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GOE 654 AIRFOIL (goe654-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: GOE 654 AIRFOIL (goe654-il)
Reynolds number: 500,000
Max Cl/Cd: 92.4 at α=6.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe654-il-500000-n5.txt
Download as CSV file: xf-goe654-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 654 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.750  -0.2469   0.11571   0.11336  -0.0410   0.9906   0.0186
 -11.500  -0.2407   0.11076   0.10840  -0.0444   0.9769   0.0191
 -11.250  -0.2407   0.10222   0.09984  -0.0515   0.9570   0.0199
 -11.000  -0.2077   0.09806   0.09562  -0.0594   0.9385   0.0202
 -10.750  -0.1650   0.09312   0.09060  -0.0702   0.9224   0.0206
 -10.500  -0.1212   0.08731   0.08463  -0.0827   0.8968   0.0213
 -10.250  -0.1005   0.08204   0.07916  -0.0903   0.8603   0.0221
 -10.000  -0.0992   0.07773   0.07470  -0.0931   0.8283   0.0223
  -9.500  -0.2143   0.04786   0.04470  -0.1107   0.7909   0.0232
  -9.250  -0.2966   0.03612   0.03236  -0.1145   0.7713   0.0231
  -9.000  -0.3153   0.03118   0.02685  -0.1127   0.7573   0.0233
  -8.750  -0.3128   0.02845   0.02367  -0.1110   0.7440   0.0235
  -8.500  -0.3033   0.02627   0.02117  -0.1095   0.7315   0.0237
  -8.250  -0.2885   0.02465   0.01933  -0.1084   0.7192   0.0239
  -8.000  -0.2702   0.02359   0.01809  -0.1073   0.7064   0.0241
  -7.750  -0.2504   0.02268   0.01704  -0.1064   0.6928   0.0243
  -7.500  -0.2296   0.02189   0.01608  -0.1055   0.6788   0.0246
  -7.250  -0.2079   0.02125   0.01531  -0.1047   0.6646   0.0249
  -7.000  -0.1866   0.02037   0.01423  -0.1038   0.6513   0.0251
  -6.750  -0.1649   0.01952   0.01319  -0.1029   0.6379   0.0253
  -6.250  -0.1199   0.01805   0.01131  -0.1011   0.6084   0.0258
  -6.000  -0.0967   0.01741   0.01048  -0.1003   0.5938   0.0260
  -5.750  -0.0729   0.01682   0.00972  -0.0995   0.5816   0.0262
  -5.500  -0.0488   0.01629   0.00903  -0.0988   0.5714   0.0265
  -5.250  -0.0239   0.01577   0.00838  -0.0982   0.5631   0.0267
  -5.000   0.0009   0.01533   0.00781  -0.0975   0.5550   0.0269
  -4.750   0.0263   0.01490   0.00728  -0.0970   0.5469   0.0272
  -4.250   0.0777   0.01431   0.00649  -0.0959   0.5342   0.0278
  -4.000   0.1038   0.01402   0.00613  -0.0955   0.5294   0.0280
  -3.750   0.1285   0.01349   0.00555  -0.0948   0.5245   0.0284
  -3.500   0.1539   0.01313   0.00516  -0.0943   0.5201   0.0287
  -3.250   0.1799   0.01282   0.00483  -0.0938   0.5156   0.0290
  -3.000   0.2059   0.01257   0.00456  -0.0934   0.5114   0.0294
  -2.750   0.2318   0.01236   0.00432  -0.0929   0.5073   0.0298
  -2.500   0.2579   0.01218   0.00410  -0.0925   0.5036   0.0302
  -2.250   0.2845   0.01198   0.00390  -0.0921   0.4997   0.0306
  -2.000   0.3109   0.01182   0.00371  -0.0917   0.4949   0.0310
  -1.750   0.3372   0.01169   0.00355  -0.0913   0.4903   0.0315
  -1.500   0.3636   0.01158   0.00340  -0.0909   0.4862   0.0320
  -1.250   0.3906   0.01147   0.00328  -0.0906   0.4820   0.0327
  -1.000   0.4173   0.01136   0.00315  -0.0902   0.4774   0.0335
  -0.750   0.4436   0.01126   0.00302  -0.0898   0.4728   0.0346
  -0.500   0.4703   0.01119   0.00294  -0.0895   0.4682   0.0357
  -0.250   0.4973   0.01113   0.00286  -0.0892   0.4625   0.0368
   0.000   0.5236   0.01111   0.00280  -0.0888   0.4561   0.0382
   0.250   0.5503   0.01108   0.00276  -0.0884   0.4501   0.0405
   0.750   0.6010   0.01072   0.00272  -0.0875   0.4367   0.1565
   1.000   0.6245   0.01027   0.00276  -0.0869   0.4290   0.3298
   1.250   0.6484   0.01010   0.00282  -0.0862   0.4207   0.4323
   1.500   0.6716   0.00989   0.00291  -0.0853   0.4107   0.5419
   1.750   0.6938   0.00974   0.00298  -0.0842   0.3999   0.6335
   2.000   0.7111   0.00944   0.00309  -0.0819   0.3892   0.7852
   2.250   0.7978   0.00948   0.00334  -0.0944   0.3718   1.0000
