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GOE 436 AIRFOIL (goe436-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 436 AIRFOIL (goe436-il)
Reynolds number: 100,000
Max Cl/Cd: 47.78 at α=10.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe436-il-100000.txt
Download as CSV file: xf-goe436-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 436 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
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.3460   0.09296   0.08805  -0.0325   1.0000   0.1192
  -8.000  -0.3773   0.09220   0.08746  -0.0322   1.0000   0.1213
  -7.750  -0.4140   0.09130   0.08670  -0.0328   1.0000   0.1221
  -7.500  -0.4497   0.09013   0.08550  -0.0352   1.0000   0.1227
  -7.250  -0.4146   0.08469   0.08021  -0.0273   1.0000   0.1252
  -7.000  -0.4093   0.08277   0.07833  -0.0235   1.0000   0.1283
  -6.750  -0.4177   0.08084   0.07645  -0.0218   1.0000   0.1319
  -6.500  -0.4357   0.07857   0.07419  -0.0235   1.0000   0.1366
  -6.250  -0.4529   0.07486   0.07038  -0.0269   1.0000   0.1399
  -6.000  -0.4455   0.07245   0.06809  -0.0223   1.0000   0.1421
  -5.750  -0.4427   0.07040   0.06606  -0.0200   1.0000   0.1455
  -5.500  -0.4479   0.06710   0.06245  -0.0256   1.0000   0.1560
  -5.250  -0.4417   0.06425   0.05975  -0.0223   1.0000   0.1579
  -5.000  -0.4356   0.06235   0.05790  -0.0199   1.0000   0.1620
  -4.750  -0.4067   0.05861   0.05400  -0.0252   0.9943   0.1762
  -4.500  -0.3639   0.05488   0.05011  -0.0318   0.9843   0.1928
  -4.250  -0.3256   0.05165   0.04676  -0.0365   0.9739   0.2101
  -4.000  -0.2898   0.04920   0.04409  -0.0412   0.9637   0.2398
  -3.750  -0.2546   0.04649   0.04145  -0.0433   0.9566   0.2602
  -3.500  -0.2273   0.04448   0.03938  -0.0447   0.9460   0.2915
  -3.250  -0.1514   0.03388   0.02651  -0.0565   0.9411   0.1416
  -3.000  -0.1179   0.03168   0.02393  -0.0575   0.9307   0.1340
  -2.750  -0.0696   0.02928   0.02107  -0.0610   0.9251   0.1297
  -2.500  -0.0376   0.02799   0.01951  -0.0616   0.9136   0.1316
  -2.250   0.0025   0.02665   0.01788  -0.0634   0.9046   0.1334
  -2.000   0.0469   0.02533   0.01629  -0.0659   0.8965   0.1350
  -1.750   0.0847   0.02454   0.01525  -0.0671   0.8860   0.1389
  -1.500   0.1345   0.02296   0.01374  -0.0707   0.8800   0.1452
  -1.250   0.1726   0.02206   0.01281  -0.0719   0.8692   0.1507
  -1.000   0.2225   0.02079   0.01163  -0.0752   0.8631   0.1612
  -0.750   0.2561   0.02006   0.01090  -0.0754   0.8504   0.1714
  -0.500   0.2911   0.01911   0.01011  -0.0759   0.8385   0.1867
  -0.250   0.4090   0.01515   0.00878  -0.0916   0.8349   1.0000
   0.000   0.4411   0.01488   0.00824  -0.0914   0.8184   1.0000
   0.250   0.4712   0.01466   0.00781  -0.0909   0.8006   1.0000
   0.500   0.5004   0.01447   0.00743  -0.0902   0.7815   1.0000
   0.750   0.5221   0.01444   0.00725  -0.0883   0.7573   1.0000
   1.000   0.5483   0.01433   0.00694  -0.0872   0.7343   1.0000
   1.250   0.5709   0.01435   0.00678  -0.0855   0.7082   1.0000
   1.500   0.5966   0.01438   0.00658  -0.0844   0.6847   1.0000
   1.750   0.6196   0.01457   0.00657  -0.0830   0.6599   1.0000
   2.000   0.6447   0.01480   0.00656  -0.0820   0.6388   1.0000
   2.250   0.6678   0.01514   0.00673  -0.0808   0.6183   1.0000
   2.500   0.6912   0.01550   0.00694  -0.0797   0.6005   1.0000
   2.750   0.7151   0.01588   0.00718  -0.0788   0.5852   1.0000
   3.000   0.7395   0.01627   0.00742  -0.0779   0.5717   1.0000
   3.250   0.7631   0.01665   0.00772  -0.0770   0.5587   1.0000
   3.500   0.7859   0.01706   0.00810  -0.0760   0.5467   1.0000
   3.750   0.8103   0.01748   0.00845  -0.0753   0.5367   1.0000
