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GOE 498 AIRFOIL (goe498-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 498 AIRFOIL (goe498-il)
Reynolds number: 100,000
Max Cl/Cd: 53.48 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe498-il-100000-n5.txt
Download as CSV file: xf-goe498-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 498 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.3139   0.10120   0.09561  -0.0624   0.9868   0.0659
 -10.750  -0.3100   0.09532   0.08971  -0.0675   0.9826   0.0666
 -10.250  -0.5126   0.04781   0.04140  -0.1122   0.9451   0.0687
 -10.000  -0.5046   0.04354   0.03678  -0.1174   0.9362   0.0702
  -9.750  -0.4943   0.03993   0.03272  -0.1206   0.9270   0.0718
  -9.500  -0.4707   0.03688   0.02922  -0.1242   0.9220   0.0736
  -9.250  -0.4531   0.03576   0.02809  -0.1236   0.9126   0.0748
  -9.000  -0.4229   0.03430   0.02650  -0.1255   0.9081   0.0768
  -8.750  -0.3897   0.03243   0.02433  -0.1284   0.9049   0.0796
  -8.500  -0.3753   0.03117   0.02282  -0.1272   0.8941   0.0814
  -8.250  -0.3427   0.03013   0.02183  -0.1286   0.8898   0.0835
  -8.000  -0.3066   0.02893   0.02051  -0.1309   0.8866   0.0865
  -7.750  -0.2893   0.02803   0.01939  -0.1296   0.8764   0.0890
  -7.500  -0.2581   0.02712   0.01850  -0.1307   0.8712   0.0918
  -7.000  -0.2027   0.02556   0.01672  -0.1313   0.8582   0.0986
  -6.750  -0.1731   0.02487   0.01608  -0.1319   0.8522   0.1018
  -6.500  -0.1382   0.02414   0.01528  -0.1333   0.8482   0.1064
  -6.250  -0.1169   0.02366   0.01475  -0.1323   0.8391   0.1103
  -6.000  -0.0872   0.02313   0.01421  -0.1327   0.8328   0.1149
  -5.750  -0.0520   0.02248   0.01348  -0.1341   0.8286   0.1211
  -5.500  -0.0310   0.02217   0.01317  -0.1329   0.8193   0.1263
  -5.250  -0.0003   0.02166   0.01260  -0.1334   0.8133   0.1336
  -5.000   0.0356   0.02110   0.01198  -0.1347   0.8091   0.1434
  -4.750   0.0558   0.02083   0.01174  -0.1334   0.7994   0.1515
  -4.500   0.0881   0.02035   0.01124  -0.1341   0.7937   0.1641
  -4.250   0.1195   0.01995   0.01081  -0.1347   0.7881   0.1784
  -4.000   0.1444   0.01973   0.01057  -0.1341   0.7797   0.1926
  -3.750   0.1779   0.01939   0.01024  -0.1350   0.7741   0.2086
  -3.500   0.2060   0.01923   0.01009  -0.1349   0.7671   0.2233
  -3.250   0.2340   0.01909   0.00996  -0.1348   0.7597   0.2378
  -3.000   0.2682   0.01887   0.00969  -0.1356   0.7543   0.2535
  -2.750   0.2939   0.01883   0.00962  -0.1351   0.7463   0.2676
  -2.500   0.3234   0.01875   0.00949  -0.1352   0.7391   0.2844
  -2.250   0.3579   0.01859   0.00928  -0.1361   0.7338   0.3019
  -2.000   0.3805   0.01864   0.00939  -0.1350   0.7249   0.3164
  -1.750   0.4106   0.01856   0.00929  -0.1351   0.7178   0.3333
  -1.500   0.4412   0.01849   0.00916  -0.1353   0.7111   0.3493
  -1.250   0.4652   0.01851   0.00919  -0.1344   0.7017   0.3629
  -1.000   0.4971   0.01839   0.00902  -0.1348   0.6945   0.3770
  -0.750   0.5204   0.01844   0.00906  -0.1338   0.6850   0.3904
  -0.500   0.5485   0.01839   0.00901  -0.1335   0.6768   0.4034
  -0.250   0.5764   0.01838   0.00899  -0.1333   0.6693   0.4167
   0.000   0.6003   0.01845   0.00907  -0.1324   0.6606   0.4307
   0.250   0.6299   0.01842   0.00903  -0.1324   0.6539   0.4458
   0.500   0.6526   0.01852   0.00919  -0.1313   0.6456   0.4609
   0.750   0.6785   0.01858   0.00925  -0.1306   0.6378   0.4788
   1.000   0.7069   0.01860   0.00928  -0.1305   0.6314   0.4998
   1.250   0.7283   0.01875   0.00952  -0.1291   0.6228   0.5211
   1.500   0.7557   0.01879   0.00957  -0.1287   0.6158   0.5438
   1.750   0.7799   0.01889   0.00972  -0.1279   0.6079   0.5655
   2.000   0.8041   0.01896   0.00982  -0.1270   0.5993   0.5871
   2.250   0.8307   0.01898   0.00985  -0.1265   0.5917   0.6104
   2.500   0.8522   0.01908   0.01004  -0.1251   0.5824   0.6347
