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GOE 621 AIRFOIL (goe621-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 621 AIRFOIL (goe621-il)
Reynolds number: 100,000
Max Cl/Cd: 49.2 at α=5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe621-il-100000-n5.txt
Download as CSV file: xf-goe621-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 621 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.2233   0.09209   0.08671  -0.0757   0.9670   0.0568
  -9.750  -0.2232   0.08583   0.08044  -0.0811   0.9602   0.0571
  -9.500  -0.2333   0.07641   0.07101  -0.0899   0.9543   0.0574
  -9.250  -0.3070   0.05606   0.05049  -0.1097   0.9344   0.0566
  -9.000  -0.3495   0.04702   0.04089  -0.1156   0.9158   0.0563
  -8.750  -0.3564   0.04224   0.03560  -0.1168   0.9052   0.0566
  -8.500  -0.3533   0.03892   0.03180  -0.1165   0.8953   0.0570
  -8.250  -0.3458   0.03633   0.02875  -0.1154   0.8859   0.0576
  -8.000  -0.3286   0.03432   0.02645  -0.1150   0.8788   0.0582
  -7.750  -0.3013   0.03293   0.02496  -0.1158   0.8749   0.0592
  -7.500  -0.2884   0.03205   0.02398  -0.1138   0.8648   0.0602
  -7.250  -0.2632   0.03077   0.02252  -0.1140   0.8598   0.0617
  -7.000  -0.2439   0.02961   0.02114  -0.1130   0.8525   0.0632
  -6.750  -0.2227   0.02842   0.01969  -0.1121   0.8456   0.0645
  -6.500  -0.1950   0.02716   0.01819  -0.1123   0.8415   0.0658
  -6.250  -0.1754   0.02647   0.01750  -0.1111   0.8341   0.0671
  -6.000  -0.1513   0.02574   0.01672  -0.1105   0.8282   0.0686
  -5.750  -0.1224   0.02494   0.01581  -0.1107   0.8242   0.0711
  -5.500  -0.1013   0.02435   0.01506  -0.1095   0.8171   0.0739
  -5.250  -0.0773   0.02380   0.01454  -0.1089   0.8112   0.0765
  -5.000  -0.0487   0.02318   0.01386  -0.1090   0.8074   0.0802
  -4.750  -0.0245   0.02268   0.01324  -0.1083   0.8019   0.0839
  -4.500  -0.0028   0.02229   0.01289  -0.1072   0.7954   0.0881
  -4.250   0.0255   0.02178   0.01230  -0.1071   0.7911   0.0954
  -4.000   0.0562   0.02124   0.01172  -0.1075   0.7880   0.1046
  -3.750   0.0731   0.02105   0.01157  -0.1057   0.7804   0.1131
  -3.500   0.0992   0.02065   0.01117  -0.1053   0.7757   0.1266
  -3.250   0.1291   0.02020   0.01073  -0.1056   0.7721   0.1436
  -3.000   0.1520   0.02001   0.01058  -0.1047   0.7666   0.1609
  -2.750   0.1750   0.01986   0.01048  -0.1039   0.7609   0.1806
  -2.500   0.2033   0.01960   0.01027  -0.1038   0.7568   0.2047
  -2.250   0.2348   0.01931   0.01004  -0.1043   0.7536   0.2357
  -2.000   0.2535   0.01938   0.01023  -0.1027   0.7470   0.2648
  -1.750   0.2791   0.01929   0.01020  -0.1022   0.7414   0.2965
  -1.500   0.3114   0.01904   0.00994  -0.1026   0.7369   0.3263
  -1.250   0.3332   0.01906   0.00996  -0.1013   0.7291   0.3488
  -1.000   0.3609   0.01889   0.00979  -0.1009   0.7221   0.3708
  -0.750   0.3923   0.01865   0.00952  -0.1011   0.7158   0.3940
  -0.500   0.4132   0.01865   0.00954  -0.0996   0.7064   0.4144
  -0.250   0.4465   0.01838   0.00922  -0.1001   0.7002   0.4389
   0.000   0.4670   0.01845   0.00934  -0.0986   0.6918   0.4608
   0.250   0.4950   0.01833   0.00928  -0.0984   0.6856   0.4904
   0.500   0.5262   0.01810   0.00912  -0.0986   0.6805   0.5292
   0.750   0.5444   0.01811   0.00933  -0.0968   0.6724   0.5696
   1.000   0.5716   0.01778   0.00925  -0.0962   0.6662   0.6336
   1.250   0.6648   0.01714   0.00925  -0.1087   0.6584   1.0000
   1.500   0.6864   0.01728   0.00928  -0.1073   0.6504   1.0000
   1.750   0.7133   0.01732   0.00916  -0.1069   0.6438   1.0000
   2.000   0.7300   0.01756   0.00935  -0.1048   0.6344   1.0000
   2.250   0.7580   0.01755   0.00920  -0.1044   0.6272   1.0000
   2.500   0.7732   0.01781   0.00944  -0.1021   0.6168   1.0000
   2.750   0.7995   0.01783   0.00934  -0.1014   0.6087   1.0000
   3.000   0.8152   0.01807   0.00957  -0.0991   0.5975   1.0000
   3.250   0.8366   0.01818   0.00961  -0.0977   0.5872   1.0000
