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GIII BL167 AIRFOIL (giiig-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GIII BL167 AIRFOIL (giiig-il)
Reynolds number: 500,000
Max Cl/Cd: 78.82 at α=3.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-giiig-il-500000.txt
Download as CSV file: xf-giiig-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.5875   0.11433   0.11207   0.0085   1.0000   0.0137
 -10.000  -0.5852   0.11029   0.10804   0.0067   1.0000   0.0141
  -9.750  -0.5833   0.10615   0.10392   0.0047   1.0000   0.0144
  -5.500  -0.5005   0.02559   0.02107  -0.0171   0.9971   0.0180
  -5.250  -0.4726   0.01949   0.01435  -0.0178   0.9935   0.0162
  -5.000  -0.4399   0.01701   0.01147  -0.0187   0.9893   0.0168
  -4.750  -0.4046   0.01571   0.00991  -0.0203   0.9858   0.0175
  -4.500  -0.3716   0.01323   0.00719  -0.0216   0.9831   0.0198
  -4.250  -0.3390   0.01239   0.00628  -0.0227   0.9770   0.0216
  -4.000  -0.3054   0.01160   0.00542  -0.0240   0.9713   0.0236
  -3.750  -0.2737   0.01102   0.00476  -0.0248   0.9635   0.0256
  -3.500  -0.2440   0.01017   0.00385  -0.0253   0.9556   0.0307
  -3.250  -0.2162   0.00984   0.00348  -0.0253   0.9449   0.0363
  -3.000  -0.1900   0.00938   0.00300  -0.0249   0.9342   0.0476
  -2.750  -0.1640   0.00909   0.00271  -0.0245   0.9240   0.0604
  -2.500  -0.1383   0.00884   0.00243  -0.0240   0.9139   0.0749
  -2.250  -0.1131   0.00854   0.00222  -0.0235   0.9034   0.1002
  -2.000  -0.0895   0.00795   0.00201  -0.0229   0.8935   0.2056
  -1.750  -0.0779   0.00607   0.00174  -0.0204   0.8834   0.6685
  -1.500  -0.0550   0.00586   0.00175  -0.0191   0.8742   0.7550
  -1.250  -0.0304   0.00578   0.00173  -0.0181   0.8657   0.7969
  -1.000  -0.0056   0.00575   0.00172  -0.0171   0.8575   0.8276
  -0.750   0.0196   0.00572   0.00171  -0.0163   0.8472   0.8494
  -0.500   0.0442   0.00571   0.00171  -0.0153   0.8365   0.8723
  -0.250   0.0691   0.00572   0.00170  -0.0143   0.8265   0.8905
   0.000   0.0937   0.00575   0.00171  -0.0132   0.8165   0.9097
   0.250   0.1170   0.00581   0.00180  -0.0116   0.8063   0.9338
   0.500   0.1442   0.00587   0.00183  -0.0112   0.7976   0.9469
   0.750   0.1727   0.00590   0.00183  -0.0113   0.7889   0.9555
   1.000   0.2052   0.00594   0.00184  -0.0123   0.7799   0.9611
   1.250   0.2355   0.00599   0.00186  -0.0128   0.7714   0.9690
   1.500   0.2711   0.00602   0.00189  -0.0145   0.7620   0.9728
   1.750   0.3061   0.00606   0.00192  -0.0162   0.7521   0.9777
   2.000   0.3404   0.00610   0.00195  -0.0177   0.7422   0.9830
   2.250   0.3777   0.00613   0.00196  -0.0198   0.7294   0.9861
   2.500   0.4131   0.00616   0.00194  -0.0215   0.7006   0.9906
   2.750   0.4482   0.00622   0.00195  -0.0232   0.6738   0.9950
   3.000   0.4844   0.00632   0.00197  -0.0252   0.6385   0.9987
   3.250   0.5123   0.00650   0.00200  -0.0254   0.5932   1.0000
   3.500   0.5344   0.00681   0.00208  -0.0245   0.5184   1.0000
   3.750   0.5533   0.00759   0.00230  -0.0233   0.3920   1.0000
   4.000   0.5733   0.00825   0.00258  -0.0222   0.3025   1.0000
   4.250   0.5920   0.00907   0.00292  -0.0210   0.1929   1.0000
   4.500   0.6090   0.01013   0.00343  -0.0195   0.0803   1.0000
   4.750   0.6292   0.01082   0.00395  -0.0183   0.0451   1.0000
   5.000   0.6500   0.01146   0.00459  -0.0170   0.0343   1.0000
   5.250   0.6727   0.01186   0.00505  -0.0161   0.0308   1.0000
   5.500   0.6945   0.01241   0.00561  -0.0151   0.0266   1.0000
   5.750   0.7135   0.01342   0.00672  -0.0136   0.0237   1.0000
   6.000   0.7360   0.01400   0.00739  -0.0126   0.0222   1.0000
   6.250   0.7579   0.01472   0.00818  -0.0116   0.0204   1.0000
   6.500   0.7807   0.01531   0.00879  -0.0109   0.0183   1.0000
   6.750   0.7973   0.01741   0.01101  -0.0092   0.0163   1.0000
   7.000   0.8196   0.01855   0.01228  -0.0083   0.0155   1.0000
   7.250   0.8424   0.01967   0.01354  -0.0074   0.0147   1.0000
   7.500   0.8643   0.02128   0.01534  -0.0064   0.0140   1.0000
   7.750   0.8855   0.02299   0.01727  -0.0054   0.0132   1.0000
   8.000   0.9071   0.02384   0.01822  -0.0048   0.0122   1.0000
   8.250   0.9275   0.02479   0.01926  -0.0041   0.0113   1.0000
   8.500   0.9432   0.02756   0.02230  -0.0028   0.0109   1.0000
   8.750   0.9533   0.03149   0.02665  -0.0008   0.0107   1.0000
   9.000   0.9591   0.03570   0.03129   0.0014   0.0106   1.0000
   9.250   0.9631   0.03961   0.03557   0.0035   0.0106   1.0000
   9.500   0.9673   0.04302   0.03932   0.0056   0.0109   1.0000
  15.250   0.5842   0.16152   0.15936  -0.0235   0.0159   1.0000
  15.500   0.5852   0.16456   0.16241  -0.0249   0.0158   1.0000
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