Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

GOE 398 AIRFOIL (goe398-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 398 AIRFOIL (goe398-il)
Reynolds number: 100,000
Max Cl/Cd: 50.05 at α=6.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe398-il-100000.txt
Download as CSV file: xf-goe398-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 398 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.3528   0.10829   0.10384  -0.0297   1.0000   0.1281
  -8.750  -0.3911   0.10839   0.10407  -0.0283   1.0000   0.1288
  -8.500  -0.4260   0.10801   0.10382  -0.0265   1.0000   0.1291
  -8.250  -0.3894   0.10299   0.09878  -0.0227   1.0000   0.1323
  -8.000  -0.3711   0.10007   0.09585  -0.0237   0.9969   0.1365
  -7.750  -0.3876   0.09689   0.09271  -0.0342   0.9854   0.1435
  -7.500  -0.3804   0.09172   0.08754  -0.0390   0.9779   0.1463
  -7.250  -0.3465   0.08880   0.08460  -0.0377   0.9744   0.1506
  -7.000  -0.3644   0.08263   0.07828  -0.0543   0.9584   0.1612
  -6.750  -0.3263   0.08033   0.07609  -0.0492   0.9574   0.1648
  -6.500  -0.3155   0.07773   0.07346  -0.0502   0.9484   0.1718
  -6.250  -0.3038   0.07252   0.06816  -0.0575   0.9406   0.1807
  -6.000  -0.2901   0.07020   0.06584  -0.0567   0.9315   0.1857
  -5.750  -0.2796   0.06555   0.06101  -0.0626   0.9219   0.1976
  -5.500  -0.2716   0.05303   0.04767  -0.0715   0.9121   0.1412
  -5.250  -0.2722   0.04197   0.03538  -0.0716   0.9032   0.1063
  -5.000  -0.2480   0.03742   0.02964  -0.0715   0.8959   0.1019
  -4.750  -0.2182   0.03514   0.02720  -0.0724   0.8892   0.1039
  -4.500  -0.1937   0.03405   0.02603  -0.0720   0.8810   0.1071
  -4.250  -0.1538   0.03220   0.02380  -0.0738   0.8766   0.1100
  -4.000  -0.1368   0.03128   0.02256  -0.0718   0.8674   0.1124
  -3.750  -0.1012   0.02992   0.02099  -0.0729   0.8617   0.1177
  -3.500  -0.0545   0.02871   0.01967  -0.0758   0.8583   0.1255
  -3.250  -0.0419   0.02829   0.01911  -0.0730   0.8473   0.1307
  -3.000   0.0016   0.02733   0.01813  -0.0752   0.8428   0.1439
  -2.750   0.0533   0.02608   0.01700  -0.0789   0.8403   0.1641
  -2.500   0.0605   0.02612   0.01703  -0.0751   0.8276   0.1782
  -2.250   0.1091   0.02494   0.01606  -0.0782   0.8244   0.2167
  -2.000   0.1232   0.02466   0.01594  -0.0756   0.8135   0.2505
  -1.750   0.1638   0.02343   0.01521  -0.0774   0.8086   0.3281
  -1.500   0.2095   0.02199   0.01452  -0.0797   0.8053   0.4807
  -1.250   0.4165   0.01956   0.01324  -0.1119   0.8086   1.0000
  -1.000   0.4397   0.01953   0.01301  -0.1108   0.7987   1.0000
  -0.750   0.4706   0.01931   0.01259  -0.1108   0.7899   1.0000
  -0.500   0.4900   0.01941   0.01255  -0.1090   0.7786   1.0000
  -0.250   0.5264   0.01905   0.01200  -0.1098   0.7708   1.0000
   0.000   0.5431   0.01923   0.01207  -0.1075   0.7581   1.0000
   0.250   0.5801   0.01887   0.01154  -0.1083   0.7502   1.0000
   0.500   0.5991   0.01898   0.01155  -0.1063   0.7373   1.0000
   0.750   0.6206   0.01905   0.01152  -0.1047   0.7250   1.0000
   1.000   0.6577   0.01870   0.01100  -0.1055   0.7165   1.0000
   1.250   0.6754   0.01887   0.01110  -0.1033   0.7026   1.0000
   1.500   0.6974   0.01897   0.01111  -0.1018   0.6898   1.0000
   1.750   0.7288   0.01882   0.01080  -0.1017   0.6797   1.0000
   2.000   0.7517   0.01888   0.01078  -0.1004   0.6667   1.0000
   2.250   0.7724   0.01905   0.01089  -0.0987   0.6536   1.0000
   2.500   0.7982   0.01909   0.01082  -0.0978   0.6419   1.0000
   2.750   0.8264   0.01907   0.01066  -0.0974   0.6307   1.0000
   3.000   0.8450   0.01933   0.01088  -0.0954   0.6174   1.0000
   3.250   0.8682   0.01950   0.01099  -0.0942   0.6058   1.0000
   3.500   0.8973   0.01952   0.01086  -0.0940   0.5954   1.0000
   3.750   0.9141   0.01986   0.01121  -0.0918   0.5828   1.0000
   4.000   0.9369   0.02008   0.01138  -0.0906   0.5718   1.0000
   4.250   0.9642   0.02017   0.01135  -0.0902   0.5614   1.0000
