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GOE 55 AIRFOIL (goe55-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: GOE 55 AIRFOIL (goe55-il)
Reynolds number: 500,000
Max Cl/Cd: 64.63 at α=6.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe55-il-500000-n5.txt
Download as CSV file: xf-goe55-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 55 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.6743   0.11070   0.10836   0.0418   1.0000   0.0156
  -9.250  -0.6736   0.10608   0.10374   0.0395   1.0000   0.0161
  -9.000  -0.6881   0.09731   0.09499   0.0342   1.0000   0.0174
  -8.750  -0.6823   0.09444   0.09213   0.0326   1.0000   0.0175
  -8.500  -0.6766   0.09159   0.08930   0.0310   1.0000   0.0177
  -8.250  -0.6704   0.08818   0.08590   0.0282   1.0000   0.0180
  -8.000  -0.6610   0.08405   0.08177   0.0239   1.0000   0.0183
  -7.750  -0.6500   0.07909   0.07680   0.0183   1.0000   0.0187
  -7.250  -0.6224   0.05499   0.05238  -0.0091   1.0000   0.0214
  -7.000  -0.5997   0.05113   0.04842  -0.0126   1.0000   0.0217
  -6.750  -0.5759   0.04760   0.04478  -0.0155   1.0000   0.0221
  -6.500  -0.5496   0.02193   0.01716  -0.0293   1.0000   0.0256
  -6.250  -0.5224   0.01973   0.01467  -0.0300   1.0000   0.0263
  -6.000  -0.4947   0.01870   0.01350  -0.0302   1.0000   0.0266
  -5.750  -0.4667   0.01773   0.01240  -0.0304   1.0000   0.0270
  -5.500  -0.4385   0.01682   0.01136  -0.0306   1.0000   0.0273
  -5.250  -0.4102   0.01595   0.01036  -0.0307   1.0000   0.0277
  -5.000  -0.3818   0.01513   0.00940  -0.0308   1.0000   0.0282
  -4.750  -0.3532   0.01438   0.00853  -0.0309   1.0000   0.0286
  -4.500  -0.3247   0.01377   0.00783  -0.0309   1.0000   0.0293
  -4.250  -0.2961   0.01318   0.00716  -0.0309   1.0000   0.0299
  -4.000  -0.2674   0.01259   0.00648  -0.0309   1.0000   0.0303
  -3.750  -0.2373   0.01223   0.00596  -0.0310   0.8981   0.0307
  -3.500  -0.2179   0.01273   0.00556  -0.0285   0.6552   0.0309
  -3.250  -0.1899   0.01279   0.00510  -0.0285   0.5178   0.0312
  -3.000  -0.1613   0.01253   0.00455  -0.0287   0.4469   0.0317
  -2.750  -0.1326   0.01221   0.00408  -0.0288   0.4116   0.0323
  -2.500  -0.1039   0.01199   0.00376  -0.0288   0.3897   0.0330
  -2.250  -0.0752   0.01181   0.00351  -0.0288   0.3742   0.0337
  -2.000  -0.0465   0.01167   0.00331  -0.0288   0.3631   0.0346
  -1.500   0.0111   0.01138   0.00293  -0.0287   0.3478   0.0367
  -1.250   0.0400   0.01125   0.00276  -0.0287   0.3418   0.0375
  -1.000   0.0688   0.01116   0.00262  -0.0286   0.3368   0.0383
  -0.750   0.0977   0.01099   0.00246  -0.0286   0.3325   0.0402
  -0.500   0.1265   0.01090   0.00236  -0.0286   0.3268   0.0423
  -0.250   0.1553   0.01086   0.00228  -0.0285   0.3208   0.0451
   0.000   0.1841   0.01077   0.00222  -0.0285   0.3154   0.0498
   0.250   0.2129   0.01071   0.00218  -0.0284   0.3099   0.0593
   0.500   0.2417   0.01066   0.00220  -0.0284   0.3040   0.0811
   0.750   0.2704   0.01063   0.00220  -0.0284   0.2960   0.0967
   1.000   0.2990   0.01064   0.00218  -0.0283   0.2869   0.1069
   1.250   0.3277   0.01061   0.00217  -0.0283   0.2772   0.1178
   1.500   0.3566   0.01047   0.00220  -0.0284   0.2703   0.1769
   2.000   0.4066   0.00839   0.00224  -0.0271   0.2560   1.0000
   2.500   0.4639   0.00861   0.00232  -0.0269   0.2308   1.0000
   2.750   0.4923   0.00886   0.00237  -0.0269   0.1908   1.0000
   3.000   0.5204   0.00930   0.00256  -0.0270   0.1469   1.0000
   3.250   0.5487   0.00962   0.00275  -0.0270   0.1251   1.0000
