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GOE 54 AIRFOIL (goe54-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 54 AIRFOIL (goe54-il)
Reynolds number: 1,000,000
Max Cl/Cd: 106.66 at α=7.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe54-il-1000000.txt
Download as CSV file: xf-goe54-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 54 AIRFOIL                                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.5822   0.10986   0.10833   0.0452   1.0000   0.0142
  -8.500  -0.5787   0.10600   0.10448   0.0423   1.0000   0.0143
  -8.250  -0.5767   0.10196   0.10046   0.0386   1.0000   0.0143
  -8.000  -0.5720   0.09784   0.09635   0.0380   1.0000   0.0144
  -7.750  -0.5654   0.09457   0.09310   0.0371   1.0000   0.0145
  -7.500  -0.5556   0.09121   0.08975   0.0345   1.0000   0.0146
  -7.250  -0.5435   0.08772   0.08627   0.0312   1.0000   0.0148
  -7.000  -0.5294   0.08406   0.08262   0.0272   1.0000   0.0151
  -6.750  -0.5132   0.08022   0.07877   0.0228   1.0000   0.0154
  -6.500  -0.4950   0.07617   0.07470   0.0181   1.0000   0.0160
  -6.250  -0.4682   0.07098   0.06946   0.0105   1.0000   0.0170
  -6.000  -0.4325   0.06423   0.06255   0.0000   1.0000   0.0171
  -5.750  -0.4156   0.06029   0.05774  -0.0021   0.6921   0.0172
  -5.500  -0.3994   0.05744   0.05459  -0.0029   0.5958   0.0173
  -5.250  -0.3785   0.05470   0.05158  -0.0047   0.5269   0.0175
  -5.000  -0.3548   0.05189   0.04860  -0.0067   0.4973   0.0177
  -4.750  -0.3292   0.04904   0.04561  -0.0088   0.4788   0.0181
  -4.500  -0.3020   0.04613   0.04255  -0.0108   0.4653   0.0187
  -4.250  -0.2600   0.04237   0.03844  -0.0135   0.4553   0.0202
  -4.000  -0.2304   0.03932   0.03517  -0.0146   0.4465   0.0202
  -3.750  -0.2050   0.03538   0.03106  -0.0160   0.4382   0.0204
  -3.500  -0.1805   0.03317   0.02877  -0.0168   0.4306   0.0206
  -3.250  -0.1544   0.03130   0.02680  -0.0175   0.4227   0.0208
  -3.000  -0.1273   0.02962   0.02501  -0.0180   0.4158   0.0212
  -2.750  -0.0990   0.02795   0.02319  -0.0184   0.4086   0.0218
  -2.500  -0.0650   0.02674   0.02169  -0.0178   0.4021   0.0236
  -2.250  -0.0344   0.02531   0.02001  -0.0177   0.3951   0.0237
  -2.000  -0.0052   0.02385   0.01834  -0.0177   0.3872   0.0237
  -1.750   0.0225   0.02095   0.01531  -0.0185   0.3795   0.0241
  -1.500   0.0502   0.01975   0.01402  -0.0189   0.3705   0.0243
  -1.250   0.0785   0.01872   0.01289  -0.0190   0.3605   0.0247
  -1.000   0.1073   0.01781   0.01183  -0.0191   0.3480   0.0253
  -0.750   0.1366   0.01701   0.01086  -0.0190   0.3310   0.0266
  -0.500   0.1674   0.01731   0.01081  -0.0181   0.3100   0.0277
  -0.250   0.1964   0.01667   0.00995  -0.0180   0.2893   0.0277
   0.000   0.2250   0.01467   0.00784  -0.0185   0.2734   0.0283
   0.250   0.2534   0.01406   0.00715  -0.0186   0.2612   0.0288
   0.500   0.2820   0.01359   0.00661  -0.0186   0.2525   0.0296
   0.750   0.3108   0.01320   0.00611  -0.0185   0.2448   0.0308
   1.000   0.3399   0.01367   0.00640  -0.0179   0.2401   0.0323
   1.250   0.3687   0.01235   0.00503  -0.0180   0.2354   0.0332
   1.500   0.3971   0.01192   0.00460  -0.0180   0.2305   0.0341
   1.750   0.4257   0.01165   0.00432  -0.0179   0.2281   0.0359
   2.000   0.4543   0.01217   0.00471  -0.0175   0.2251   0.0378
   2.250   0.4828   0.01110   0.00371  -0.0176   0.2221   0.0393
