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GOE 505 AIRFOIL (goe505-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 505 AIRFOIL (goe505-il)
Reynolds number: 200,000
Max Cl/Cd: 53.82 at α=3.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe505-il-200000-n5.txt
Download as CSV file: xf-goe505-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 505 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.0721   0.09328   0.08939  -0.1054   0.9459   0.0350
 -10.250  -0.0630   0.08863   0.08472  -0.1097   0.9443   0.0353
 -10.000  -0.0651   0.08512   0.08122  -0.1106   0.9366   0.0352
  -9.750  -0.0609   0.08013   0.07622  -0.1148   0.9331   0.0354
  -9.500  -0.0558   0.07436   0.07043  -0.1205   0.9303   0.0355
  -9.250  -0.0664   0.06910   0.06519  -0.1235   0.9218   0.0359
  -8.750  -0.2425   0.03619   0.03133  -0.1338   0.8887   0.0352
  -8.500  -0.2414   0.03247   0.02710  -0.1325   0.8850   0.0355
  -8.250  -0.2442   0.03067   0.02498  -0.1283   0.8783   0.0357
  -8.000  -0.2347   0.02884   0.02282  -0.1261   0.8742   0.0360
  -7.750  -0.2168   0.02716   0.02078  -0.1252   0.8716   0.0364
  -7.500  -0.1941   0.02568   0.01899  -0.1249   0.8697   0.0368
  -7.250  -0.1880   0.02497   0.01809  -0.1210   0.8636   0.0371
  -7.000  -0.1689   0.02411   0.01700  -0.1196   0.8600   0.0375
  -6.750  -0.1456   0.02290   0.01562  -0.1191   0.8575   0.0383
  -6.500  -0.1181   0.02189   0.01449  -0.1194   0.8556   0.0389
  -6.250  -0.0900   0.02105   0.01354  -0.1196   0.8537   0.0394
  -6.000  -0.0826   0.02073   0.01316  -0.1157   0.8474   0.0398
  -5.750  -0.0581   0.02009   0.01243  -0.1151   0.8441   0.0403
  -5.500  -0.0269   0.01937   0.01161  -0.1157   0.8413   0.0410
  -5.250   0.0088   0.01863   0.01075  -0.1172   0.8388   0.0418
  -5.000   0.0188   0.01838   0.01045  -0.1136   0.8313   0.0425
  -4.750   0.0492   0.01780   0.00978  -0.1140   0.8267   0.0432
  -4.500   0.0866   0.01717   0.00903  -0.1157   0.8231   0.0445
  -4.000   0.1309   0.01640   0.00817  -0.1131   0.8093   0.0474
  -3.750   0.1550   0.01606   0.00777  -0.1122   0.8022   0.0491
  -3.500   0.1783   0.01576   0.00741  -0.1111   0.7950   0.0511
  -3.000   0.2271   0.01521   0.00683  -0.1094   0.7842   0.0589
  -2.750   0.2505   0.01495   0.00660  -0.1084   0.7783   0.0700
  -2.500   0.2823   0.01462   0.00627  -0.1091   0.7738   0.0887
  -2.250   0.2959   0.01453   0.00624  -0.1061   0.7663   0.1028
  -2.000   0.3203   0.01432   0.00609  -0.1053   0.7601   0.1221
  -1.750   0.3418   0.01419   0.00600  -0.1039   0.7530   0.1403
  -1.500   0.3618   0.01409   0.00593  -0.1022   0.7446   0.1558
  -1.250   0.3818   0.01401   0.00586  -0.1004   0.7360   0.1689
  -1.000   0.4038   0.01390   0.00574  -0.0991   0.7266   0.1832
  -0.750   0.4190   0.01388   0.00569  -0.0963   0.7156   0.1937
  -0.500   0.4372   0.01378   0.00559  -0.0942   0.7043   0.2031
  -0.250   0.4567   0.01368   0.00548  -0.0923   0.6912   0.2163
   0.000   0.4768   0.01359   0.00535  -0.0905   0.6759   0.2303
   0.250   0.4980   0.01350   0.00520  -0.0890   0.6577   0.2424
   0.500   0.5196   0.01343   0.00505  -0.0875   0.6360   0.2533
   0.750   0.5393   0.01344   0.00492  -0.0857   0.6116   0.2637
   1.000   0.5559   0.01352   0.00488  -0.0833   0.5862   0.2753
   1.250   0.5701   0.01367   0.00491  -0.0805   0.5607   0.2882
   1.500   0.5828   0.01387   0.00500  -0.0774   0.5363   0.3036
   1.750   0.5950   0.01408   0.00514  -0.0743   0.5134   0.3209
   2.000   0.6064   0.01432   0.00529  -0.0711   0.4916   0.3394
   2.250   0.6183   0.01456   0.00546  -0.0681   0.4727   0.3603
   2.500   0.6300   0.01479   0.00564  -0.0650   0.4554   0.3847
