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GIII BL167 AIRFOIL (giiig-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GIII BL167 AIRFOIL (giiig-il)
Reynolds number: 200,000
Max Cl/Cd: 65.89 at α=6.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-giiig-il-200000.txt
Download as CSV file: xf-giiig-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.4629   0.08640   0.08316  -0.0135   1.0000   0.0414
  -8.750  -0.4654   0.08207   0.07886  -0.0149   1.0000   0.0424
  -8.500  -0.4696   0.07752   0.07433  -0.0169   1.0000   0.0432
  -8.250  -0.4760   0.07273   0.06958  -0.0194   1.0000   0.0440
  -8.000  -0.5823   0.07671   0.07335  -0.0217   1.0000   0.0394
  -7.750  -0.5777   0.07309   0.06970  -0.0226   1.0000   0.0406
  -7.500  -0.5730   0.06911   0.06567  -0.0241   1.0000   0.0418
  -7.250  -0.5670   0.06506   0.06153  -0.0255   1.0000   0.0433
  -7.000  -0.5590   0.06095   0.05728  -0.0267   1.0000   0.0455
  -6.750  -0.5452   0.05891   0.05467  -0.0274   1.0000   0.0492
  -5.250  -0.4866   0.03699   0.03175  -0.0194   1.0000   0.0646
  -5.000  -0.4755   0.03461   0.02937  -0.0174   1.0000   0.0668
  -4.750  -0.4662   0.03342   0.02776  -0.0144   1.0000   0.0776
  -4.500  -0.4467   0.02665   0.02038  -0.0109   1.0000   0.0451
  -4.250  -0.4262   0.02281   0.01568  -0.0079   1.0000   0.0376
  -4.000  -0.4059   0.02059   0.01314  -0.0064   1.0000   0.0378
  -3.750  -0.3821   0.01844   0.01080  -0.0058   0.9996   0.0395
  -3.500  -0.3440   0.01749   0.00975  -0.0082   0.9958   0.0452
  -3.250  -0.3062   0.01624   0.00827  -0.0099   0.9923   0.0488
  -3.000  -0.2709   0.01478   0.00684  -0.0117   0.9880   0.0570
  -2.750  -0.2329   0.01388   0.00596  -0.0140   0.9839   0.0723
  -2.500  -0.1978   0.01309   0.00523  -0.0160   0.9784   0.0937
  -2.250  -0.1612   0.01240   0.00465  -0.0182   0.9729   0.1296
  -2.000  -0.1391   0.00954   0.00434  -0.0181   0.9692   0.7248
  -1.750  -0.1158   0.00947   0.00459  -0.0156   0.9616   0.8515
  -1.500  -0.0831   0.00962   0.00473  -0.0153   0.9571   0.9004
  -1.250  -0.0454   0.00984   0.00487  -0.0162   0.9535   0.9328
  -1.000  -0.0025   0.01003   0.00496  -0.0186   0.9496   0.9552
  -0.750   0.0805   0.01024   0.00506  -0.0289   0.9579   0.9790
  -0.500   0.1386   0.01013   0.00486  -0.0354   0.9566   0.9883
  -0.250   0.1800   0.01000   0.00469  -0.0386   0.9482   0.9923
   0.000   0.2207   0.00982   0.00448  -0.0415   0.9377   0.9957
   0.250   0.2581   0.00963   0.00425  -0.0435   0.9243   1.0000
   0.500   0.2792   0.00954   0.00413  -0.0422   0.9083   1.0000
   0.750   0.3004   0.00948   0.00405  -0.0409   0.8945   1.0000
   1.000   0.3220   0.00945   0.00400  -0.0398   0.8821   1.0000
   1.250   0.3440   0.00942   0.00396  -0.0387   0.8703   1.0000
   1.500   0.3663   0.00941   0.00395  -0.0377   0.8582   1.0000
   1.750   0.3887   0.00941   0.00397  -0.0368   0.8460   1.0000
   2.000   0.4111   0.00943   0.00400  -0.0358   0.8339   1.0000
   2.250   0.4337   0.00946   0.00407  -0.0347   0.8217   1.0000
   2.500   0.4563   0.00949   0.00413  -0.0336   0.8092   1.0000
   2.750   0.4783   0.00949   0.00414  -0.0322   0.7933   1.0000
   3.000   0.4986   0.00939   0.00400  -0.0301   0.7676   1.0000
   3.250   0.5196   0.00932   0.00391  -0.0282   0.7394   1.0000
   3.500   0.5416   0.00931   0.00392  -0.0267   0.7111   1.0000
   3.750   0.5633   0.00933   0.00389  -0.0250   0.6741   1.0000
   4.000   0.5843   0.00945   0.00388  -0.0233   0.6211   1.0000
   4.250   0.6032   0.00980   0.00393  -0.0213   0.5274   1.0000
   4.500   0.6155   0.01093   0.00423  -0.0185   0.3635   1.0000
   4.750   0.6218   0.01321   0.00515  -0.0157   0.1148   1.0000
   5.000   0.6379   0.01465   0.00629  -0.0138   0.0697   1.0000
   5.250   0.6564   0.01577   0.00739  -0.0123   0.0576   1.0000
   5.500   0.6774   0.01658   0.00822  -0.0111   0.0493   1.0000
   5.750   0.6961   0.01811   0.00976  -0.0096   0.0452   1.0000
   6.000   0.7186   0.01928   0.01101  -0.0084   0.0420   1.0000
   6.250   0.7411   0.02030   0.01209  -0.0076   0.0374   1.0000
   6.500   0.7367   0.01118   0.00342  -0.0042   0.0350   1.0000
   6.750   0.7589   0.01330   0.00582  -0.0031   0.0340   1.0000
   7.000   0.7797   0.01526   0.00812  -0.0018   0.0332   1.0000
   7.250   0.7990   0.01693   0.01014  -0.0003   0.0309   1.0000
   7.500   0.8148   0.02000   0.01364   0.0015   0.0307   1.0000
   7.750   0.8258   0.02410   0.01819   0.0037   0.0319   1.0000
  11.250   0.6274   0.10897   0.10569  -0.0027   0.0570   1.0000
  11.500   0.6148   0.11503   0.11171  -0.0062   0.0551   1.0000
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