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

GOE 512 AIRFOIL (goe512-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: GOE 512 AIRFOIL (goe512-il)
Reynolds number: 1,000,000
Max Cl/Cd: 88.16 at α=9.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe512-il-1000000-n5.txt
Download as CSV file: xf-goe512-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 512 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -15.000  -0.4596   0.09880   0.09667  -0.0774   0.9891   0.0084
 -14.750  -0.5267   0.08270   0.08042  -0.0875   0.9878   0.0084
 -14.500  -0.8059   0.03675   0.03373  -0.1232   0.9754   0.0076
 -14.250  -0.8099   0.03048   0.02716  -0.1259   0.9736   0.0076
 -14.000  -0.8088   0.02781   0.02431  -0.1239   0.9688   0.0076
 -13.750  -0.7955   0.02609   0.02245  -0.1232   0.9663   0.0077
 -13.500  -0.7773   0.02474   0.02097  -0.1229   0.9645   0.0078
 -13.250  -0.7582   0.02323   0.01932  -0.1228   0.9630   0.0079
 -13.000  -0.7363   0.02177   0.01773  -0.1231   0.9617   0.0081
 -12.750  -0.7112   0.02058   0.01643  -0.1237   0.9608   0.0083
 -12.500  -0.7069   0.01995   0.01572  -0.1195   0.9552   0.0085
 -12.250  -0.6857   0.01912   0.01480  -0.1187   0.9527   0.0087
 -12.000  -0.6599   0.01835   0.01395  -0.1189   0.9507   0.0089
 -11.750  -0.6329   0.01759   0.01310  -0.1192   0.9490   0.0091
 -11.500  -0.6031   0.01690   0.01233  -0.1200   0.9474   0.0093
 -11.250  -0.5844   0.01639   0.01174  -0.1184   0.9430   0.0096
 -11.000  -0.5661   0.01589   0.01117  -0.1165   0.9373   0.0097
 -10.750  -0.5371   0.01529   0.01048  -0.1170   0.9337   0.0100
 -10.500  -0.5048   0.01478   0.00989  -0.1181   0.9309   0.0102
 -10.250  -0.4940   0.01431   0.00936  -0.1146   0.9233   0.0105
 -10.000  -0.4684   0.01380   0.00879  -0.1142   0.9189   0.0109
  -9.750  -0.4396   0.01334   0.00826  -0.1145   0.9148   0.0114
  -9.500  -0.4199   0.01301   0.00790  -0.1127   0.9068   0.0119
  -9.250  -0.3906   0.01260   0.00741  -0.1130   0.8993   0.0124
  -9.000  -0.3668   0.01230   0.00703  -0.1121   0.8905   0.0128
  -8.750  -0.3399   0.01192   0.00659  -0.1119   0.8823   0.0136
  -8.500  -0.3139   0.01160   0.00621  -0.1114   0.8716   0.0143
  -8.250  -0.2881   0.01133   0.00585  -0.1109   0.8572   0.0151
  -8.000  -0.2635   0.01112   0.00554  -0.1101   0.8407   0.0159
  -7.750  -0.2404   0.01091   0.00524  -0.1089   0.8261   0.0168
  -7.500  -0.2178   0.01073   0.00499  -0.1077   0.8120   0.0180
  -7.250  -0.1958   0.01059   0.00477  -0.1063   0.7968   0.0192
  -7.000  -0.1747   0.01045   0.00456  -0.1047   0.7799   0.0208
  -6.750  -0.1541   0.01036   0.00438  -0.1030   0.7613   0.0223
  -6.500  -0.1332   0.01027   0.00420  -0.1013   0.7442   0.0235
  -6.250  -0.1144   0.01020   0.00404  -0.0992   0.7216   0.0250
  -6.000  -0.0953   0.01015   0.00390  -0.0972   0.6984   0.0264
  -5.750  -0.0763   0.01013   0.00376  -0.0951   0.6765   0.0276
  -5.500  -0.0556   0.01008   0.00362  -0.0934   0.6603   0.0291
  -5.250  -0.0341   0.01000   0.00349  -0.0919   0.6469   0.0305
  -5.000  -0.0127   0.00995   0.00338  -0.0904   0.6336   0.0322
