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GOE 464 AIRFOIL (goe464-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 464 AIRFOIL (goe464-il)
Reynolds number: 500,000
Max Cl/Cd: 164.88 at α=2°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe464-il-500000.txt
Download as CSV file: xf-goe464-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 464 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.500  -0.1984   0.13050   0.12824  -0.0289   1.0000   0.0153
 -11.250  -0.1939   0.12824   0.12601  -0.0294   1.0000   0.0154
 -10.750  -0.1886   0.12347   0.12132  -0.0289   1.0000   0.0155
 -10.500  -0.1738   0.12018   0.11804  -0.0311   0.9986   0.0157
 -10.250  -0.1549   0.11680   0.11467  -0.0346   0.9925   0.0159
 -10.000  -0.1372   0.11366   0.11151  -0.0379   0.9854   0.0164
  -9.750  -0.1200   0.11046   0.10832  -0.0411   0.9766   0.0169
  -9.500  -0.0999   0.10701   0.10486  -0.0452   0.9691   0.0175
  -9.250  -0.0779   0.10325   0.10108  -0.0503   0.9594   0.0185
  -9.000  -0.0501   0.09934   0.09714  -0.0582   0.9515   0.0187
  -8.750  -0.0198   0.09497   0.09273  -0.0663   0.9422   0.0188
  -8.500   0.0089   0.09060   0.08832  -0.0708   0.9343   0.0190
  -8.250   0.0390   0.08714   0.08480  -0.0765   0.9237   0.0194
  -8.000   0.0637   0.08424   0.08183  -0.0810   0.9107   0.0200
  -7.750   0.0809   0.08172   0.07924  -0.0837   0.8974   0.0209
  -7.500   0.0923   0.07949   0.07694  -0.0851   0.8850   0.0219
  -7.250   0.0982   0.07782   0.07523  -0.0869   0.8727   0.0224
  -7.000   0.1087   0.07594   0.07332  -0.0897   0.8625   0.0225
  -6.750   0.1208   0.07293   0.07026  -0.0888   0.8548   0.0228
  -6.500   0.1337   0.07098   0.06831  -0.0891   0.8465   0.0230
  -6.250   0.1477   0.06920   0.06649  -0.0899   0.8379   0.0236
  -6.000   0.1623   0.06727   0.06454  -0.0911   0.8293   0.0243
  -5.750   0.1781   0.06519   0.06242  -0.0927   0.8204   0.0250
  -5.500   0.2019   0.06254   0.05972  -0.0988   0.8111   0.0266
  -5.250   0.2183   0.05952   0.05666  -0.1004   0.8023   0.0270
  -5.000   0.2347   0.05760   0.05473  -0.1006   0.7927   0.0273
  -4.750   0.2540   0.05586   0.05293  -0.1017   0.7823   0.0281
  -4.500   0.2755   0.05388   0.05092  -0.1036   0.7697   0.0292
  -4.250   0.3103   0.05036   0.04732  -0.1108   0.7565   0.0319
  -4.000   0.3274   0.04874   0.04566  -0.1104   0.7405   0.0325
  -3.750   0.3502   0.04710   0.04394  -0.1117   0.7206   0.0337
  -3.250   0.4077   0.04254   0.03907  -0.1180   0.6764   0.0380
  -3.000   0.4319   0.04125   0.03765  -0.1190   0.6591   0.0399
  -2.750   0.4657   0.03898   0.03523  -0.1228   0.6458   0.0439
  -2.500   0.4909   0.03781   0.03395  -0.1237   0.6338   0.0458
  -2.250   0.5282   0.03557   0.03157  -0.1279   0.6233   0.0498
  -2.000   0.5529   0.03450   0.03040  -0.1284   0.6133   0.0514
  -1.750   0.5938   0.03246   0.02823  -0.1327   0.6036   0.0558
  -1.500   0.6188   0.03115   0.02683  -0.1331   0.5950   0.0566
  -1.250   0.6933   0.01836   0.01309  -0.1469   0.5898   0.0438
  -1.000   0.7192   0.01847   0.01316  -0.1463   0.5806   0.0450
  -0.750   0.7460   0.01835   0.01303  -0.1460   0.5713   0.0466
  -0.500   0.7730   0.01794   0.01250  -0.1458   0.5616   0.0493
  -0.250   0.7985   0.01821   0.01281  -0.1452   0.5508   0.0506
   0.000   0.8259   0.01773   0.01221  -0.1450   0.5408   0.0553
   0.250   0.8513   0.01794   0.01240  -0.1444   0.5295   0.0583
   0.500   0.8792   0.01781   0.01217  -0.1441   0.5182   0.0689
   0.750   0.9045   0.01821   0.01253  -0.1434   0.5063   0.0755
   1.000   0.9278   0.01862   0.01291  -0.1426   0.4934   0.0833
   1.250   0.9596   0.01954   0.01359  -0.1421   0.4807   0.0891