   2.750   0.8800   0.01904   0.01001  -0.1248   0.5752   0.6642
   3.000   0.8987   0.01914   0.01027  -0.1229   0.5657   0.6982
   3.250   0.9225   0.01904   0.01029  -0.1217   0.5578   0.7508
   3.500   0.9478   0.01886   0.01042  -0.1209   0.5481   1.0000
   3.750   0.9735   0.01906   0.01049  -0.1204   0.5393   1.0000
   4.000   0.9952   0.01935   0.01072  -0.1193   0.5298   1.0000
   4.250   1.0191   0.01960   0.01089  -0.1186   0.5212   1.0000
   4.500   1.0416   0.01990   0.01113  -0.1176   0.5129   1.0000
   4.750   1.0633   0.02021   0.01141  -0.1165   0.5046   1.0000
   5.000   1.0881   0.02049   0.01160  -0.1159   0.4972   1.0000
   5.250   1.1063   0.02087   0.01201  -0.1142   0.4880   1.0000
   5.500   1.1306   0.02114   0.01217  -0.1135   0.4804   1.0000
   5.750   1.1470   0.02156   0.01264  -0.1116   0.4712   1.0000
   6.000   1.1681   0.02188   0.01290  -0.1104   0.4632   1.0000
   6.250   1.1845   0.02229   0.01333  -0.1085   0.4548   1.0000
   6.500   1.2019   0.02267   0.01368  -0.1067   0.4462   1.0000
   6.750   1.2180   0.02310   0.01410  -0.1048   0.4375   1.0000
   7.000   1.2334   0.02354   0.01454  -0.1028   0.4284   1.0000
   7.250   1.2495   0.02401   0.01499  -0.1009   0.4201   1.0000
   7.500   1.2643   0.02453   0.01554  -0.0989   0.4119   1.0000
   7.750   1.2820   0.02500   0.01598  -0.0974   0.4048   1.0000
   8.000   1.2948   0.02563   0.01668  -0.0953   0.3967   1.0000
   8.250   1.3116   0.02615   0.01716  -0.0937   0.3896   1.0000
   8.500   1.3237   0.02685   0.01794  -0.0916   0.3816   1.0000
   8.750   1.3377   0.02749   0.01858  -0.0898   0.3740   1.0000
   9.000   1.3510   0.02820   0.01931  -0.0879   0.3666   1.0000
   9.250   1.3620   0.02900   0.02018  -0.0859   0.3585   1.0000
   9.500   1.3758   0.02972   0.02086  -0.0842   0.3511   1.0000
   9.750   1.3830   0.03073   0.02197  -0.0819   0.3421   1.0000
  10.000   1.3943   0.03157   0.02275  -0.0800   0.3336   1.0000
  10.250   1.3984   0.03281   0.02409  -0.0777   0.3234   1.0000
  10.500   1.4055   0.03392   0.02518  -0.0756   0.3137   1.0000
  10.750   1.4083   0.03534   0.02666  -0.0734   0.3030   1.0000
  11.000   1.4126   0.03677   0.02811  -0.0714   0.2931   1.0000
  11.250   1.4159   0.03830   0.02965  -0.0695   0.2830   1.0000
  11.500   1.4182   0.04003   0.03147  -0.0678   0.2731   1.0000
  11.750   1.4212   0.04173   0.03314  -0.0662   0.2637   1.0000
  12.000   1.4213   0.04380   0.03531  -0.0647   0.2535   1.0000
  12.250   1.4216   0.04591   0.03745  -0.0633   0.2438   1.0000
  12.500   1.4212   0.04817   0.03970  -0.0621   0.2343   1.0000
  12.750   1.4209   0.05058   0.04217  -0.0610   0.2251   1.0000
  13.000   1.4204   0.05303   0.04461  -0.0601   0.2170   1.0000
  13.250   1.4197   0.05566   0.04730  -0.0594   0.2089   1.0000
  13.500   1.4193   0.05830   0.04993  -0.0588   0.2019   1.0000
  13.750   1.4189   0.06105   0.05275  -0.0583   0.1952   1.0000
  14.000   1.4186   0.06378   0.05543  -0.0578   0.1893   1.0000
  14.250   1.4183   0.06672   0.05850  -0.0576   0.1833   1.0000
  14.500   1.4175   0.06970   0.06148  -0.0575   0.1776   1.0000
  14.750   1.4173   0.07266   0.06448  -0.0574   0.1721   1.0000
  15.000   1.4154   0.07598   0.06790  -0.0575   0.1663   1.0000
  15.250   1.4153   0.07896   0.07084  -0.0576   0.1607   1.0000
  15.500   1.4123   0.08263   0.07466  -0.0580   0.1552   1.0000
  15.750   1.4087   0.08636   0.07849  -0.0586   0.1493   1.0000
  16.000   1.4062   0.08993   0.08210  -0.0591   0.1436   1.0000
  16.250   1.3991   0.09446   0.08683  -0.0602   0.1371   1.0000
  16.500   1.3941   0.09858   0.09099  -0.0613   0.1312   1.0000
  16.750   1.3857   0.10352   0.09613  -0.0628   0.1241   1.0000
  17.000   1.3790   0.10816   0.10085  -0.0643   0.1178   1.0000
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