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GIII BL167 AIRFOIL (giiig-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GIII BL167 AIRFOIL (giiig-il)
Reynolds number: 100,000
Max Cl/Cd: 46.66 at α=4.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-giiig-il-100000.txt
Download as CSV file: xf-giiig-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GIII BL167 AIRFOIL                              
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.5758   0.11013   0.10528  -0.0028   1.0000   0.0748
  -9.250  -0.5855   0.10644   0.10167  -0.0097   1.0000   0.0756
  -9.000  -0.5965   0.10224   0.09752  -0.0169   1.0000   0.0758
  -8.750  -0.5741   0.09669   0.09198  -0.0091   1.0000   0.0786
  -8.500  -0.5675   0.09301   0.08831  -0.0090   1.0000   0.0814
  -8.250  -0.5684   0.08882   0.08417  -0.0121   1.0000   0.0840
  -8.000  -0.5739   0.08438   0.07975  -0.0169   1.0000   0.0864
  -7.750  -0.5865   0.08095   0.07611  -0.0244   1.0000   0.0892
  -7.500  -0.5832   0.07545   0.07060  -0.0253   1.0000   0.0909
  -7.250  -0.5693   0.07135   0.06661  -0.0234   1.0000   0.0943
  -7.000  -0.5630   0.06777   0.06294  -0.0245   1.0000   0.1000
  -6.750  -0.5605   0.06359   0.05855  -0.0262   1.0000   0.1055
  -6.500  -0.5539   0.06254   0.05706  -0.0264   1.0000   0.1172
  -6.250  -0.5401   0.05675   0.05164  -0.0251   1.0000   0.1233
  -6.000  -0.4949   0.04026   0.03554  -0.0247   1.0000   0.1379
  -5.750  -0.4926   0.03680   0.03194  -0.0233   1.0000   0.1488
  -5.500  -0.5114   0.04767   0.04205  -0.0227   1.0000   0.1615
  -5.250  -0.5006   0.04474   0.03910  -0.0211   1.0000   0.1767
  -5.000  -0.4895   0.04210   0.03644  -0.0192   1.0000   0.1944
  -4.750  -0.4733   0.02618   0.02108  -0.0143   1.0000   0.2105
  -4.500  -0.4338   0.03127   0.02337  -0.0150   1.0000   0.0741
  -4.250  -0.4157   0.02901   0.02070  -0.0130   1.0000   0.0747
  -4.000  -0.3959   0.02641   0.01777  -0.0113   1.0000   0.0734
  -3.750  -0.3743   0.02423   0.01523  -0.0098   1.0000   0.0731
  -3.500  -0.3514   0.02251   0.01314  -0.0083   1.0000   0.0747
  -3.250  -0.3296   0.02094   0.01150  -0.0074   1.0000   0.0825
  -3.000  -0.3062   0.01987   0.01016  -0.0062   1.0000   0.0896
  -2.750  -0.2831   0.01846   0.00884  -0.0054   1.0000   0.1016
  -2.500  -0.2609   0.01735   0.00784  -0.0046   1.0000   0.1199
  -2.250  -0.2392   0.01643   0.00707  -0.0037   1.0000   0.1468
  -2.000  -0.2171   0.01536   0.00627  -0.0031   1.0000   0.1944
  -1.750  -0.0337   0.01324   0.00634  -0.0243   1.0000   1.0000
  -1.500  -0.0415   0.01328   0.00632  -0.0193   1.0000   1.0000
  -1.250  -0.0536   0.01332   0.00632  -0.0136   1.0000   1.0000
  -1.000  -0.0631   0.01335   0.00629  -0.0084   1.0000   1.0000
  -0.750  -0.0653   0.01340   0.00625  -0.0043   1.0000   1.0000
  -0.500  -0.0586   0.01351   0.00625  -0.0017   1.0000   1.0000
  -0.250  -0.0455   0.01369   0.00632  -0.0002   1.0000   1.0000
   0.000  -0.0068   0.01402   0.00652  -0.0035   0.9945   1.0000
   0.250   0.0349   0.01434   0.00674  -0.0073   0.9865   1.0000
   0.500   0.0780   0.01469   0.00701  -0.0112   0.9786   1.0000
   0.750   0.1287   0.01500   0.00729  -0.0165   0.9695   1.0000
   1.000   0.1750   0.01521   0.00750  -0.0207   0.9579   1.0000
   1.250   0.2190   0.01542   0.00773  -0.0245   0.9471   1.0000
   1.500   0.2666   0.01559   0.00795  -0.0288   0.9378   1.0000
   1.750   0.3172   0.01567   0.00815  -0.0335   0.9286   1.0000
   2.000   0.3574   0.01577   0.00834  -0.0361   0.9169   1.0000
   2.250   0.3969   0.01582   0.00851  -0.0384   0.9051   1.0000
   2.500   0.4346   0.01584   0.00870  -0.0401   0.8927   1.0000
   2.750   0.4690   0.01583   0.00883  -0.0409   0.8792   1.0000
   3.000   0.4998   0.01580   0.00895  -0.0409   0.8644   1.0000
   3.250   0.5283   0.01571   0.00901  -0.0400   0.8480   1.0000
   3.500   0.5531   0.01521   0.00866  -0.0372   0.8219   1.0000
   3.750   0.5742   0.01449   0.00798  -0.0329   0.7883   1.0000
   4.000   0.5925   0.01411   0.00766  -0.0292   0.7523   1.0000
   4.250   0.6112   0.01373   0.00732  -0.0256   0.7083   1.0000
   4.500   0.6294   0.01349   0.00704  -0.0221   0.6449   1.0000
   4.750   0.6420   0.01376   0.00676  -0.0176   0.4835   1.0000
   5.000   0.6371   0.01712   0.00779  -0.0123   0.1508   1.0000
   5.250   0.6514   0.01898   0.00928  -0.0100   0.1056   1.0000
   5.500   0.6694   0.02048   0.01066  -0.0083   0.0887   1.0000
   5.750   0.6907   0.02224   0.01236  -0.0069   0.0801   1.0000
   6.000   0.7138   0.02425   0.01422  -0.0061   0.0710   1.0000
   6.250   0.7396   0.02590   0.01613  -0.0051   0.0660   1.0000
   6.500   0.7656   0.02814   0.01860  -0.0043   0.0632   1.0000
   6.750   0.7893   0.03098   0.02155  -0.0037   0.0598   1.0000
   7.000   0.8097   0.03365   0.02472  -0.0022   0.0570   1.0000
   7.250   0.8295   0.03706   0.02858  -0.0007   0.0573   1.0000
   7.500   0.8469   0.04190   0.03373   0.0004   0.0586   1.0000
   7.750   0.8594   0.04562   0.03857   0.0039   0.0675   1.0000
   9.750   0.7618   0.10090   0.09621  -0.0132   0.1460   1.0000
  10.000   0.6212   0.09850   0.09391  -0.0049   0.1571   1.0000
  10.250   0.6569   0.10168   0.09721   0.0002   0.1513   1.0000
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