   1.500   0.9840   0.01845   0.01242  -0.1420   0.4698   0.0897
   1.750   1.0075   0.01792   0.01181  -0.1416   0.4593   0.0902
   2.000   1.0074   0.00611   0.00016  -0.1358   0.4402   0.0914
   2.250   1.0570   0.01730   0.01107  -0.1408   0.4385   0.0921
   2.500   1.0820   0.01714   0.01081  -0.1403   0.4275   0.0936
   2.750   1.1085   0.01707   0.01065  -0.1398   0.4175   0.0959
   3.000   1.1368   0.01778   0.01111  -0.1390   0.4083   0.0972
   3.250   1.1632   0.01764   0.01089  -0.1385   0.4006   0.0973
   3.500   1.1875   0.01706   0.01023  -0.1380   0.3932   0.0976
   3.750   1.2123   0.01655   0.00972  -0.1377   0.3866   0.0980
   4.000   1.2367   0.01628   0.00942  -0.1372   0.3797   0.0983
   4.250   1.2610   0.01614   0.00922  -0.1366   0.3735   0.0987
   4.500   1.2861   0.01597   0.00906  -0.1361   0.3672   0.0993
   4.750   1.3101   0.01593   0.00896  -0.1355   0.3608   0.1002
   5.000   1.3349   0.01588   0.00890  -0.1349   0.3552   0.1015
   5.250   1.3599   0.01586   0.00886  -0.1343   0.3495   0.1034
   5.500   1.3853   0.01649   0.00932  -0.1332   0.3439   0.1060
   5.750   1.4091   0.01594   0.00880  -0.1327   0.3389   0.1069
   6.000   1.4332   0.01582   0.00872  -0.1322   0.3334   0.1079
   6.250   1.4562   0.01588   0.00876  -0.1314   0.3276   0.1093
   6.500   1.4799   0.01593   0.00882  -0.1306   0.3219   0.1117
   6.750   1.5041   0.01607   0.00891  -0.1297   0.3158   0.1163
   7.000   1.5259   0.01612   0.00895  -0.1288   0.3098   0.1177
   7.250   1.5493   0.01616   0.00905  -0.1281   0.3043   0.1200
   7.750   1.5929   0.01648   0.00935  -0.1261   0.2918   0.1296
   8.250   1.6351   0.01683   0.00973  -0.1239   0.2767   0.1435
   8.500   1.6568   0.01695   0.00991  -0.1229   0.2685   0.1554
   9.500   1.7243   0.01813   0.01109  -0.1161   0.2262   0.2332
   9.750   1.7359   0.01859   0.01151  -0.1135   0.2142   0.2402
  10.000   1.7492   0.01913   0.01203  -0.1111   0.2029   0.2257
  10.250   1.7622   0.01977   0.01255  -0.1084   0.1935   0.1472
  10.750   1.7841   0.02105   0.01382  -0.1036   0.1779   0.1340
  11.000   1.7925   0.02186   0.01462  -0.1010   0.1712   0.1309
  11.250   1.8039   0.02256   0.01536  -0.0989   0.1659   0.1286
  11.500   1.8131   0.02342   0.01625  -0.0967   0.1600   0.1288
  11.750   1.8196   0.02450   0.01734  -0.0943   0.1546   0.1288
  12.000   1.8317   0.02529   0.01821  -0.0927   0.1502   0.1289
  12.250   1.8389   0.02643   0.01938  -0.0907   0.1446   0.1293
  12.500   1.8452   0.02769   0.02067  -0.0887   0.1394   0.1295
  12.750   1.8548   0.02876   0.02182  -0.0872   0.1343   0.1323
  13.000   1.8595   0.03025   0.02334  -0.0853   0.1293   0.1336
  13.250   1.8655   0.03169   0.02484  -0.0837   0.1248   0.1342
  13.500   1.8719   0.03316   0.02635  -0.0823   0.1192   0.1347
  13.750   1.8719   0.03525   0.02845  -0.0806   0.1134   0.1353
  14.000   1.8769   0.03697   0.03023  -0.0794   0.1068   0.1367
  14.250   1.8744   0.03950   0.03276  -0.0780   0.1000   0.1372
  14.500   1.8727   0.04208   0.03536  -0.0770   0.0909   0.1384
  14.750   1.8656   0.04542   0.03869  -0.0761   0.0808   0.1401
  15.000   1.8543   0.04945   0.04271  -0.0756   0.0705   0.1414
  15.250   1.8394   0.05419   0.04744  -0.0755   0.0609   0.1424
  15.500   1.8250   0.05909   0.05237  -0.0757   0.0533   0.1436
  15.750   1.8086   0.06447   0.05778  -0.0762   0.0460   0.1441
  16.000   1.7879   0.07067   0.06401  -0.0772   0.0359   0.1452
  16.250   1.7622   0.07790   0.07125  -0.0789   0.0249   0.1446
  16.500   1.7419   0.08460   0.07803  -0.0806   0.0214   0.1454
  16.750   1.7233   0.09131   0.08484  -0.0826   0.0193   0.1461
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