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

GOE 460 AIRFOIL (goe460-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 460 AIRFOIL (goe460-il)
Reynolds number: 100,000
Max Cl/Cd: 39.84 at α=7°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe460-il-100000.txt
Download as CSV file: xf-goe460-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 460 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
  ------ -------- --------- --------- -------- -------- --------
 -17.500  -0.4740   0.17853   0.17208  -0.0215   1.0000   0.1817
 -17.250  -0.9007   0.08888   0.08219  -0.0653   1.0000   0.1382
 -17.000  -0.9645   0.07792   0.07099  -0.0689   1.0000   0.1391
 -16.500  -0.9631   0.07321   0.06626  -0.0688   1.0000   0.1467
 -16.250  -1.0241   0.06468   0.05740  -0.0699   1.0000   0.1479
 -16.000  -1.0688   0.05888   0.05127  -0.0692   1.0000   0.1496
 -15.750  -1.0271   0.06023   0.05292  -0.0686   1.0000   0.1559
 -15.500  -1.0478   0.05676   0.04930  -0.0675   1.0000   0.1595
 -15.250  -1.0830   0.05262   0.04487  -0.0653   1.0000   0.1624
 -15.000  -1.0650   0.05212   0.04452  -0.0644   1.0000   0.1682
 -14.750  -1.0731   0.05027   0.04259  -0.0624   1.0000   0.1729
 -14.500  -1.1029   0.04735   0.03942  -0.0589   1.0000   0.1764
 -14.250  -1.0897   0.04664   0.03882  -0.0576   1.0000   0.1824
 -14.000  -1.0945   0.04536   0.03750  -0.0549   1.0000   0.1875
 -13.750  -1.1206   0.04335   0.03526  -0.0500   1.0000   0.1913
 -13.500  -1.1108   0.04249   0.03447  -0.0482   1.0000   0.1971
 -13.250  -1.1098   0.04166   0.03365  -0.0452   1.0000   0.2025
 -13.000  -1.1308   0.04032   0.03211  -0.0396   1.0000   0.2065
 -12.750  -1.1348   0.03926   0.03101  -0.0357   1.0000   0.2115
 -12.500  -1.1209   0.03875   0.03061  -0.0339   1.0000   0.2178
 -12.250  -1.1379   0.03785   0.02958  -0.0278   1.0000   0.2220
 -12.000  -1.1667   0.03711   0.02864  -0.0194   1.0000   0.2251
 -11.750  -1.1352   0.03642   0.02819  -0.0203   1.0000   0.2331
 -11.500  -1.1483   0.03584   0.02754  -0.0141   1.0000   0.2377
 -11.250  -1.1730   0.03525   0.02678  -0.0059   1.0000   0.2414
 -11.000  -1.1542   0.03455   0.02624  -0.0048   1.0000   0.2487
 -10.750  -1.1586   0.03400   0.02565   0.0002   1.0000   0.2548
 -10.500  -1.1781   0.03333   0.02476   0.0076   1.0000   0.2597
 -10.250  -1.1562   0.03279   0.02447   0.0083   1.0000   0.2681
 -10.000  -1.1646   0.03224   0.02380   0.0139   1.0000   0.2749
  -9.750  -1.1575   0.03172   0.02337   0.0170   1.0000   0.2830
  -9.500  -1.1576   0.03130   0.02293   0.0214   1.0000   0.2911
  -9.250  -1.1546   0.03077   0.02239   0.0252   1.0000   0.2991
  -9.000  -1.1479   0.03043   0.02209   0.0285   1.0000   0.3076
  -8.750  -1.1466   0.02989   0.02146   0.0325   1.0000   0.3156
  -8.500  -1.1343   0.02957   0.02124   0.0349   1.0000   0.3238
  -8.250  -1.1358   0.02904   0.02049   0.0394   1.0000   0.3313
  -8.000  -1.1170   0.02868   0.02032   0.0406   1.0000   0.3386
  -7.750  -1.1107   0.02826   0.01980   0.0439   1.0000   0.3464
  -7.500  -1.0993   0.02785   0.01941   0.0462   1.0000   0.3537
  -7.250  -1.0883   0.02755   0.01913   0.0487   1.0000   0.3616
  -7.000  -1.0811   0.02714   0.01863   0.0517   1.0000   0.3697