   2.750   0.6421   0.01496   0.00582  -0.0621   0.4401   0.4221
   3.250   0.8375   0.01556   0.00732  -0.0930   0.3982   1.0000
   3.500   0.8487   0.01585   0.00751  -0.0900   0.3908   1.0000
   3.750   0.8617   0.01612   0.00771  -0.0872   0.3841   1.0000
   4.000   0.8754   0.01640   0.00792  -0.0847   0.3776   1.0000
   4.250   0.8883   0.01674   0.00816  -0.0821   0.3711   1.0000
   4.500   0.9038   0.01701   0.00840  -0.0799   0.3647   1.0000
   4.750   0.9178   0.01735   0.00866  -0.0775   0.3581   1.0000
   5.000   0.9333   0.01768   0.00893  -0.0754   0.3526   1.0000
   5.250   0.9497   0.01797   0.00920  -0.0735   0.3471   1.0000
   5.500   0.9656   0.01832   0.00949  -0.0716   0.3423   1.0000
   5.750   0.9817   0.01869   0.00980  -0.0697   0.3380   1.0000
   6.000   0.9999   0.01898   0.01010  -0.0682   0.3337   1.0000
   6.250   1.0177   0.01930   0.01043  -0.0667   0.3299   1.0000
   6.500   1.0348   0.01967   0.01077  -0.0651   0.3260   1.0000
   6.750   1.0519   0.02007   0.01112  -0.0635   0.3226   1.0000
   7.000   1.0702   0.02041   0.01149  -0.0621   0.3188   1.0000
   7.250   1.0885   0.02076   0.01187  -0.0608   0.3152   1.0000
   7.500   1.1062   0.02114   0.01226  -0.0594   0.3117   1.0000
   7.750   1.1237   0.02155   0.01267  -0.0580   0.3085   1.0000
   8.000   1.1415   0.02200   0.01309  -0.0567   0.3055   1.0000
   8.250   1.1589   0.02239   0.01355  -0.0553   0.3014   1.0000
   8.500   1.1741   0.02284   0.01405  -0.0537   0.2959   1.0000
   8.750   1.1862   0.02344   0.01459  -0.0517   0.2894   1.0000
   9.000   1.2020   0.02389   0.01514  -0.0502   0.2836   1.0000
   9.250   1.2162   0.02444   0.01572  -0.0486   0.2778   1.0000
   9.500   1.2287   0.02507   0.01634  -0.0468   0.2715   1.0000
   9.750   1.2427   0.02565   0.01699  -0.0453   0.2641   1.0000
  10.000   1.2542   0.02638   0.01770  -0.0435   0.2577   1.0000
  10.250   1.2690   0.02698   0.01840  -0.0422   0.2502   1.0000
  10.500   1.2795   0.02780   0.01922  -0.0404   0.2414   1.0000
  10.750   1.2910   0.02862   0.02006  -0.0388   0.2314   1.0000
  11.000   1.3004   0.02959   0.02102  -0.0371   0.2184   1.0000
  11.250   1.3079   0.03072   0.02212  -0.0353   0.2038   1.0000
  11.500   1.3135   0.03202   0.02337  -0.0334   0.1896   1.0000
  11.750   1.3134   0.03379   0.02502  -0.0311   0.1709   1.0000
  12.000   1.3154   0.03551   0.02667  -0.0291   0.1566   1.0000
  12.250   1.3162   0.03738   0.02849  -0.0272   0.1398   1.0000
  12.500   1.3015   0.04060   0.03145  -0.0244   0.0939   1.0000
  12.750   1.2727   0.04529   0.03589  -0.0213   0.0507   1.0000
  13.000   1.2571   0.04911   0.03965  -0.0193   0.0259   1.0000
  13.250   1.2531   0.05201   0.04262  -0.0182   0.0221   1.0000
  13.500   1.2518   0.05475   0.04546  -0.0174   0.0206   1.0000
  13.750   1.2505   0.05757   0.04841  -0.0168   0.0197   1.0000
  14.000   1.2484   0.06060   0.05157  -0.0163   0.0189   1.0000
  14.250   1.2461   0.06374   0.05485  -0.0161   0.0183   1.0000
  14.500   1.2419   0.06724   0.05850  -0.0160   0.0177   1.0000
  14.750   1.2366   0.07098   0.06239  -0.0161   0.0173   1.0000
  15.000   1.2294   0.07506   0.06662  -0.0164   0.0168   1.0000
  15.250   1.2184   0.07979   0.07151  -0.0170   0.0163   1.0000
  15.500   1.2091   0.08442   0.07629  -0.0177   0.0162   1.0000
  15.750   1.1968   0.08958   0.08161  -0.0187   0.0160   1.0000
  16.000   1.1853   0.09471   0.08689  -0.0198   0.0159   1.0000
  16.250   1.1713   0.10033   0.09267  -0.0212   0.0157   1.0000
  16.500   1.1596   0.10567   0.09815  -0.0226   0.0157   1.0000
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