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

FX 75-VG-166/22 (fx75vg166-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: FX 75-VG-166/22 (fx75vg166-il)
Reynolds number: 500,000
Max Cl/Cd: 82.42 at α=7.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx75vg166-il-500000.txt
Download as CSV file: xf-fx75vg166-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 75-VG-166/22                                 
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -12.750  -0.1716   0.08906   0.08580  -0.1005   0.7617   0.0296
 -12.500  -0.4913   0.05007   0.04575  -0.1260   0.7650   0.0173
 -12.250  -0.5042   0.04711   0.04268  -0.1246   0.7643   0.0171
 -12.000  -0.5291   0.04346   0.03878  -0.1216   0.7635   0.0171
 -11.750  -0.5343   0.04130   0.03652  -0.1195   0.7626   0.0166
 -11.500  -0.5515   0.03840   0.03334  -0.1157   0.7616   0.0169
 -11.250  -0.5654   0.03542   0.03006  -0.1116   0.7606   0.0169
 -11.000  -0.5659   0.03323   0.02765  -0.1087   0.7596   0.0165
 -10.750  -0.5677   0.03151   0.02565  -0.1052   0.7588   0.0171
 -10.500  -0.5608   0.02963   0.02353  -0.1028   0.7580   0.0172
 -10.250  -0.5486   0.02814   0.02183  -0.1010   0.7573   0.0172
 -10.000  -0.5404   0.02732   0.02079  -0.0983   0.7566   0.0176
  -9.750  -0.5147   0.02547   0.01875  -0.0986   0.7559   0.0181
  -9.500  -0.4928   0.02457   0.01782  -0.0981   0.7552   0.0186
  -9.250  -0.4738   0.02390   0.01713  -0.0971   0.7544   0.0191
  -9.000  -0.4569   0.02340   0.01660  -0.0958   0.7535   0.0201
  -8.750  -0.4351   0.02270   0.01582  -0.0951   0.7526   0.0209
  -8.500  -0.4130   0.02208   0.01511  -0.0943   0.7516   0.0215
  -8.250  -0.3875   0.02117   0.01415  -0.0942   0.7506   0.0222
  -8.000  -0.3685   0.02059   0.01360  -0.0931   0.7494   0.0233
  -7.750  -0.3496   0.02011   0.01311  -0.0919   0.7481   0.0244
  -7.500  -0.3308   0.01970   0.01266  -0.0906   0.7469   0.0256
  -7.250  -0.3119   0.01935   0.01225  -0.0893   0.7458   0.0264
  -7.000  -0.2972   0.01869   0.01163  -0.0875   0.7448   0.0284
  -6.750  -0.2805   0.01830   0.01122  -0.0858   0.7439   0.0295
  -6.500  -0.2623   0.01808   0.01096  -0.0844   0.7430   0.0316
  -6.250  -0.2505   0.01760   0.01046  -0.0819   0.7421   0.0332
  -6.000  -0.2362   0.01737   0.01024  -0.0798   0.7412   0.0356
  -5.750  -0.2222   0.01731   0.01015  -0.0775   0.7403   0.0379
  -5.500  -0.2133   0.01702   0.00989  -0.0744   0.7388   0.0410
  -5.250  -0.2008   0.01682   0.00973  -0.0719   0.7368   0.0449
  -5.000  -0.1861   0.01656   0.00951  -0.0698   0.7348   0.0519
  -4.750  -0.1707   0.01629   0.00931  -0.0678   0.7332   0.0649
  -4.500  -0.1572   0.01589   0.00910  -0.0655   0.7316   0.1020
  -4.250  -0.1471   0.01528   0.00885  -0.0628   0.7302   0.1826
  -4.000  -0.1397   0.01449   0.00856  -0.0597   0.7288   0.2996
  -3.750  -0.1338   0.01358   0.00820  -0.0563   0.7277   0.4339
  -3.500  -0.1321   0.01250   0.00785  -0.0519   0.7265   0.6072