   2.500   0.8203   0.00966   0.00343  -0.0933   0.3627   1.0000
   2.750   0.8430   0.00983   0.00354  -0.0923   0.3554   1.0000
   3.000   0.8656   0.01002   0.00365  -0.0912   0.3480   1.0000
   3.250   0.8881   0.01021   0.00378  -0.0902   0.3418   1.0000
   3.500   0.9112   0.01039   0.00391  -0.0892   0.3357   1.0000
   3.750   0.9337   0.01059   0.00406  -0.0882   0.3303   1.0000
   4.000   0.9566   0.01078   0.00421  -0.0873   0.3262   1.0000
   4.250   0.9801   0.01095   0.00435  -0.0864   0.3220   1.0000
   4.500   1.0031   0.01114   0.00451  -0.0855   0.3178   1.0000
   4.750   1.0253   0.01137   0.00470  -0.0845   0.3135   1.0000
   5.000   1.0482   0.01156   0.00487  -0.0836   0.3102   1.0000
   5.250   1.0716   0.01173   0.00505  -0.0828   0.3070   1.0000
   5.500   1.0945   0.01193   0.00523  -0.0819   0.3033   1.0000
   5.750   1.1165   0.01215   0.00544  -0.0809   0.2996   1.0000
   6.000   1.1377   0.01241   0.00567  -0.0798   0.2959   1.0000
   6.250   1.1605   0.01259   0.00586  -0.0790   0.2924   1.0000
   6.500   1.1827   0.01280   0.00607  -0.0780   0.2877   1.0000
   6.750   1.2032   0.01306   0.00631  -0.0768   0.2828   1.0000
   7.000   1.2230   0.01334   0.00656  -0.0755   0.2790   1.0000
   7.250   1.2444   0.01352   0.00678  -0.0744   0.2767   1.0000
   7.500   1.2643   0.01373   0.00701  -0.0731   0.2733   1.0000
   7.750   1.2829   0.01398   0.00727  -0.0715   0.2693   1.0000
   8.000   1.2994   0.01431   0.00757  -0.0696   0.2647   1.0000
   8.250   1.3186   0.01456   0.00785  -0.0683   0.2605   1.0000
   8.500   1.3372   0.01483   0.00815  -0.0669   0.2559   1.0000
   8.750   1.3534   0.01520   0.00850  -0.0651   0.2502   1.0000
   9.000   1.3709   0.01553   0.00885  -0.0636   0.2448   1.0000
   9.250   1.3879   0.01590   0.00922  -0.0621   0.2386   1.0000
   9.500   1.4025   0.01637   0.00968  -0.0603   0.2319   1.0000
   9.750   1.4179   0.01683   0.01014  -0.0587   0.2235   1.0000
  10.000   1.4314   0.01739   0.01069  -0.0569   0.2164   1.0000
  10.250   1.4442   0.01801   0.01130  -0.0551   0.2073   1.0000
  10.500   1.4553   0.01874   0.01202  -0.0532   0.1974   1.0000
  10.750   1.4632   0.01969   0.01292  -0.0511   0.1852   1.0000
  11.000   1.4674   0.02091   0.01407  -0.0488   0.1705   1.0000
  11.250   1.4699   0.02234   0.01543  -0.0465   0.1562   1.0000
  11.500   1.4717   0.02391   0.01696  -0.0445   0.1434   1.0000
  11.750   1.4734   0.02561   0.01864  -0.0427   0.1321   1.0000
  12.000   1.4718   0.02766   0.02065  -0.0409   0.1196   1.0000
  12.250   1.4692   0.02993   0.02289  -0.0394   0.1077   1.0000
  12.500   1.4649   0.03246   0.02539  -0.0381   0.0953   1.0000
  12.750   1.4386   0.03718   0.02996  -0.0364   0.0657   1.0000
  13.000   1.4141   0.04209   0.03482  -0.0354   0.0442   1.0000
  13.250   1.3925   0.04705   0.03979  -0.0349   0.0242   1.0000
  13.500   1.3825   0.05097   0.04375  -0.0348   0.0190   1.0000
  13.750   1.3780   0.05436   0.04723  -0.0349   0.0170   1.0000
  14.000   1.3764   0.05747   0.05042  -0.0350   0.0163   1.0000
  14.250   1.3725   0.06090   0.05394  -0.0352   0.0154   1.0000
  14.500   1.3680   0.06448   0.05761  -0.0355   0.0148   1.0000
  14.750   1.3634   0.06811   0.06134  -0.0359   0.0143   1.0000
  15.000   1.3599   0.07165   0.06498  -0.0363   0.0140   1.0000
  15.250   1.3557   0.07536   0.06878  -0.0368   0.0137   1.0000
  15.500   1.3512   0.07918   0.07270  -0.0375   0.0134   1.0000
  15.750   1.3452   0.08326   0.07688  -0.0382   0.0130   1.0000
  16.000   1.3394   0.08735   0.08107  -0.0391   0.0127   1.0000
  16.250   1.3324   0.09172   0.08554  -0.0401   0.0125   1.0000
  16.500   1.3239   0.09640   0.09032  -0.0412   0.0121   1.0000
  16.750   1.3163   0.10099   0.09501  -0.0425   0.0120   1.0000
  17.000   1.3072   0.10588   0.10000  -0.0439   0.0118   1.0000
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