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GIII BL145 AIRFOIL (giiif-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GIII BL145 AIRFOIL (giiif-il)
Reynolds number: 500,000
Max Cl/Cd: 78.93 at α=3.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-giiif-il-500000.txt
Download as CSV file: xf-giiif-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.5854   0.08730   0.08517  -0.0069   1.0000   0.0147
  -8.500  -0.5873   0.08237   0.08026  -0.0113   1.0000   0.0148
  -8.250  -0.5928   0.07689   0.07478  -0.0172   1.0000   0.0148
  -8.000  -0.5922   0.07209   0.06994  -0.0207   1.0000   0.0151
  -7.750  -0.5889   0.06746   0.06524  -0.0233   1.0000   0.0154
  -7.500  -0.5835   0.06292   0.06062  -0.0252   1.0000   0.0158
  -7.250  -0.5759   0.05842   0.05600  -0.0265   1.0000   0.0165
  -7.000  -0.5662   0.05384   0.05128  -0.0272   1.0000   0.0175
  -6.750  -0.5423   0.05049   0.04770  -0.0271   1.0000   0.0198
  -6.500  -0.5307   0.04629   0.04328  -0.0262   1.0000   0.0199
  -5.250  -0.4723   0.02068   0.01578  -0.0185   0.9933   0.0166
  -5.000  -0.4417   0.01616   0.01056  -0.0186   0.9890   0.0156
  -4.750  -0.4069   0.01452   0.00869  -0.0201   0.9854   0.0167
  -4.500  -0.3710   0.01326   0.00726  -0.0218   0.9826   0.0180
  -4.250  -0.3383   0.01257   0.00648  -0.0228   0.9757   0.0196
  -4.000  -0.3067   0.01111   0.00488  -0.0238   0.9700   0.0225
  -3.750  -0.2765   0.01050   0.00422  -0.0243   0.9609   0.0256
  -3.500  -0.2458   0.01007   0.00372  -0.0249   0.9523   0.0293
  -3.250  -0.2185   0.00954   0.00317  -0.0248   0.9418   0.0403
  -3.000  -0.1929   0.00912   0.00280  -0.0243   0.9303   0.0598
  -2.750  -0.1669   0.00890   0.00258  -0.0239   0.9195   0.0764
  -2.500  -0.1410   0.00871   0.00237  -0.0235   0.9094   0.0938
  -2.250  -0.1157   0.00845   0.00217  -0.0230   0.8997   0.1211
  -2.000  -0.0920   0.00790   0.00198  -0.0224   0.8892   0.2179
  -1.750  -0.0805   0.00604   0.00173  -0.0199   0.8788   0.6792
  -1.500  -0.0572   0.00587   0.00172  -0.0186   0.8707   0.7583
  -1.250  -0.0327   0.00579   0.00172  -0.0177   0.8617   0.8001
  -1.000  -0.0075   0.00575   0.00170  -0.0169   0.8535   0.8268
  -0.750   0.0175   0.00574   0.00169  -0.0159   0.8447   0.8504
  -0.500   0.0426   0.00573   0.00169  -0.0151   0.8340   0.8709
  -0.250   0.0678   0.00573   0.00168  -0.0142   0.8237   0.8879
   0.000   0.0927   0.00576   0.00169  -0.0132   0.8146   0.9055
   0.250   0.1179   0.00579   0.00172  -0.0124   0.8049   0.9220
   0.500   0.1427   0.00584   0.00177  -0.0113   0.7954   0.9404
   0.750   0.1707   0.00591   0.00181  -0.0111   0.7867   0.9534
   1.000   0.2025   0.00595   0.00183  -0.0119   0.7777   0.9600
   1.250   0.2333   0.00599   0.00185  -0.0125   0.7689   0.9677
   1.500   0.2678   0.00605   0.00186  -0.0140   0.7605   0.9721
   1.750   0.3030   0.00607   0.00191  -0.0157   0.7505   0.9770
   2.000   0.3368   0.00611   0.00195  -0.0171   0.7408   0.9826
   2.250   0.3744   0.00615   0.00198  -0.0194   0.7304   0.9855
   2.500   0.4101   0.00617   0.00197  -0.0211   0.7065   0.9898
   2.750   0.4446   0.00623   0.00195  -0.0226   0.6701   0.9946
   3.000   0.4812   0.00631   0.00198  -0.0247   0.6417   0.9982
   3.250   0.5107   0.00647   0.00202  -0.0253   0.6003   1.0000
   3.500   0.5328   0.00678   0.00209  -0.0244   0.5260   1.0000
   3.750   0.5516   0.00757   0.00231  -0.0231   0.3932   1.0000
   4.000   0.5712   0.00829   0.00262  -0.0220   0.2947   1.0000
   4.250   0.5881   0.00935   0.00303  -0.0207   0.1531   1.0000
   4.500   0.6057   0.01034   0.00355  -0.0192   0.0606   1.0000
   4.750   0.6261   0.01103   0.00414  -0.0179   0.0376   1.0000
   5.000   0.6483   0.01146   0.00462  -0.0169   0.0310   1.0000
   5.250   0.6687   0.01220   0.00541  -0.0156   0.0259   1.0000
   5.500   0.6909   0.01272   0.00601  -0.0146   0.0235   1.0000
   5.750   0.7127   0.01336   0.00669  -0.0135   0.0213   1.0000
   6.000   0.7324   0.01436   0.00775  -0.0122   0.0188   1.0000
   6.250   0.7518   0.01565   0.00917  -0.0108   0.0171   1.0000
   6.500   0.7743   0.01652   0.01013  -0.0099   0.0162   1.0000
   6.750   0.7964   0.01764   0.01136  -0.0089   0.0151   1.0000
   7.000   0.8186   0.01896   0.01281  -0.0079   0.0142   1.0000
   7.250   0.8407   0.02039   0.01438  -0.0070   0.0134   1.0000
   7.500   0.8624   0.02140   0.01546  -0.0064   0.0123   1.0000
   7.750   0.8777   0.02542   0.01984  -0.0048   0.0114   1.0000
   8.000   0.8907   0.02963   0.02450  -0.0029   0.0113   1.0000
   8.250   0.9010   0.03353   0.02886  -0.0009   0.0112   1.0000
   8.500   0.9103   0.03696   0.03266   0.0011   0.0111   1.0000
   8.750   0.9274   0.03884   0.03469   0.0022   0.0116   1.0000
  17.250   0.8469   0.22165   0.21931  -0.0712   0.0091   1.0000
  17.500   0.8543   0.22541   0.22306  -0.0733   0.0086   1.0000
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