  -3.250  -0.1105   0.01302   0.00885  -0.0497   0.7257   0.7171
  -3.000  -0.0815   0.01373   0.00953  -0.0495   0.7249   0.7400
  -2.750  -0.0574   0.01431   0.01010  -0.0488   0.7222   0.7553
  -2.500  -0.0330   0.01480   0.01055  -0.0483   0.7198   0.7674
  -2.250  -0.0040   0.01555   0.01130  -0.0479   0.7180   0.7726
  -2.000   0.0229   0.01604   0.01175  -0.0474   0.7164   0.7819
  -1.750   0.0535   0.01691   0.01264  -0.0468   0.7153   0.7862
  -1.500   0.0802   0.01740   0.01309  -0.0463   0.7142   0.7961
  -1.250   0.1105   0.01798   0.01367  -0.0456   0.7134   0.7988
  -1.000   0.1397   0.01826   0.01392  -0.0454   0.7126   0.8015
  -0.750   0.1671   0.01834   0.01397  -0.0453   0.7118   0.8051
  -0.500   0.1915   0.01825   0.01381  -0.0452   0.7109   0.8116
  -0.250   0.2202   0.01825   0.01379  -0.0451   0.7101   0.8129
   0.000   0.2360   0.01857   0.01418  -0.0430   0.7052   0.8150
   0.250   0.2593   0.01869   0.01431  -0.0422   0.7028   0.8174
   0.500   0.2840   0.01869   0.01430  -0.0419   0.7011   0.8207
   0.750   0.3095   0.01855   0.01411  -0.0424   0.6997   0.8260
   1.000   0.3363   0.01837   0.01392  -0.0421   0.6987   0.8271
   1.250   0.3641   0.01822   0.01376  -0.0420   0.6977   0.8283
   1.500   0.3927   0.01803   0.01356  -0.0422   0.6968   0.8296
   1.750   0.4224   0.01780   0.01332  -0.0426   0.6960   0.8311
   2.000   0.4520   0.01761   0.01310  -0.0430   0.6952   0.8327
   2.250   0.4625   0.01797   0.01356  -0.0406   0.6892   0.8355
   2.500   0.4895   0.01781   0.01340  -0.0409   0.6871   0.8376
   2.750   0.5201   0.01762   0.01319  -0.0421   0.6855   0.8405
   3.000   0.5488   0.01715   0.01273  -0.0421   0.6841   0.8417
   3.250   0.5794   0.01675   0.01234  -0.0425   0.6830   0.8427
   3.500   0.6101   0.01641   0.01200  -0.0431   0.6821   0.8435
   3.750   0.6413   0.01610   0.01169  -0.0439   0.6812   0.8442
   4.000   0.6606   0.01611   0.01177  -0.0426   0.6770   0.8454
   4.250   0.6874   0.01575   0.01145  -0.0426   0.6729   0.8464
   4.500   0.7267   0.01474   0.01041  -0.0445   0.6697   0.8469
   4.750   0.7634   0.01401   0.00966  -0.0461   0.6672   0.8476
   5.000   0.7873   0.01384   0.00955  -0.0456   0.6629   0.8487
   5.250   0.8117   0.01365   0.00943  -0.0452   0.6580   0.8502
   5.500   0.8425   0.01326   0.00906  -0.0460   0.6543   0.8513
   5.750   0.8705   0.01296   0.00878  -0.0462   0.6493   0.8521
   6.000   0.8941   0.01279   0.00869  -0.0457   0.6418   0.8530
   6.250   0.9212   0.01252   0.00844  -0.0458   0.6335   0.8538
   6.500   0.9469   0.01226   0.00818  -0.0456   0.6207   0.8546
   6.750   0.9674   0.01209   0.00797  -0.0443   0.5994   0.8555
   7.000   0.9819   0.01196   0.00778  -0.0417   0.5747   0.8567
   7.250   0.9915   0.01203   0.00775  -0.0383   0.5447   0.8578
   7.500   0.9923   0.01230   0.00790  -0.0332   0.5127   0.8592
   8.000   0.9612   0.01344   0.00874  -0.0177   0.4482   0.8623
   8.250   0.9481   0.01441   0.00961  -0.0115   0.4225   0.8637
