000   0.0057
  -8.750  -0.9060   0.01452   0.00904   0.0003   1.0000   0.0062
  -8.500  -0.8835   0.01410   0.00860   0.0011   0.9994   0.0066
  -8.000  -0.8208   0.01323   0.00766  -0.0011   0.9871   0.0076
  -7.750  -0.7898   0.01281   0.00719  -0.0020   0.9786   0.0081
  -7.500  -0.7588   0.01244   0.00677  -0.0030   0.9683   0.0085
  -7.250  -0.7296   0.01197   0.00621  -0.0035   0.9534   0.0091
  -6.750  -0.6786   0.01131   0.00543  -0.0027   0.9175   0.0107
  -6.500  -0.6535   0.01107   0.00513  -0.0022   0.9044   0.0115
  -6.250  -0.6282   0.01083   0.00482  -0.0017   0.8931   0.0121
  -6.000  -0.6024   0.01060   0.00453  -0.0013   0.8832   0.0125
  -5.750  -0.5772   0.01029   0.00414  -0.0008   0.8743   0.0138
  -5.500  -0.5516   0.01003   0.00386  -0.0004   0.8660   0.0155
  -5.250  -0.5256   0.00981   0.00361  -0.0001   0.8586   0.0172
  -5.000  -0.4993   0.00962   0.00338   0.0002   0.8509   0.0187
  -4.750  -0.4733   0.00938   0.00313   0.0005   0.8439   0.0228
  -4.500  -0.4468   0.00920   0.00292   0.0007   0.8367   0.0261
  -4.250  -0.4205   0.00900   0.00272   0.0010   0.8290   0.0322
  -4.000  -0.3941   0.00884   0.00253   0.0012   0.8205   0.0378
  -3.750  -0.3676   0.00864   0.00235   0.0014   0.8123   0.0472
  -3.500  -0.3413   0.00845   0.00218   0.0017   0.8048   0.0597
  -3.250  -0.3149   0.00824   0.00202   0.0019   0.7969   0.0766
  -3.000  -0.2889   0.00801   0.00187   0.0022   0.7890   0.1037
  -2.750  -0.2628   0.00777   0.00174   0.0025   0.7805   0.1350
  -2.500  -0.2364   0.00759   0.00161   0.0027   0.7719   0.1603
  -2.250  -0.2098   0.00744   0.00150   0.0029   0.7618   0.1823
  -2.000  -0.1834   0.00727   0.00140   0.0031   0.7501   0.2110
  -1.500  -0.1360   0.00656   0.00112   0.0044   0.7095   0.3708
  -1.250  -0.1179   0.00589   0.00093   0.0061   0.6755   0.5442
  -0.750  -0.0698   0.00560   0.00083   0.0076   0.6268   0.6539
  -0.250  -0.0190   0.00552   0.00079   0.0086   0.5840   0.7154
   0.000   0.0064   0.00549   0.00079   0.0091   0.5647   0.7446
   0.250   0.0317   0.00547   0.00080   0.0097   0.5452   0.7755
   0.500   0.0572   0.00546   0.00083   0.0102   0.5270   0.8064
   0.750   0.0828   0.00548   0.00088   0.0108   0.5091   0.8347
   1.000   0.1086   0.00553   0.00094   0.0113   0.4892   0.8580
   1.250   0.1352   0.00560   0.00099   0.0116   0.4704   0.8731
   1.500   0.1623   0.00570   0.00103   0.0117   0.4481   0.8807
   1.750   0.1893   0.00583   0.00108   0.0118   0.4229   0.8870
   2.000   0.2161   0.00598   0.00114   0.0120   0.3947   0.8933
   2.250   0.2423   0.00621   0.00123   0.0122   0.3517   0.8995
   2.500   0.2677   0.00653   0.00135   0.0125   0.2992   0.9058
   2.750   0.2943   0.00675   0.00147   0.0127   0.2680   0.9111
   3.000   0.3211   0.00693   0.00158   0.0128   0.2476   0.9168
   3.250   0.3481   0.00708   0.00169   0.0128   0.2319   0.9223
   3.500   0.3756   0.00723   0.00181   0.0128   0.2190   0.9275
   3.750   0.4027   0.00736   0.00193   0.0129   0.2081   0.9331
   4.000   0.4303   0.00751   0.00205   0.0129   0.1976   0.9378
   4.250   0.4581   0.00767   0.00220   0.0128   0.1890   0.9427
   4.500   0.4851   0.00781   0.00233   0.0128   0.1796   0.9481
   4.750   0.5133   0.00799   0.00248   0.0126   0.1693   0.9522