   2.500   0.5111   0.01090   0.00353  -0.0176   0.2186   0.0414
   3.500   0.6255   0.01018   0.00282  -0.0171   0.2083   0.0366
   3.750   0.6541   0.01010   0.00274  -0.0170   0.2052   0.0365
   4.000   0.6825   0.01013   0.00275  -0.0170   0.2013   0.0370
   4.250   0.7108   0.01015   0.00279  -0.0169   0.1988   0.0380
   4.500   0.7395   0.01005   0.00272  -0.0169   0.1962   0.0385
   4.750   0.7679   0.01004   0.00272  -0.0168   0.1926   0.0402
   5.000   0.7961   0.01010   0.00278  -0.0168   0.1884   0.0421
   5.250   0.8243   0.01020   0.00288  -0.0167   0.1840   0.0442
   5.500   0.8526   0.01020   0.00289  -0.0166   0.1785   0.0499
   5.750   0.8796   0.00888   0.00318  -0.0170   0.1712   0.8687
   6.000   0.9050   0.00875   0.00323  -0.0162   0.1660   1.0000
   6.250   0.9329   0.00895   0.00337  -0.0161   0.1572   1.0000
   6.500   0.9607   0.00913   0.00353  -0.0161   0.1499   1.0000
   6.750   0.9884   0.00937   0.00373  -0.0160   0.1425   1.0000
   7.000   1.0161   0.00958   0.00393  -0.0159   0.1378   1.0000
   7.250   1.0436   0.00985   0.00418  -0.0159   0.1322   1.0000
   7.500   1.0712   0.01007   0.00442  -0.0158   0.1284   1.0000
   7.750   1.0986   0.01030   0.00466  -0.0157   0.1252   1.0000
   8.000   1.1259   0.01057   0.00493  -0.0156   0.1212   1.0000
   8.250   1.1531   0.01087   0.00524  -0.0156   0.1167   1.0000
   8.500   1.1804   0.01107   0.00547  -0.0155   0.1130   1.0000
   8.750   1.2072   0.01141   0.00579  -0.0154   0.1071   1.0000
   9.000   1.2343   0.01166   0.00608  -0.0153   0.1024   1.0000
   9.250   1.2609   0.01201   0.00641  -0.0152   0.0941   1.0000
   9.500   1.2867   0.01256   0.00685  -0.0152   0.0736   1.0000
   9.750   1.3108   0.01360   0.00774  -0.0151   0.0530   1.0000
  10.000   1.3363   0.01418   0.00834  -0.0150   0.0477   1.0000
  10.250   1.3612   0.01489   0.00906  -0.0149   0.0427   1.0000
  10.500   1.3869   0.01532   0.00955  -0.0147   0.0406   1.0000
  10.750   1.4117   0.01594   0.01021  -0.0146   0.0378   1.0000
  11.000   1.4361   0.01663   0.01095  -0.0144   0.0351   1.0000
  11.250   1.4611   0.01709   0.01147  -0.0142   0.0334   1.0000
  11.500   1.4852   0.01774   0.01216  -0.0141   0.0311   1.0000
  11.750   1.5084   0.01853   0.01299  -0.0138   0.0287   1.0000
  12.000   1.5326   0.01905   0.01358  -0.0136   0.0271   1.0000
  12.250   1.5553   0.01984   0.01440  -0.0134   0.0249   1.0000
  12.500   1.5774   0.02069   0.01532  -0.0131   0.0231   1.0000
  12.750   1.5999   0.02141   0.01610  -0.0129   0.0214   1.0000
  13.000   1.6198   0.02253   0.01726  -0.0126   0.0195   1.0000
  13.250   1.6408   0.02339   0.01821  -0.0123   0.0183   1.0000
  13.500   1.6606   0.02437   0.01926  -0.0120   0.0171   1.0000
  13.750   1.6772   0.02578   0.02073  -0.0116   0.0159   1.0000
  14.000   1.6928   0.02722   0.02229  -0.0112   0.0151   1.0000
  14.250   1.7085   0.02852   0.02370  -0.0109   0.0145   1.0000
  14.500   1.7213   0.03012   0.02541  -0.0105   0.0139   1.0000
  14.750   1.7290   0.03224   0.02764  -0.0104   0.0133   1.0000
  15.000   1.7260   0.03542   0.03098  -0.0106   0.0129   1.0000
  15.250   1.6946   0.04763   0.04355  -0.0232   0.0132   1.0000
  15.500   1.6421   0.06019   0.05634  -0.0311   0.0136   1.0000
  15.750   1.5852   0.07241   0.06876  -0.0373   0.0141   1.0000
  16.000   1.5331   0.08404   0.08056  -0.0429   0.0146   1.0000
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