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GIII BL145 AIRFOIL (giiif-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GIII BL145 AIRFOIL (giiif-il)
Reynolds number: 1,000,000
Max Cl/Cd: 83.91 at α=3°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-giiif-il-1000000.txt
Download as CSV file: xf-giiif-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GIII BL145 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.4674   0.10099   0.09948  -0.0059   1.0000   0.0082
 -10.000  -0.4694   0.09637   0.09487  -0.0072   1.0000   0.0082
  -6.500  -0.5974   0.02072   0.01700  -0.0178   0.9985   0.0071
  -6.250  -0.5672   0.01805   0.01394  -0.0189   0.9954   0.0076
  -6.000  -0.5361   0.01633   0.01194  -0.0199   0.9918   0.0079
  -5.750  -0.5040   0.01526   0.01067  -0.0211   0.9872   0.0081
  -5.500  -0.4742   0.01256   0.00759  -0.0218   0.9825   0.0087
  -5.250  -0.4454   0.01145   0.00638  -0.0223   0.9737   0.0097
  -5.000  -0.4150   0.01082   0.00567  -0.0230   0.9648   0.0105
  -4.750  -0.3867   0.01029   0.00506  -0.0231   0.9530   0.0116
  -4.500  -0.3609   0.00984   0.00452  -0.0226   0.9387   0.0124
  -4.250  -0.3353   0.00957   0.00417  -0.0221   0.9241   0.0129
  -4.000  -0.3124   0.00869   0.00311  -0.0210   0.9098   0.0150
  -3.750  -0.2868   0.00844   0.00281  -0.0205   0.8972   0.0175
  -3.500  -0.2608   0.00823   0.00251  -0.0201   0.8854   0.0194
  -3.250  -0.2351   0.00788   0.00210  -0.0196   0.8740   0.0258
  -3.000  -0.2088   0.00764   0.00188  -0.0194   0.8637   0.0402
  -2.750  -0.1822   0.00749   0.00174  -0.0192   0.8545   0.0550
  -2.500  -0.1553   0.00737   0.00160  -0.0190   0.8457   0.0672
  -2.250  -0.1283   0.00724   0.00148  -0.0189   0.8374   0.0804
  -2.000  -0.1015   0.00709   0.00136  -0.0188   0.8296   0.1003
  -1.750  -0.0751   0.00684   0.00125  -0.0187   0.8211   0.1480
  -1.500  -0.0510   0.00622   0.00110  -0.0183   0.8122   0.3029
  -1.250  -0.0338   0.00487   0.00089  -0.0168   0.8024   0.6645
  -1.000  -0.0084   0.00469   0.00088  -0.0162   0.7924   0.7279
  -0.750   0.0177   0.00461   0.00087  -0.0158   0.7837   0.7657
  -0.500   0.0445   0.00458   0.00085  -0.0155   0.7753   0.7882
  -0.250   0.0712   0.00453   0.00084  -0.0152   0.7665   0.8101
   0.000   0.0981   0.00452   0.00084  -0.0149   0.7580   0.8279
   0.250   0.1249   0.00450   0.00084  -0.0146   0.7488   0.8446
   0.500   0.1515   0.00447   0.00086  -0.0143   0.7402   0.8623
   0.750   0.1779   0.00446   0.00087  -0.0139   0.7319   0.8799
   1.000   0.2040   0.00445   0.00091  -0.0134   0.7227   0.9000
   1.250   0.2304   0.00445   0.00094  -0.0130   0.7137   0.9152
   1.500   0.2573   0.00448   0.00097  -0.0127   0.7043   0.9267
   1.750   0.2845   0.00450   0.00101  -0.0125   0.6942   0.9373
   2.000   0.3122   0.00453   0.00105  -0.0125   0.6824   0.9477
   2.250   0.3397   0.00463   0.00108  -0.0124   0.6547   0.9579
   2.500   0.3676   0.00479   0.00112  -0.0124   0.6179   0.9677
   2.750   0.3995   0.00493   0.00121  -0.0134   0.5917   0.9738
   3.000   0.4296   0.00512   0.00129  -0.0140   0.5537   0.9811
   3.250   0.4601   0.00579   0.00146  -0.0151   0.4222   0.9855
   3.500   0.4923   0.00636   0.00169  -0.0166   0.3352   0.9892
   3.750   0.5231   0.00701   0.00195  -0.0179   0.2384   0.9933
   4.000   0.5545   0.00784   0.00230  -0.0194   0.1232   0.9961
   4.250   0.5872   0.00847   0.00264  -0.0211   0.0591   0.9988
   4.500   0.6154   0.00887   0.00293  -0.0215   0.0352   1.0000
   4.750   0.6373   0.00920   0.00324  -0.0205   0.0253   1.0000
   5.000   0.6595   0.00954   0.00357  -0.0195   0.0204   1.0000
   5.250   0.6811   0.01003   0.00414  -0.0183   0.0173   1.0000
   5.500   0.7045   0.01030   0.00443  -0.0175   0.0160   1.0000
   5.750   0.7277   0.01060   0.00474  -0.0168   0.0143   1.0000
   6.000   0.7498   0.01111   0.00529  -0.0158   0.0126   1.0000
   6.250   0.7680   0.01226   0.00661  -0.0141   0.0111   1.0000
   6.500   0.7919   0.01264   0.00702  -0.0135   0.0107   1.0000
   6.750   0.8152   0.01314   0.00757  -0.0128   0.0099   1.0000
   7.000   0.8392   0.01354   0.00801  -0.0123   0.0090   1.0000
   7.250   0.8634   0.01390   0.00838  -0.0119   0.0081   1.0000
   7.500   0.8832   0.01508   0.00965  -0.0107   0.0074   1.0000
   7.750   0.8986   0.01746   0.01229  -0.0088   0.0069   1.0000
   8.000   0.9219   0.01811   0.01304  -0.0083   0.0067   1.0000
   8.250   0.9442   0.01901   0.01406  -0.0076   0.0064   1.0000
   8.500   0.9655   0.02014   0.01534  -0.0068   0.0061   1.0000
   8.750   0.9860   0.02141   0.01678  -0.0059   0.0057   1.0000
   9.000   1.0058   0.02269   0.01821  -0.0050   0.0053   1.0000
   9.250   1.0241   0.02416   0.01987  -0.0040   0.0050   1.0000
   9.500   1.0403   0.02592   0.02184  -0.0028   0.0048   1.0000
   9.750   1.0510   0.02867   0.02490  -0.0010   0.0047   1.0000
  10.000   0.9444   0.05179   0.04962   0.0097   0.0063   1.0000
  10.250   0.9191   0.05633   0.05434   0.0115   0.0065   1.0000
  10.500   0.8916   0.06177   0.05994   0.0103   0.0066   1.0000
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