   5.000   0.5412   0.00821   0.00265   0.0124   0.1533   0.9565
   5.250   0.5679   0.00842   0.00282   0.0125   0.1393   0.9617
   5.500   0.5969   0.00863   0.00300   0.0121   0.1280   0.9651
   5.750   0.6259   0.00890   0.00320   0.0116   0.1104   0.9686
   6.000   0.6502   0.00945   0.00354   0.0119   0.0694   0.9739
   6.250   0.6783   0.01001   0.00397   0.0113   0.0404   0.9767
   6.500   0.7075   0.01043   0.00433   0.0107   0.0271   0.9794
   6.750   0.7359   0.01079   0.00466   0.0102   0.0195   0.9827
   7.000   0.7642   0.01115   0.00500   0.0098   0.0150   0.9856
   7.250   0.7958   0.01151   0.00536   0.0086   0.0126   0.9870
   7.500   0.8268   0.01190   0.00578   0.0076   0.0106   0.9886
   7.750   0.8572   0.01223   0.00614   0.0066   0.0096   0.9904
   8.000   0.8862   0.01262   0.00654   0.0060   0.0085   0.9925
   8.250   0.9139   0.01309   0.00704   0.0055   0.0075   0.9945
   8.500   0.9437   0.01352   0.00752   0.0047   0.0070   0.9957
   8.750   0.9731   0.01394   0.00798   0.0039   0.0066   0.9970
   9.000   1.0018   0.01439   0.00850   0.0031   0.0061   0.9984
   9.250   1.0300   0.01488   0.00902   0.0025   0.0057   0.9997
   9.500   1.0502   0.01533   0.00951   0.0036   0.0053   1.0000
   9.750   1.0662   0.01587   0.01009   0.0055   0.0049   1.0000
  10.000   1.0819   0.01646   0.01074   0.0074   0.0046   1.0000
  10.250   1.0995   0.01690   0.01124   0.0090   0.0045   1.0000
  10.500   1.1167   0.01740   0.01179   0.0106   0.0043   1.0000
  10.750   1.1333   0.01796   0.01243   0.0123   0.0041   1.0000
  11.000   1.1500   0.01856   0.01310   0.0138   0.0040   1.0000
  11.250   1.1667   0.01919   0.01380   0.0153   0.0038   1.0000
  11.500   1.1833   0.01985   0.01452   0.0167   0.0036   1.0000
  11.750   1.1994   0.02055   0.01528   0.0181   0.0035   1.0000
  12.000   1.2149   0.02129   0.01610   0.0195   0.0034   1.0000
  12.250   1.2287   0.02209   0.01697   0.0211   0.0033   1.0000
  12.500   1.2391   0.02298   0.01793   0.0231   0.0031   1.0000
  12.750   1.2472   0.02403   0.01908   0.0252   0.0030   1.0000
  13.000   1.2527   0.02534   0.02050   0.0273   0.0029   1.0000
  13.250   1.2546   0.02701   0.02232   0.0293   0.0028   1.0000
  13.500   1.2549   0.02897   0.02441   0.0308   0.0028   1.0000
  13.750   1.2597   0.03067   0.02622   0.0318   0.0027   1.0000
  14.000   1.2628   0.03264   0.02831   0.0324   0.0027   1.0000
  14.250   1.2649   0.03486   0.03065   0.0328   0.0027   1.0000
  14.500   1.2653   0.03740   0.03332   0.0327   0.0027   1.0000
  14.750   1.2637   0.04037   0.03641   0.0322   0.0026   1.0000
  15.000   1.2596   0.04387   0.04005   0.0312   0.0026   1.0000
  15.250   1.2532   0.04792   0.04424   0.0297   0.0026   1.0000
  15.500   1.2436   0.05268   0.04914   0.0276   0.0026   1.0000
  15.750   1.2312   0.05812   0.05472   0.0249   0.0026   1.0000
  16.000   1.2155   0.06433   0.06108   0.0217   0.0026   1.0000
  16.250   1.1958   0.07152   0.06842   0.0179   0.0026   1.0000
  16.500   1.1734   0.07951   0.07656   0.0136   0.0026   1.0000
  16.750   1.1480   0.08832   0.08551   0.0091   0.0026   1.0000
  17.000   1.1209   0.09747   0.09479   0.0046   0.0026   1.0000
<< Back to GIII BL45 AIRFOIL (giiib-il)

Polar data table (+)

Polar graphs


<< Back to GIII BL45 AIRFOIL (giiib-il)