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GOE 427 AIRFOIL (goe427-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 427 AIRFOIL (goe427-il)
Reynolds number: 100,000
Max Cl/Cd: 67.07 at α=4°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe427-il-100000-n5.txt
Download as CSV file: xf-goe427-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 427 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
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.3260   0.10217   0.09750  -0.0240   1.0000   0.0303
  -7.500  -0.3327   0.10101   0.09643  -0.0225   1.0000   0.0305
  -7.250  -0.3361   0.09974   0.09524  -0.0225   1.0000   0.0307
  -7.000  -0.3366   0.09800   0.09357  -0.0228   1.0000   0.0308
  -6.750  -0.3355   0.09630   0.09192  -0.0238   1.0000   0.0309
  -6.500  -0.3321   0.09434   0.09001  -0.0252   1.0000   0.0310
  -6.250  -0.3265   0.09211   0.08781  -0.0267   1.0000   0.0311
  -6.000  -0.3022   0.08840   0.08406  -0.0327   0.9967   0.0312
  -5.750  -0.2716   0.08400   0.07960  -0.0394   0.9920   0.0313
  -5.500  -0.2386   0.07934   0.07488  -0.0463   0.9875   0.0313
  -5.250  -0.2261   0.07356   0.06915  -0.0469   0.9827   0.0319
  -5.000  -0.2030   0.06893   0.06447  -0.0497   0.9784   0.0328
  -4.750  -0.1746   0.06489   0.06038  -0.0542   0.9719   0.0337
  -4.500  -0.1358   0.06055   0.05594  -0.0612   0.9673   0.0345
  -4.250  -0.1005   0.05649   0.05177  -0.0671   0.9599   0.0347
  -4.000  -0.0580   0.05256   0.04770  -0.0740   0.9554   0.0378
  -3.500   0.0330   0.04321   0.03782  -0.0874   0.9433   0.0300
  -3.250   0.0723   0.03919   0.03357  -0.0919   0.9382   0.0291
  -3.000   0.1112   0.03529   0.02938  -0.0957   0.9324   0.0290
  -2.750   0.1587   0.03058   0.02410  -0.1005   0.9292   0.0321
  -2.500   0.1907   0.02826   0.02155  -0.1023   0.9235   0.0342
  -2.250   0.2271   0.02532   0.01810  -0.1042   0.9183   0.0360
  -2.000   0.2680   0.02292   0.01488  -0.1063   0.9149   0.0424
  -1.750   0.2986   0.02093   0.01255  -0.1070   0.9086   0.0460
  -1.500   0.3327   0.01991   0.01118  -0.1081   0.9031   0.0543
  -1.250   0.3706   0.01847   0.00936  -0.1097   0.8996   0.0569
  -1.000   0.3978   0.01765   0.00845  -0.1095   0.8908   0.0609
  -0.750   0.4337   0.01703   0.00767  -0.1109   0.8860   0.0691
  -0.500   0.4615   0.01656   0.00721  -0.1108   0.8765   0.0754
  -0.250   0.4935   0.01605   0.00660  -0.1112   0.8692   0.0798
   0.000   0.5260   0.01563   0.00612  -0.1118   0.8607   0.0880
   0.250   0.5565   0.01526   0.00576  -0.1120   0.8505   0.1141
   0.500   0.5884   0.01481   0.00551  -0.1126   0.8401   0.1937
   1.000   0.6579   0.01302   0.00506  -0.1149   0.8176   1.0000
   1.250   0.6876   0.01301   0.00492  -0.1150   0.8038   1.0000
   1.500   0.7170   0.01302   0.00483  -0.1149   0.7896   1.0000
   1.750   0.7461   0.01306   0.00478  -0.1149   0.7750   1.0000
   2.000   0.7743   0.01312   0.00479  -0.1147   0.7594   1.0000
   2.250   0.8016   0.01322   0.00487  -0.1143   0.7427   1.0000
   2.500   0.8287   0.01335   0.00496  -0.1140   0.7256   1.0000
   2.750   0.8556   0.01349   0.00508  -0.1135   0.7081   1.0000
   3.000   0.8822   0.01365   0.00526  -0.1131   0.6904   1.0000
   3.250   0.9078   0.01384   0.00546  -0.1124   0.6711   1.0000
   3.500   0.9321   0.01403   0.00560  -0.1114   0.6441   1.0000
   3.750   0.9550   0.01425   0.00574  -0.1101   0.6101   1.0000
   4.000   0.9772   0.01457   0.00591  -0.1086   0.5716   1.0000
   4.250   0.9996   0.01496   0.00619  -0.1074   0.5406   1.0000
   4.500   1.0222   0.01537   0.00656  -0.1062   0.5152   1.0000
   4.750   1.0443   0.01580   0.00698  -0.1051   0.4887   1.0000
   5.000   1.0657   0.01623   0.00749  -0.1038   0.4584   1.0000
   5.250   1.0853   0.01671   0.00796  -0.1022   0.4145   1.0000
   5.500   1.1028   0.01737   0.00846  -0.1002   0.3555   1.0000
   5.750   1.1164   0.01849   0.00917  -0.0979   0.2643   1.0000
   6.000   1.1224   0.02075   0.01049  -0.0949   0.1132   1.0000
   6.250   1.1338   0.02252   0.01191  -0.0925   0.0643   1.0000
   6.500   1.1489   0.02378   0.01323  -0.0905   0.0487   1.0000
   6.750   1.1611   0.02528   0.01480  -0.0881   0.0401   1.0000
   7.000   1.1698   0.02701   0.01667  -0.0853   0.0342   1.0000
   7.250   1.1795   0.02863   0.01850  -0.0824   0.0295   1.0000
   7.500   1.1878   0.03046   0.02040  -0.0796   0.0258   1.0000
   7.750   1.1979   0.03290   0.02285  -0.0771   0.0237   1.0000
   8.000   1.2164   0.03444   0.02467  -0.0755   0.0209   1.0000
   8.250   1.2367   0.03666   0.02712  -0.0743   0.0186   1.0000
   8.500   1.2589   0.03942   0.03013  -0.0733   0.0172   1.0000
   8.750   1.2776   0.04222   0.03331  -0.0720   0.0161   1.0000
   9.000   1.2894   0.04485   0.03617  -0.0704   0.0147   1.0000
   9.250   1.2983   0.04939   0.04100  -0.0688   0.0136   1.0000
   9.500   1.3019   0.05274   0.04476  -0.0660   0.0132   1.0000
   9.750   1.3020   0.05597   0.04840  -0.0630   0.0130   1.0000
  10.000   1.2966   0.05914   0.05193  -0.0595   0.0129   1.0000
  10.250   1.2873   0.06240   0.05551  -0.0560   0.0128   1.0000
  10.500   1.2757   0.06581   0.05922  -0.0531   0.0128   1.0000
  10.750   1.2620   0.06947   0.06317  -0.0507   0.0128   1.0000
  11.000   1.2466   0.07348   0.06744  -0.0491   0.0128   1.0000
  11.250   1.2301   0.07787   0.07208  -0.0484   0.0128   1.0000
  11.500   1.2133   0.08266   0.07710  -0.0486   0.0128   1.0000
  11.750   1.1957   0.08796   0.08260  -0.0497   0.0129   1.0000
  12.000   1.1779   0.09375   0.08859  -0.0518   0.0129   1.0000
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