   4.000   0.8348   0.01789   0.00880  -0.0746   0.5272   1.0000
   4.250   0.8577   0.01834   0.00927  -0.0737   0.5176   1.0000
   4.500   0.8839   0.01877   0.00960  -0.0732   0.5098   1.0000
   4.750   0.9057   0.01928   0.01020  -0.0722   0.5010   1.0000
   5.000   0.9324   0.01974   0.01056  -0.0719   0.4939   1.0000
   5.250   0.9535   0.02029   0.01123  -0.0707   0.4853   1.0000
   5.500   0.9803   0.02077   0.01163  -0.0705   0.4783   1.0000
   5.750   1.0005   0.02132   0.01231  -0.0692   0.4691   1.0000
   6.000   1.0264   0.02177   0.01268  -0.0687   0.4606   1.0000
   6.250   1.0471   0.02221   0.01321  -0.0674   0.4500   1.0000
   6.500   1.0690   0.02269   0.01372  -0.0663   0.4399   1.0000
   6.750   1.0955   0.02308   0.01398  -0.0659   0.4301   1.0000
   7.000   1.1134   0.02360   0.01469  -0.0642   0.4199   1.0000
   7.250   1.1379   0.02413   0.01521  -0.0636   0.4115   1.0000
   7.500   1.1578   0.02468   0.01591  -0.0623   0.4027   1.0000
   7.750   1.1806   0.02524   0.01650  -0.0614   0.3941   1.0000
   8.000   1.2019   0.02565   0.01700  -0.0603   0.3843   1.0000
   8.250   1.2205   0.02616   0.01764  -0.0587   0.3741   1.0000
   8.500   1.2456   0.02648   0.01790  -0.0581   0.3646   1.0000
   8.750   1.2610   0.02694   0.01859  -0.0561   0.3542   1.0000
   9.000   1.2806   0.02738   0.01915  -0.0547   0.3446   1.0000
   9.250   1.3039   0.02750   0.01921  -0.0537   0.3338   1.0000
   9.500   1.3158   0.02778   0.01972  -0.0511   0.3215   1.0000
   9.750   1.3296   0.02803   0.02012  -0.0487   0.3091   1.0000
  10.000   1.3429   0.02818   0.02040  -0.0463   0.2961   1.0000
  10.250   1.3535   0.02833   0.02065  -0.0434   0.2820   1.0000
  10.500   1.3593   0.02851   0.02096  -0.0398   0.2656   1.0000
  10.750   1.3599   0.02877   0.02129  -0.0355   0.2464   1.0000
  11.000   1.3534   0.02929   0.02178  -0.0303   0.2255   1.0000
  11.250   1.3438   0.03034   0.02274  -0.0254   0.2015   1.0000
  11.500   1.3338   0.03201   0.02427  -0.0212   0.1787   1.0000
  11.750   1.3240   0.03408   0.02618  -0.0177   0.1609   1.0000
  12.000   1.3165   0.03632   0.02831  -0.0149   0.1469   1.0000
  12.250   1.3115   0.03863   0.03060  -0.0126   0.1353   1.0000
  12.500   1.3083   0.04099   0.03292  -0.0108   0.1262   1.0000
  12.750   1.3064   0.04335   0.03518  -0.0092   0.1181   1.0000
  13.000   1.3047   0.04584   0.03781  -0.0079   0.1105   1.0000
  13.250   1.3047   0.04828   0.04016  -0.0068   0.1035   1.0000
  13.500   1.3020   0.05105   0.04309  -0.0059   0.0970   1.0000
  13.750   1.3027   0.05364   0.04564  -0.0051   0.0908   1.0000
  14.000   1.3003   0.05659   0.04874  -0.0046   0.0854   1.0000
  14.250   1.3048   0.05906   0.05111  -0.0038   0.0797   1.0000
  14.500   1.3034   0.06220   0.05443  -0.0035   0.0754   1.0000
  14.750   1.3205   0.06394   0.05597  -0.0022   0.0699   1.0000
  15.000   1.3134   0.06772   0.06004  -0.0023   0.0673   1.0000
  15.250   1.3120   0.07112   0.06360  -0.0023   0.0646   1.0000
  15.500   1.3445   0.07285   0.06514  -0.0006   0.0601   1.0000
  15.750   1.3302   0.07731   0.06991  -0.0012   0.0595   1.0000
  16.000   1.3153   0.08217   0.07507  -0.0023   0.0589   1.0000
  16.250   1.2990   0.08746   0.08065  -0.0039   0.0584   1.0000
  16.500   1.2797   0.09348   0.08694  -0.0062   0.0581   1.0000
  16.750   1.2577   0.10017   0.09390  -0.0093   0.0579   1.0000
  17.000   1.2329   0.10772   0.10170  -0.0133   0.0579   1.0000
  17.250   1.2056   0.11630   0.11051  -0.0181   0.0583   1.0000
  17.500   1.1735   0.12635   0.12078  -0.0242   0.0589   1.0000
  17.750   1.1415   0.13723   0.13182  -0.0309   0.0597   1.0000
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