  -4.750   0.0089   0.00991   0.00327  -0.0889   0.6218   0.0334
  -4.500   0.0318   0.00982   0.00314  -0.0877   0.6119   0.0353
  -4.250   0.0533   0.00977   0.00305  -0.0862   0.5985   0.0375
  -4.000   0.0749   0.00974   0.00296  -0.0847   0.5862   0.0392
  -3.750   0.0977   0.00969   0.00285  -0.0835   0.5750   0.0406
  -3.500   0.1194   0.00963   0.00276  -0.0820   0.5621   0.0434
  -3.250   0.1412   0.00959   0.00268  -0.0806   0.5504   0.0460
  -3.000   0.1620   0.00959   0.00260  -0.0790   0.5337   0.0477
  -2.750   0.1814   0.00957   0.00252  -0.0770   0.5144   0.0508
  -2.500   0.1986   0.00962   0.00247  -0.0746   0.4889   0.0538
  -2.250   0.2169   0.00968   0.00242  -0.0725   0.4682   0.0566
  -2.000   0.2359   0.00971   0.00238  -0.0705   0.4511   0.0604
  -1.500   0.2768   0.00973   0.00231  -0.0672   0.4280   0.0685
  -1.250   0.2972   0.00972   0.00228  -0.0655   0.4194   0.0765
  -1.000   0.3186   0.00968   0.00224  -0.0640   0.4130   0.0862
  -0.750   0.3375   0.00953   0.00221  -0.0621   0.4076   0.1277
  -0.500   0.3577   0.00949   0.00221  -0.0604   0.4027   0.1523
  -0.250   0.3788   0.00943   0.00221  -0.0589   0.3985   0.1737
   0.000   0.3994   0.00939   0.00228  -0.0574   0.3935   0.2151
   0.250   0.4212   0.00947   0.00234  -0.0560   0.3876   0.2300
   0.500   0.4440   0.00952   0.00240  -0.0549   0.3826   0.2391
   0.750   0.4670   0.00959   0.00244  -0.0538   0.3781   0.2447
   1.000   0.4890   0.00966   0.00250  -0.0525   0.3730   0.2485
   1.250   0.5113   0.00974   0.00256  -0.0513   0.3685   0.2531
   1.500   0.5344   0.00982   0.00262  -0.0503   0.3638   0.2579
   1.750   0.5567   0.00989   0.00267  -0.0491   0.3585   0.2603
   2.000   0.5784   0.00999   0.00275  -0.0478   0.3530   0.2643
   2.250   0.6012   0.01006   0.00282  -0.0468   0.3479   0.2673
   2.500   0.6231   0.01016   0.00289  -0.0455   0.3411   0.2701
   2.750   0.6445   0.01027   0.00297  -0.0442   0.3347   0.2711
   3.000   0.6661   0.01038   0.00304  -0.0430   0.3269   0.2721
   3.250   0.6867   0.01050   0.00314  -0.0415   0.3187   0.2743
   3.500   0.7073   0.01063   0.00323  -0.0401   0.3090   0.2757
   3.750   0.7275   0.01079   0.00336  -0.0387   0.2980   0.2782
   4.000   0.7470   0.01097   0.00349  -0.0371   0.2875   0.2804
   4.250   0.7660   0.01117   0.00364  -0.0354   0.2763   0.2824
   4.500   0.7858   0.01135   0.00378  -0.0339   0.2679   0.2835
   4.750   0.8047   0.01156   0.00395  -0.0323   0.2588   0.2847
   5.000   0.8249   0.01173   0.00410  -0.0309   0.2524   0.2855
   5.250   0.8439   0.01194   0.00427  -0.0294   0.2453   0.2871
   5.500   0.8634   0.01211   0.00444  -0.0279   0.2407   0.2888
   5.750   0.8832   0.01227   0.00461  -0.0265   0.2367   0.2904
   6.000   0.9027   0.01246   0.00479  -0.0251   0.2327   0.2923
   6.250   0.9215   0.01268   0.00500  -0.0235   0.2279   0.2942
   6.500   0.9416   0.01285   0.00519  -0.0222   0.2257   0.2962
   6.750   0.9613   0.01303   0.00539  -0.0209   0.2230   0.2982
   7.000   0.9808   0.01322   0.00559  -0.0196   0.2207   0.3000