   3.500   0.8572   0.01829   0.00966  -0.0962   0.5759   1.0000
   3.750   0.8738   0.01850   0.00984  -0.0940   0.5630   1.0000
   4.000   0.8924   0.01867   0.00995  -0.0921   0.5499   1.0000
   4.250   0.9109   0.01883   0.01004  -0.0903   0.5360   1.0000
   4.500   0.9283   0.01902   0.01015  -0.0882   0.5207   1.0000
   4.750   0.9445   0.01924   0.01029  -0.0859   0.5042   1.0000
   5.000   0.9598   0.01951   0.01046  -0.0836   0.4869   1.0000
   5.250   0.9740   0.01980   0.01065  -0.0811   0.4696   1.0000
   5.500   0.9877   0.02015   0.01087  -0.0785   0.4526   1.0000
   5.750   1.0015   0.02055   0.01114  -0.0760   0.4364   1.0000
   6.000   1.0156   0.02100   0.01147  -0.0737   0.4217   1.0000
   6.250   1.0296   0.02151   0.01187  -0.0715   0.4077   1.0000
   6.500   1.0442   0.02203   0.01230  -0.0694   0.3954   1.0000
   6.750   1.0598   0.02257   0.01273  -0.0675   0.3844   1.0000
   7.000   1.0748   0.02315   0.01324  -0.0657   0.3736   1.0000
   7.250   1.0901   0.02374   0.01376  -0.0639   0.3638   1.0000
   7.500   1.1056   0.02435   0.01429  -0.0622   0.3545   1.0000
   7.750   1.1210   0.02497   0.01489  -0.0605   0.3458   1.0000
   8.000   1.1364   0.02561   0.01547  -0.0589   0.3375   1.0000
   8.250   1.1525   0.02625   0.01609  -0.0574   0.3301   1.0000
   8.500   1.1676   0.02692   0.01677  -0.0559   0.3226   1.0000
   8.750   1.1851   0.02757   0.01733  -0.0546   0.3161   1.0000
   9.000   1.1987   0.02830   0.01815  -0.0530   0.3092   1.0000
   9.250   1.2138   0.02902   0.01886  -0.0516   0.3027   1.0000
   9.500   1.2293   0.02976   0.01958  -0.0502   0.2965   1.0000
   9.750   1.2421   0.03058   0.02049  -0.0487   0.2900   1.0000
  10.000   1.2568   0.03135   0.02125  -0.0473   0.2843   1.0000
  10.250   1.2710   0.03218   0.02211  -0.0460   0.2787   1.0000
  10.500   1.2823   0.03312   0.02314  -0.0444   0.2726   1.0000
  10.750   1.2950   0.03400   0.02404  -0.0430   0.2670   1.0000
  11.000   1.3065   0.03499   0.02508  -0.0416   0.2613   1.0000
  11.250   1.3157   0.03609   0.02628  -0.0401   0.2551   1.0000
  11.500   1.3265   0.03711   0.02730  -0.0387   0.2498   1.0000
  11.750   1.3363   0.03827   0.02855  -0.0373   0.2444   1.0000
  12.000   1.3442   0.03955   0.02993  -0.0359   0.2386   1.0000
  12.250   1.3541   0.04071   0.03111  -0.0347   0.2339   1.0000
  12.500   1.3637   0.04197   0.03244  -0.0335   0.2292   1.0000
  12.750   1.3701   0.04348   0.03408  -0.0322   0.2238   1.0000
  13.000   1.3782   0.04486   0.03552  -0.0311   0.2194   1.0000
  13.250   1.3887   0.04609   0.03672  -0.0301   0.2154   1.0000
  13.500   1.3925   0.04794   0.03876  -0.0290   0.2106   1.0000
  13.750   1.3979   0.04966   0.04057  -0.0280   0.2062   1.0000
  14.000   1.4056   0.05115   0.04208  -0.0271   0.2024   1.0000
  14.250   1.4120   0.05289   0.04390  -0.0263   0.1987   1.0000
  14.500   1.4144   0.05506   0.04624  -0.0255   0.1948   1.0000
  14.750   1.4191   0.05704   0.04832  -0.0248   0.1914   1.0000
  15.000   1.4261   0.05878   0.05011  -0.0241   0.1884   1.0000
  15.250   1.4393   0.05995   0.05125  -0.0235   0.1858   1.0000
  15.500   1.4352   0.06299   0.05453  -0.0230   0.1829   1.0000
  15.750   1.4327   0.06591   0.05763  -0.0227   0.1798   1.0000
  16.000   1.4330   0.06854   0.06038  -0.0224   0.1768   1.0000
  16.250   1.4381   0.07058   0.06247  -0.0221   0.1739   1.0000
  16.500   1.4492   0.07196   0.06382  -0.0217   0.1712   1.0000
  16.750   1.4330   0.07678   0.06892  -0.0221   0.1687   1.0000
  17.000   1.4184   0.08158   0.07395  -0.0228   0.1659   1.0000
  17.250   1.4088   0.08584   0.07837  -0.0235   0.1632   1.0000
  17.500   1.4113   0.08837   0.08095  -0.0238   0.1601   1.0000
  17.750   1.4220   0.08976   0.08230  -0.0237   0.1570   1.0000
  18.000   1.3835   0.09866   0.09154  -0.0265   0.1549   1.0000
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