   8.500   0.9322   0.01598   0.01106  -0.0061   0.3941   0.8652
   8.750   0.9168   0.01751   0.01241  -0.0006   0.3600   0.8669
   9.000   0.9096   0.01881   0.01356   0.0035   0.3314   0.8678
   9.250   0.9040   0.02013   0.01471   0.0073   0.2993   0.8686
   9.500   0.8990   0.02150   0.01589   0.0108   0.2628   0.8691
   9.750   0.8985   0.02277   0.01699   0.0135   0.2313   0.8696
  10.000   0.8997   0.02404   0.01807   0.0160   0.1993   0.8699
  10.250   0.9049   0.02517   0.01908   0.0178   0.1756   0.8702
  10.500   0.9125   0.02623   0.02003   0.0193   0.1540   0.8704
  10.750   0.9221   0.02725   0.02097   0.0204   0.1350   0.8707
  11.000   0.9314   0.02841   0.02202   0.0214   0.1143   0.8710
  11.250   0.9420   0.02954   0.02306   0.0222   0.0951   0.8713
  11.500   0.9505   0.03086   0.02424   0.0231   0.0727   0.8715
  11.750   0.9579   0.03232   0.02558   0.0240   0.0546   0.8717
  12.000   0.9670   0.03372   0.02692   0.0247   0.0437   0.8719
  12.250   0.9767   0.03514   0.02832   0.0253   0.0373   0.8721
  12.500   0.9893   0.03641   0.02962   0.0255   0.0343   0.8723
  12.750   0.9989   0.03794   0.03116   0.0259   0.0310   0.8724
  13.000   1.0115   0.03926   0.03254   0.0261   0.0290   0.8726
  13.250   1.0218   0.04083   0.03412   0.0262   0.0269   0.8730
  13.500   1.0307   0.04252   0.03588   0.0264   0.0253   0.8732
  13.750   1.0416   0.04412   0.03755   0.0265   0.0242   0.8735
  14.000   1.0525   0.04572   0.03921   0.0264   0.0231   0.8736
  14.250   1.0603   0.04764   0.04118   0.0265   0.0225   0.8736
  14.500   1.0607   0.05021   0.04378   0.0269   0.0213   0.8736
  14.750   1.0711   0.05198   0.04564   0.0267   0.0206   0.8736
  15.000   1.0807   0.05383   0.04758   0.0265   0.0198   0.8737
  15.250   1.0884   0.05585   0.04967   0.0264   0.0197   0.8737
  15.500   1.0958   0.05800   0.05188   0.0261   0.0188   0.8737
  15.750   1.1041   0.06006   0.05399   0.0257   0.0183   0.8737
  16.000   1.1072   0.06258   0.05655   0.0256   0.0176   0.8737
  16.250   1.1126   0.06481   0.05884   0.0255   0.0174   0.8739
  16.500   1.1186   0.06723   0.06138   0.0251   0.0167   0.8741
  16.750   1.1258   0.06938   0.06361   0.0249   0.0167   0.8744
  17.000   1.1324   0.07181   0.06616   0.0243   0.0163   0.8748
  17.250   1.1375   0.07439   0.06884   0.0237   0.0158   0.8750
  17.500   1.1434   0.07683   0.07138   0.0231   0.0157   0.8751
  17.750   1.1473   0.07955   0.07419   0.0225   0.0153   0.8750
  18.000   1.1513   0.08238   0.07712   0.0216   0.0151   0.8750
  18.250   1.1547   0.08524   0.08006   0.0208   0.0148   0.8749
  18.500   1.1576   0.08817   0.08308   0.0200   0.0147   0.8749
  18.750   1.1603   0.09118   0.08614   0.0189   0.0144   0.8749
  19.000   1.1619   0.09421   0.08928   0.0181   0.0143   0.8748
  19.250   1.1631   0.09708   0.09221   0.0177   0.0139   0.8748
<< Back to FX 75-VG-166/22 (fx75vg166-il)

Polar data table (+)

Polar graphs


<< Back to FX 75-VG-166/22 (fx75vg166-il)