  -6.750  -1.0390   0.02723   0.01879   0.0482   0.9926   0.3814
  -6.500  -1.0010   0.02711   0.01869   0.0455   0.9838   0.3926
  -6.250  -0.9663   0.02704   0.01851   0.0434   0.9748   0.4058
  -6.000  -0.9254   0.02699   0.01860   0.0404   0.9663   0.4185
  -5.750  -0.8939   0.02685   0.01853   0.0392   0.9566   0.4324
  -5.500  -0.8535   0.02689   0.01863   0.0364   0.9487   0.4499
  -5.250  -0.8308   0.02671   0.01848   0.0370   0.9372   0.4661
  -5.000  -0.7935   0.02672   0.01856   0.0350   0.9291   0.4850
  -4.750  -0.7687   0.02661   0.01848   0.0354   0.9181   0.5027
  -4.500  -0.7386   0.02661   0.01852   0.0349   0.9088   0.5214
  -4.250  -0.7070   0.02658   0.01856   0.0343   0.8992   0.5397
  -4.000  -0.6736   0.02661   0.01869   0.0333   0.8905   0.5564
  -3.750  -0.6405   0.02657   0.01872   0.0325   0.8812   0.5723
  -3.500  -0.5901   0.02647   0.01866   0.0286   0.8764   0.5896
  -3.250  -0.5811   0.02637   0.01855   0.0319   0.8628   0.6028
  -3.000  -0.5343   0.02617   0.01834   0.0287   0.8579   0.6196
  -2.750  -0.5138   0.02636   0.01865   0.0302   0.8454   0.6306
  -2.500  -0.4657   0.02618   0.01850   0.0269   0.8400   0.6457
  -2.250  -0.4570   0.02619   0.01848   0.0304   0.8275   0.6595
  -2.000  -0.4014   0.02624   0.01864   0.0260   0.8222   0.6722
  -1.750  -0.3414   0.02606   0.01850   0.0209   0.8191   0.6857
  -1.500  -0.3456   0.02613   0.01854   0.0265   0.8043   0.6988
  -1.250  -0.2715   0.02612   0.01863   0.0192   0.8015   0.7090
  -1.000  -0.2079   0.02587   0.01837   0.0134   0.7988   0.7218
  -0.750  -0.2008   0.02624   0.01879   0.0174   0.7847   0.7331
  -0.500  -0.1221   0.02631   0.01890   0.0095   0.7815   0.7445
  -0.250  -0.0559   0.02608   0.01866   0.0039   0.7782   0.7589
   0.000   0.0003   0.02678   0.01943   0.0000   0.7653   0.7653
   0.250   0.1030   0.02640   0.01899  -0.0116   0.7592   0.7713
   0.500   0.1223   0.02629   0.01888  -0.0095   0.7444   0.7815
   0.750   0.2006   0.02624   0.01878  -0.0173   0.7330   0.7847
   1.000   0.2080   0.02586   0.01837  -0.0134   0.7218   0.7988
   1.250   0.2715   0.02611   0.01862  -0.0192   0.7090   0.8015
   1.500   0.3458   0.02613   0.01854  -0.0266   0.6988   0.8043
   1.750   0.3414   0.02605   0.01849  -0.0209   0.6856   0.8191
   2.000   0.4016   0.02624   0.01864  -0.0260   0.6722   0.8222
   2.500   0.4661   0.02619   0.01852  -0.0270   0.6458   0.8400
   2.750   0.5139   0.02636   0.01865  -0.0302   0.6307   0.8454
   3.000   0.5344   0.02617   0.01834  -0.0288   0.6196   0.8579
   3.250   0.5810   0.02637   0.01855  -0.0319   0.6029   0.8628
   3.500   0.5898   0.02646   0.01866  -0.0285   0.5896   0.8764
   3.750   0.6403   0.02656   0.01871  -0.0324   0.5723   0.8812
   4.000   0.6736   0.02661   0.01868  -0.0333   0.5566   0.8906
   4.250   0.7071   0.02658   0.01855  -0.0343   0.5397   0.8993
   4.500   0.7384   0.02660   0.01851  -0.0349   0.5214   0.9089
   4.750   0.7685   0.02661   0.01848  -0.0354   0.5028   0.9181
   5.000   0.7932   0.02673   0.01857  -0.0350   0.4851   0.9291
   5.250   0.8307   0.02670   0.01847  -0.0370   0.4661   0.9373
   5.500   0.8536   0.02688   0.01861  -0.0365   0.4499   0.9487
