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GOE 497 AIRFOIL (goe497-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 497 AIRFOIL (goe497-il)
Reynolds number: 100,000
Max Cl/Cd: 58.61 at α=7.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe497-il-100000.txt
Download as CSV file: xf-goe497-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 497 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
  ------ -------- --------- --------- -------- -------- --------
  -7.000  -0.3755   0.09739   0.09304  -0.0327   0.9825   0.1624
  -6.750  -0.3473   0.09418   0.08978  -0.0320   0.9782   0.1659
  -6.500  -0.3871   0.06331   0.05844  -0.0773   0.9614   0.1157
  -6.250  -0.3618   0.05943   0.05454  -0.0802   0.9567   0.1168
  -6.000  -0.3401   0.05058   0.04526  -0.0893   0.9513   0.1132
  -5.750  -0.3085   0.04172   0.03553  -0.0993   0.9468   0.1129
  -5.500  -0.2692   0.03689   0.02982  -0.1056   0.9429   0.1169
  -5.250  -0.2318   0.03554   0.02841  -0.1084   0.9390   0.1211
  -5.000  -0.2078   0.03403   0.02658  -0.1089   0.9322   0.1258
  -4.750  -0.1717   0.03233   0.02443  -0.1116   0.9277   0.1326
  -4.500  -0.1291   0.03145   0.02341  -0.1147   0.9240   0.1409
  -4.250  -0.1067   0.03058   0.02236  -0.1144   0.9154   0.1485
  -4.000  -0.0627   0.02977   0.02131  -0.1174   0.9096   0.1617
  -3.750  -0.0330   0.02935   0.02089  -0.1179   0.9005   0.1742
  -3.500   0.0097   0.02872   0.02015  -0.1205   0.8938   0.1920
  -3.250   0.0408   0.02845   0.01986  -0.1212   0.8865   0.2086
  -3.000   0.0716   0.02825   0.01965  -0.1218   0.8797   0.2257
  -2.750   0.1141   0.02793   0.01946  -0.1243   0.8756   0.2460
  -2.500   0.1324   0.02806   0.01957  -0.1229   0.8666   0.2616
  -2.250   0.1698   0.02788   0.01948  -0.1245   0.8612   0.2836
  -2.000   0.2158   0.02755   0.01910  -0.1273   0.8580   0.3117
  -1.750   0.2277   0.02786   0.01942  -0.1249   0.8472   0.3283
  -1.500   0.2697   0.02752   0.01922  -0.1269   0.8431   0.3535
  -1.250   0.2891   0.02773   0.01946  -0.1256   0.8336   0.3724
  -1.000   0.3284   0.02746   0.01915  -0.1272   0.8282   0.3989
  -0.750   0.3760   0.02696   0.01875  -0.1299   0.8252   0.4247
  -0.500   0.3877   0.02736   0.01918  -0.1274   0.8135   0.4409
  -0.250   0.4339   0.02685   0.01868  -0.1299   0.8101   0.4686
   0.000   0.4519   0.02707   0.01897  -0.1282   0.7995   0.4876
   0.250   0.4959   0.02650   0.01844  -0.1303   0.7950   0.5178
   0.500   0.5449   0.02564   0.01769  -0.1330   0.7924   0.5494
   0.750   0.5598   0.02586   0.01801  -0.1307   0.7802   0.5713
   1.000   0.6052   0.02500   0.01726  -0.1328   0.7769   0.6062
   1.250   0.6251   0.02510   0.01749  -0.1313   0.7658   0.6378
   1.500   0.6671   0.02419   0.01679  -0.1326   0.7613   0.6902
   1.750   0.6880   0.02376   0.01675  -0.1306   0.7515   0.7781
   2.000   0.7361   0.02280   0.01587  -0.1333   0.7454   1.0000
   2.250   0.7688   0.02270   0.01562  -0.1338   0.7359   1.0000
   2.500   0.8098   0.02212   0.01492  -0.1351   0.7285   1.0000
   2.750   0.8383   0.02204   0.01476  -0.1347   0.7172   1.0000
   3.000   0.8826   0.02126   0.01386  -0.1363   0.7104   1.0000
   3.250   0.9071   0.02133   0.01389  -0.1353   0.6977   1.0000
   3.500   0.9389   0.02113   0.01362  -0.1353   0.6873   1.0000
   3.750   0.9749   0.02080   0.01321  -0.1359   0.6780   1.0000
   4.000   0.9983   0.02105   0.01346  -0.1349   0.6660   1.0000
   4.250   1.0308   0.02097   0.01332  -0.1352   0.6567   1.0000
   4.500   1.0594   0.02104   0.01336  -0.1349   0.6459   1.0000
   4.750   1.0832   0.02134   0.01368  -0.1340   0.6343   1.0000
   5.000   1.1178   0.02127   0.01353  -0.1346   0.6258   1.0000