   7.250   0.9996   0.01344   0.00582  -0.0181   0.2175   0.3023
   7.500   1.0185   0.01365   0.00605  -0.0167   0.2153   0.3056
   7.750   1.0369   0.01389   0.00631  -0.0153   0.2130   0.3095
   8.000   1.0548   0.01414   0.00658  -0.0137   0.2107   0.3131
   8.250   1.0739   0.01434   0.00683  -0.0125   0.2097   0.3206
   8.500   1.0936   0.01453   0.00708  -0.0113   0.2080   0.3282
   8.750   1.1118   0.01472   0.00736  -0.0099   0.2065   0.3610
   9.250   1.3083   0.01484   0.00889  -0.0429   0.1961   0.9931
   9.500   1.3319   0.01521   0.00928  -0.0428   0.1934   0.9968
   9.750   1.3640   0.01555   0.00965  -0.0445   0.1910   0.9986
  10.000   1.3930   0.01597   0.01007  -0.0456   0.1854   0.9996
  10.250   1.4132   0.01644   0.01052  -0.0451   0.1806   1.0000
  10.500   1.4283   0.01679   0.01090  -0.0432   0.1774   1.0000
  10.750   1.4421   0.01721   0.01132  -0.0413   0.1720   1.0000
  11.000   1.4538   0.01777   0.01184  -0.0391   0.1648   1.0000
  11.250   1.4656   0.01832   0.01238  -0.0370   0.1570   1.0000
  11.500   1.4714   0.01921   0.01318  -0.0341   0.1422   1.0000
  11.750   1.4699   0.02052   0.01437  -0.0305   0.1227   1.0000
  12.000   1.4763   0.02147   0.01530  -0.0280   0.1153   1.0000
  12.250   1.4802   0.02261   0.01642  -0.0253   0.1063   1.0000
  12.500   1.4845   0.02379   0.01758  -0.0229   0.0974   1.0000
  12.750   1.4846   0.02529   0.01904  -0.0201   0.0859   1.0000
  13.000   1.4628   0.02836   0.02193  -0.0156   0.0573   1.0000
  13.250   1.4332   0.03238   0.02583  -0.0113   0.0269   1.0000
  13.500   1.4248   0.03507   0.02852  -0.0091   0.0169   1.0000
  13.750   1.4260   0.03709   0.03059  -0.0078   0.0144   1.0000
  14.000   1.4274   0.03917   0.03273  -0.0067   0.0128   1.0000
  14.250   1.4291   0.04130   0.03493  -0.0057   0.0117   1.0000
  14.500   1.4322   0.04338   0.03707  -0.0050   0.0114   1.0000
  14.750   1.4327   0.04578   0.03954  -0.0043   0.0104   1.0000
  15.000   1.4328   0.04829   0.04212  -0.0038   0.0100   1.0000
  15.250   1.4315   0.05100   0.04489  -0.0034   0.0095   1.0000
  15.500   1.4297   0.05383   0.04781  -0.0031   0.0089   1.0000
  15.750   1.4271   0.05682   0.05088  -0.0029   0.0087   1.0000
  16.000   1.4244   0.05992   0.05405  -0.0028   0.0085   1.0000
  16.250   1.4199   0.06326   0.05748  -0.0029   0.0082   1.0000
  16.500   1.4142   0.06684   0.06114  -0.0032   0.0079   1.0000
  16.750   1.4064   0.07078   0.06517  -0.0035   0.0076   1.0000
  17.000   1.3983   0.07485   0.06933  -0.0041   0.0074   1.0000
  17.250   1.3899   0.07899   0.07356  -0.0047   0.0072   1.0000
  17.500   1.3805   0.08333   0.07799  -0.0055   0.0070   1.0000
  17.750   1.3719   0.08763   0.08238  -0.0063   0.0068   1.0000
  18.000   1.3614   0.09222   0.08706  -0.0073   0.0069   1.0000
  18.250   1.3529   0.09657   0.09150  -0.0083   0.0066   1.0000
  18.500   1.3421   0.10129   0.09632  -0.0094   0.0063   1.0000
  18.750   1.3310   0.10612   0.10124  -0.0107   0.0062   1.0000
<< Back to GOE 512 AIRFOIL (goe512-il)

Polar data table (+)

Polar graphs


<< Back to GOE 512 AIRFOIL (goe512-il)