   5.750   0.8940   0.02685   0.01853  -0.0392   0.4323   0.9567
   6.000   0.9257   0.02698   0.01859  -0.0405   0.4185   0.9664
   6.250   0.9662   0.02703   0.01851  -0.0434   0.4058   0.9749
   6.500   1.0012   0.02710   0.01868  -0.0456   0.3926   0.9839
   6.750   1.0389   0.02722   0.01879  -0.0482   0.3813   0.9926
   7.000   1.0809   0.02713   0.01862  -0.0516   0.3697   1.0000
   7.250   1.0881   0.02753   0.01911  -0.0486   0.3616   1.0000
   7.500   1.0992   0.02784   0.01939  -0.0462   0.3537   1.0000
   7.750   1.1105   0.02825   0.01979  -0.0439   0.3464   1.0000
   8.000   1.1169   0.02867   0.02031  -0.0406   0.3387   1.0000
   8.250   1.1357   0.02903   0.02048  -0.0394   0.3313   1.0000
   8.500   1.1342   0.02957   0.02123  -0.0349   0.3238   1.0000
   8.750   1.1466   0.02987   0.02144  -0.0326   0.3155   1.0000
   9.000   1.1479   0.03042   0.02208  -0.0285   0.3076   1.0000
   9.250   1.1546   0.03076   0.02238  -0.0252   0.2990   1.0000
   9.500   1.1573   0.03129   0.02292  -0.0213   0.2910   1.0000
   9.750   1.1574   0.03171   0.02335  -0.0170   0.2829   1.0000
  10.000   1.1647   0.03223   0.02379  -0.0139   0.2750   1.0000
  10.250   1.1561   0.03278   0.02445  -0.0082   0.2681   1.0000
  10.500   1.1781   0.03333   0.02476  -0.0076   0.2597   1.0000
  10.750   1.1586   0.03399   0.02564  -0.0002   0.2547   1.0000
  11.000   1.1543   0.03454   0.02622   0.0048   0.2487   1.0000
  11.250   1.1731   0.03524   0.02676   0.0059   0.2414   1.0000
  11.500   1.1483   0.03583   0.02752   0.0141   0.2377   1.0000
  11.750   1.1352   0.03640   0.02816   0.0203   0.2330   1.0000
  12.000   1.1665   0.03710   0.02863   0.0195   0.2250   1.0000
  12.250   1.1381   0.03785   0.02958   0.0278   0.2220   1.0000
  12.500   1.1210   0.03873   0.03059   0.0339   0.2177   1.0000
  12.750   1.1368   0.03920   0.03093   0.0355   0.2112   1.0000
  13.000   1.1315   0.04032   0.03211   0.0395   0.2065   1.0000
  13.250   1.1102   0.04164   0.03362   0.0452   0.2025   1.0000
  13.500   1.1121   0.04245   0.03442   0.0480   0.1970   1.0000
  13.750   1.1208   0.04335   0.03525   0.0500   0.1912   1.0000
  14.000   1.0951   0.04533   0.03746   0.0548   0.1874   1.0000
  14.250   1.0909   0.04660   0.03877   0.0575   0.1823   1.0000
  14.500   1.1028   0.04736   0.03943   0.0588   0.1763   1.0000
  14.750   1.0741   0.05024   0.04256   0.0623   0.1728   1.0000
  15.000   1.0668   0.05206   0.04446   0.0643   0.1681   1.0000
  15.250   1.0840   0.05259   0.04485   0.0652   0.1624   1.0000
  15.500   1.0490   0.05673   0.04926   0.0673   0.1594   1.0000
  15.750   1.0291   0.06015   0.05283   0.0684   0.1558   1.0000
  16.000   1.0689   0.05892   0.05132   0.0691   0.1496   1.0000
  16.250   1.0251   0.06468   0.05740   0.0697   0.1478   1.0000
  16.500   0.9650   0.07312   0.06617   0.0686   0.1465   1.0000
  17.000   1.0166   0.07257   0.06538   0.0705   0.1372   1.0000
  17.250   0.9304   0.08518   0.07839   0.0668   0.1373   1.0000
  17.500   0.4757   0.17877   0.17232   0.0212   0.1817   1.0000
<< Back to GOE 460 AIRFOIL (goe460-il)

Polar data table (+)

Polar graphs


<< Back to GOE 460 AIRFOIL (goe460-il)