   5.250   1.1394   0.02166   0.01398  -0.1333   0.6139   1.0000
   5.500   1.1637   0.02199   0.01433  -0.1325   0.6031   1.0000
   5.750   1.1974   0.02197   0.01423  -0.1330   0.5938   1.0000
   6.000   1.2164   0.02242   0.01478  -0.1314   0.5812   1.0000
   6.250   1.2401   0.02272   0.01511  -0.1304   0.5695   1.0000
   6.500   1.2685   0.02281   0.01517  -0.1301   0.5579   1.0000
   6.750   1.2957   0.02283   0.01516  -0.1294   0.5444   1.0000
   7.000   1.3173   0.02295   0.01527  -0.1279   0.5287   1.0000
   7.250   1.3395   0.02303   0.01530  -0.1264   0.5121   1.0000
   7.500   1.3596   0.02321   0.01546  -0.1247   0.4949   1.0000
   7.750   1.3784   0.02352   0.01575  -0.1229   0.4775   1.0000
   8.000   1.3975   0.02392   0.01613  -0.1211   0.4605   1.0000
   8.250   1.4169   0.02441   0.01659  -0.1195   0.4439   1.0000
   8.500   1.4356   0.02497   0.01712  -0.1179   0.4276   1.0000
   8.750   1.4533   0.02557   0.01772  -0.1161   0.4115   1.0000
   9.000   1.4694   0.02618   0.01832  -0.1141   0.3957   1.0000
   9.250   1.4831   0.02678   0.01894  -0.1118   0.3803   1.0000
   9.500   1.4917   0.02741   0.01965  -0.1087   0.3649   1.0000
   9.750   1.4975   0.02803   0.02036  -0.1051   0.3497   1.0000
  10.000   1.5001   0.02869   0.02108  -0.1011   0.3345   1.0000
  10.250   1.5014   0.02945   0.02187  -0.0972   0.3187   1.0000
  10.500   1.5018   0.03037   0.02276  -0.0933   0.3020   1.0000
  10.750   1.5011   0.03153   0.02385  -0.0896   0.2840   1.0000
  11.000   1.4981   0.03303   0.02531  -0.0860   0.2642   1.0000
  11.250   1.4958   0.03479   0.02697  -0.0827   0.2440   1.0000
  11.500   1.4966   0.03670   0.02867  -0.0800   0.2246   1.0000
  11.750   1.5012   0.03862   0.03040  -0.0778   0.2072   1.0000
  12.000   1.5026   0.04055   0.03238  -0.0754   0.1935   1.0000
  12.250   1.5051   0.04248   0.03438  -0.0733   0.1818   1.0000
  12.500   1.5081   0.04439   0.03630  -0.0714   0.1719   1.0000
  12.750   1.5112   0.04622   0.03806  -0.0698   0.1629   1.0000
  13.000   1.5091   0.04847   0.04049  -0.0680   0.1544   1.0000
  13.250   1.5106   0.05058   0.04256  -0.0666   0.1466   1.0000
  13.500   1.5101   0.05293   0.04500  -0.0652   0.1392   1.0000
  13.750   1.5145   0.05514   0.04721  -0.0641   0.1323   1.0000
  14.000   1.5167   0.05753   0.04967  -0.0631   0.1257   1.0000
  14.250   1.5228   0.05985   0.05199  -0.0622   0.1191   1.0000
  14.500   1.5231   0.06255   0.05481  -0.0613   0.1129   1.0000
  14.750   1.5291   0.06508   0.05734  -0.0605   0.1062   1.0000
  15.000   1.5256   0.06826   0.06067  -0.0598   0.1004   1.0000
  15.250   1.5304   0.07109   0.06349  -0.0592   0.0936   1.0000
  15.500   1.5234   0.07481   0.06742  -0.0588   0.0885   1.0000
  15.750   1.5301   0.07763   0.07019  -0.0583   0.0822   1.0000
  16.000   1.5177   0.08213   0.07498  -0.0584   0.0785   1.0000
  16.250   1.5348   0.08396   0.07659  -0.0578   0.0725   1.0000
  16.500   1.5173   0.08917   0.08219  -0.0584   0.0706   1.0000
  16.750   1.5055   0.09412   0.08742  -0.0593   0.0683   1.0000
  17.000   1.4978   0.09859   0.09207  -0.0602   0.0661   1.0000
  17.250   1.5156   0.10029   0.09360  -0.0595   0.0625   1.0000
  17.500   1.4933   0.10669   0.10036  -0.0617   0.0618   1.0000
  17.750   1.4704   0.11363   0.10763  -0.0646   0.0612   1.0000
  18.000   1.4461   0.12124   0.11555  -0.0683   0.0608   1.0000
  18.250   1.4188   0.12984   0.12445  -0.0731   0.0606   1.0000
  18.500   1.3871   0.13988   0.13478  -0.0792   0.0609   1.0000
  18.750   1.3507   0.15171   0.14684  -0.0870   0.0615   1.0000
  19.000   1.3107   0.16553   0.16085  -0.0963   0.0624   1.0000
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