   3.500   0.5771   0.00989   0.00293  -0.0270   0.1096   1.0000
   3.750   0.6054   0.01016   0.00313  -0.0269   0.0953   1.0000
   4.000   0.6332   0.01080   0.00347  -0.0270   0.0460   1.0000
   4.250   0.6614   0.01112   0.00374  -0.0270   0.0401   1.0000
   4.500   0.6896   0.01141   0.00403  -0.0269   0.0371   1.0000
   4.750   0.7178   0.01167   0.00429  -0.0268   0.0359   1.0000
   5.000   0.7459   0.01194   0.00458  -0.0267   0.0351   1.0000
   5.250   0.7739   0.01223   0.00490  -0.0266   0.0344   1.0000
   5.500   0.8018   0.01254   0.00524  -0.0266   0.0336   1.0000
   5.750   0.8296   0.01288   0.00561  -0.0265   0.0328   1.0000
   6.000   0.8573   0.01327   0.00603  -0.0264   0.0319   1.0000
   6.250   0.8848   0.01369   0.00648  -0.0263   0.0312   1.0000
   6.500   0.9121   0.01416   0.00699  -0.0262   0.0306   1.0000
   6.750   0.9392   0.01471   0.00760  -0.0261   0.0300   1.0000
   7.000   0.9659   0.01535   0.00830  -0.0260   0.0295   1.0000
   7.250   0.9925   0.01598   0.00898  -0.0259   0.0291   1.0000
   7.500   1.0191   0.01649   0.00955  -0.0257   0.0289   1.0000
   7.750   1.0455   0.01703   0.01016  -0.0255   0.0286   1.0000
   8.000   1.0717   0.01757   0.01077  -0.0253   0.0283   1.0000
   8.250   1.0978   0.01814   0.01141  -0.0251   0.0278   1.0000
   8.500   1.1234   0.01879   0.01213  -0.0249   0.0274   1.0000
   8.750   1.1487   0.01948   0.01291  -0.0247   0.0270   1.0000
   9.000   1.1736   0.02020   0.01371  -0.0244   0.0266   1.0000
   9.250   1.1984   0.02091   0.01450  -0.0241   0.0260   1.0000
   9.500   1.2228   0.02163   0.01531  -0.0238   0.0255   1.0000
   9.750   1.2467   0.02244   0.01619  -0.0235   0.0250   1.0000
  10.000   1.2701   0.02328   0.01710  -0.0232   0.0246   1.0000
  10.250   1.2926   0.02426   0.01814  -0.0228   0.0240   1.0000
  10.500   1.3120   0.02583   0.01980  -0.0223   0.0234   1.0000
  10.750   1.3336   0.02686   0.02096  -0.0218   0.0230   1.0000
  11.000   1.3560   0.02762   0.02186  -0.0214   0.0227   1.0000
  11.250   1.3776   0.02849   0.02287  -0.0209   0.0222   1.0000
  11.500   1.3980   0.02948   0.02400  -0.0204   0.0217   1.0000
  11.750   1.4176   0.03054   0.02520  -0.0199   0.0211   1.0000
  12.000   1.4366   0.03156   0.02635  -0.0193   0.0206   1.0000
  12.250   1.4550   0.03258   0.02748  -0.0188   0.0201   1.0000
  12.500   1.4726   0.03363   0.02862  -0.0182   0.0197   1.0000
  12.750   1.4886   0.03480   0.02988  -0.0176   0.0193   1.0000
  13.000   1.5025   0.03611   0.03130  -0.0170   0.0190   1.0000
  13.250   1.5114   0.03790   0.03318  -0.0162   0.0186   1.0000
  13.500   1.5158   0.03998   0.03542  -0.0153   0.0184   1.0000
  13.750   1.5117   0.04255   0.03819  -0.0143   0.0181   1.0000
  14.000   1.5031   0.04708   0.04294  -0.0171   0.0179   1.0000
  14.250   1.4936   0.05435   0.05045  -0.0243   0.0177   1.0000
  14.500   1.4797   0.06218   0.05847  -0.0306   0.0176   1.0000
  14.750   1.4597   0.07008   0.06653  -0.0358   0.0175   1.0000
  15.000   1.4364   0.07806   0.07465  -0.0404   0.0174   1.0000
  15.250   1.4116   0.08613   0.08284  -0.0448   0.0174   1.0000
  15.500   1.3852   0.09450   0.09134  -0.0493   0.0174   1.0000
  15.750   1.3585   0.10309   0.10006  -0.0538   0.0173   1.0000
  16.000   1.3316   0.11230   0.10940  -0.0588   0.0173   1.0000
  16.250   1.3032   0.12249   0.11973  -0.0644   0.0172   1.0000
  16.500   1.2681   0.13489   0.13229  -0.0714   0.0172   1.0000
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