   4.500   0.9809   0.02055   0.01175  -0.0880   0.5495   1.0000
   4.750   1.0046   0.02078   0.01193  -0.0871   0.5391   1.0000
   5.000   1.0289   0.02099   0.01206  -0.0862   0.5285   1.0000
   5.250   1.0466   0.02139   0.01249  -0.0842   0.5173   1.0000
   5.500   1.0718   0.02164   0.01266  -0.0836   0.5071   1.0000
   5.750   1.0931   0.02196   0.01295  -0.0822   0.4959   1.0000
   6.000   1.1115   0.02242   0.01342  -0.0805   0.4849   1.0000
   6.250   1.1387   0.02275   0.01364  -0.0802   0.4749   1.0000
   6.500   1.1561   0.02326   0.01420  -0.0783   0.4638   1.0000
   6.750   1.1762   0.02382   0.01474  -0.0770   0.4533   1.0000
   7.000   1.2046   0.02424   0.01504  -0.0770   0.4431   1.0000
   7.250   1.2166   0.02494   0.01586  -0.0743   0.4321   1.0000
   7.500   1.2408   0.02553   0.01638  -0.0737   0.4223   1.0000
   7.750   1.2586   0.02618   0.01707  -0.0721   0.4123   1.0000
   8.000   1.2777   0.02695   0.01788  -0.0707   0.4033   1.0000
   8.250   1.2982   0.02762   0.01857  -0.0696   0.3944   1.0000
   8.500   1.3157   0.02848   0.01950  -0.0681   0.3863   1.0000
   8.750   1.3338   0.02914   0.02021  -0.0666   0.3778   1.0000
   9.000   1.3508   0.02987   0.02099  -0.0649   0.3695   1.0000
   9.250   1.3669   0.03039   0.02154  -0.0631   0.3608   1.0000
   9.500   1.3821   0.03106   0.02226  -0.0612   0.3527   1.0000
   9.750   1.3962   0.03153   0.02279  -0.0590   0.3443   1.0000
  10.000   1.4128   0.03217   0.02346  -0.0574   0.3371   1.0000
  10.250   1.4208   0.03285   0.02427  -0.0545   0.3297   1.0000
  10.500   1.4436   0.03320   0.02455  -0.0538   0.3223   1.0000
  10.750   1.4425   0.03405   0.02562  -0.0495   0.3154   1.0000
  11.000   1.4736   0.03415   0.02556  -0.0500   0.3078   1.0000
  11.250   1.4622   0.03527   0.02696  -0.0444   0.3023   1.0000
  11.500   1.4733   0.03558   0.02728  -0.0419   0.2950   1.0000
  11.750   1.4772   0.03630   0.02809  -0.0387   0.2884   1.0000
  12.000   1.4764   0.03717   0.02909  -0.0351   0.2819   1.0000
  12.250   1.4950   0.03748   0.02935  -0.0339   0.2749   1.0000
  12.500   1.4834   0.03890   0.03101  -0.0295   0.2689   1.0000
  12.750   1.5055   0.03891   0.03089  -0.0288   0.2605   1.0000
  13.000   1.4870   0.04083   0.03312  -0.0243   0.2549   1.0000
  13.250   1.4973   0.04126   0.03349  -0.0225   0.2462   1.0000
  13.500   1.4821   0.04335   0.03582  -0.0192   0.2395   1.0000
  13.750   1.4889   0.04403   0.03640  -0.0174   0.2295   1.0000
  14.000   1.4675   0.04686   0.03951  -0.0145   0.2220   1.0000
  14.250   1.4607   0.04874   0.04139  -0.0126   0.2117   1.0000
  14.500   1.4512   0.05098   0.04364  -0.0110   0.2005   1.0000
  14.750   1.4287   0.05482   0.04766  -0.0096   0.1899   1.0000
  15.000   1.4110   0.05855   0.05143  -0.0087   0.1778   1.0000
  15.250   1.3943   0.06251   0.05539  -0.0083   0.1655   1.0000
  15.500   1.3810   0.06641   0.05924  -0.0081   0.1543   1.0000
  15.750   1.3706   0.07019   0.06296  -0.0081   0.1447   1.0000
  16.000   1.3569   0.07478   0.06766  -0.0086   0.1369   1.0000
  16.250   1.3542   0.07785   0.07063  -0.0086   0.1298   1.0000
  16.500   1.3443   0.08223   0.07515  -0.0093   0.1241   1.0000
  16.750   1.3490   0.08435   0.07712  -0.0090   0.1184   1.0000
  17.000   1.3383   0.08906   0.08204  -0.0100   0.1145   1.0000
  17.250   1.3391   0.09199   0.08497  -0.0103   0.1103   1.0000
  17.500   1.3459   0.09398   0.08693  -0.0100   0.1063   1.0000
  17.750   1.3351   0.09891   0.09207  -0.0113   0.1037   1.0000
  18.000   1.3312   0.10275   0.09602  -0.0122   0.1008   1.0000
  18.250   1.3599   0.10129   0.09430  -0.0102   0.0964   1.0000
  18.500   1.3399   0.10777   0.10108  -0.0126   0.0950   1.0000
  18.750   1.3200   0.11450   0.10806  -0.0154   0.0937   1.0000
  19.000   1.2944   0.12245   0.11627  -0.0190   0.0928   1.0000
<< Back to GOE 398 AIRFOIL (goe398-il)

Polar data table (+)

Polar graphs


<< Back to GOE 398 AIRFOIL (goe398-il)