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GOE 433 AIRFOIL (goe433-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 433 AIRFOIL (goe433-il)
Reynolds number: 200,000
Max Cl/Cd: 75.91 at α=6.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe433-il-200000.txt
Download as CSV file: xf-goe433-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 433 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.500  -0.2476   0.12006   0.11616  -0.0469   1.0000   0.1181
 -11.250  -0.2590   0.11946   0.11564  -0.0441   1.0000   0.1205
 -11.000  -0.6292   0.04004   0.03505  -0.1184   0.9672   0.0998
 -10.750  -0.6111   0.03528   0.02969  -0.1258   0.9591   0.1019
 -10.500  -0.5834   0.03256   0.02667  -0.1296   0.9526   0.1038
 -10.250  -0.5449   0.03167   0.02585  -0.1322   0.9492   0.1058
 -10.000  -0.5178   0.03072   0.02483  -0.1332   0.9411   0.1077
  -9.750  -0.4877   0.02925   0.02316  -0.1352   0.9347   0.1100
  -9.500  -0.4599   0.02774   0.02133  -0.1369   0.9278   0.1124
  -9.250  -0.4351   0.02638   0.01983  -0.1374   0.9190   0.1144
  -9.000  -0.4038   0.02565   0.01913  -0.1381   0.9135   0.1166
  -8.750  -0.3802   0.02499   0.01842  -0.1377   0.9029   0.1187
  -8.500  -0.3519   0.02411   0.01737  -0.1381   0.8958   0.1213
  -8.250  -0.3273   0.02338   0.01640  -0.1380   0.8851   0.1239
  -8.000  -0.3004   0.02235   0.01532  -0.1379   0.8775   0.1265
  -7.750  -0.2748   0.02184   0.01483  -0.1376   0.8672   0.1289
  -7.500  -0.2473   0.02129   0.01419  -0.1374   0.8588   0.1319
  -7.250  -0.2208   0.02080   0.01352  -0.1373   0.8482   0.1353
  -7.000  -0.1937   0.02006   0.01264  -0.1372   0.8394   0.1385
  -6.750  -0.1671   0.01961   0.01223  -0.1369   0.8293   0.1417
  -6.500  -0.1393   0.01921   0.01175  -0.1368   0.8204   0.1456
  -6.250  -0.1114   0.01891   0.01126  -0.1368   0.8109   0.1500
  -6.000  -0.0844   0.01826   0.01064  -0.1367   0.8018   0.1544
  -5.750  -0.0565   0.01794   0.01028  -0.1366   0.7934   0.1594
  -5.500  -0.0281   0.01768   0.00985  -0.1366   0.7838   0.1651
  -5.250  -0.0002   0.01713   0.00935  -0.1365   0.7771   0.1715
  -5.000   0.0278   0.01689   0.00907  -0.1366   0.7678   0.1788
  -4.750   0.0561   0.01645   0.00864  -0.1367   0.7608   0.1861
  -4.500   0.0850   0.01626   0.00840  -0.1368   0.7541   0.1947
  -4.250   0.1132   0.01594   0.00814  -0.1369   0.7463   0.2032
  -4.000   0.1426   0.01578   0.00788  -0.1370   0.7402   0.2125
  -3.750   0.1712   0.01554   0.00770  -0.1371   0.7338   0.2213
  -3.500   0.2002   0.01544   0.00753  -0.1372   0.7266   0.2313
  -3.250   0.2293   0.01520   0.00734  -0.1373   0.7208   0.2412
  -3.000   0.2585   0.01510   0.00720  -0.1374   0.7147   0.2522
  -2.750   0.2873   0.01497   0.00713  -0.1376   0.7079   0.2639
  -2.500   0.3166   0.01480   0.00696  -0.1377   0.7021   0.2769
  -2.250   0.3458   0.01470   0.00685  -0.1378   0.6962   0.2922
  -2.000   0.3746   0.01460   0.00680  -0.1379   0.6893   0.3098
  -1.750   0.4039   0.01448   0.00670  -0.1380   0.6836   0.3298
  -1.500   0.4331   0.01442   0.00670  -0.1381   0.6779   0.3515
  -1.250   0.4614   0.01440   0.00678  -0.1381   0.6709   0.3726
  -1.000   0.4905   0.01440   0.00680  -0.1381   0.6646   0.3928
  -0.750   0.5197   0.01451   0.00691  -0.1381   0.6588   0.4124
  -0.500   0.5479   0.01462   0.00708  -0.1380   0.6519   0.4310
  -0.250   0.5770   0.01473   0.00715  -0.1380   0.6455   0.4489
   0.000   0.6061   0.01492   0.00729  -0.1380   0.6394   0.4661
   0.250   0.6335   0.01505   0.00751  -0.1377   0.6319   0.4810
   0.500   0.6623   0.01518   0.00761  -0.1376   0.6256   0.4961
   0.750   0.6911   0.01539   0.00777  -0.1375   0.6195   0.5113
   1.000   0.7185   0.01553   0.00795  -0.1373   0.6119   0.5258
   1.250   0.7469   0.01562   0.00805  -0.1371   0.6054   0.5384
   1.500   0.7750   0.01581   0.00822  -0.1370   0.5988   0.5518
   1.750   0.8022   0.01595   0.00839  -0.1367   0.5913   0.5657
   2.000   0.8304   0.01604   0.00849  -0.1365   0.5851   0.5788
   2.250   0.8577   0.01621   0.00869  -0.1362   0.5785   0.5930
   2.500   0.8847   0.01631   0.00884  -0.1360   0.5709   0.6074
   2.750   0.9129   0.01637   0.00889  -0.1357   0.5649   0.6195
   3.000   0.9400   0.01651   0.00908  -0.1355   0.5584   0.6307
   3.250   0.9668   0.01660   0.00922  -0.1352   0.5512   0.6421
   3.500   0.9952   0.01660   0.00918  -0.1351   0.5447   0.6523
   3.750   1.0209   0.01665   0.00931  -0.1346   0.5359   0.6635
   4.000   1.0475   0.01657   0.00923  -0.1342   0.5276   0.6745
   4.250   1.0737   0.01660   0.00929  -0.1337   0.5192   0.6870
   4.500   1.0993   0.01658   0.00933  -0.1331   0.5107   0.6992
   4.750   1.1258   0.01662   0.00937  -0.1327   0.5034   0.7129
   5.000   1.1503   0.01665   0.00951  -0.1320   0.4943   0.7292
   5.250   1.1765   0.01668   0.00951  -0.1315   0.4869   0.7487
   5.500   1.1990   0.01673   0.00974  -0.1305   0.4777   0.7745
   5.750   1.2225   0.01671   0.00976  -0.1294   0.4700   0.8192
   6.000   1.2424   0.01654   0.00984  -0.1277   0.4611   1.0000
   6.250   1.2698   0.01679   0.00996  -0.1278   0.4529   1.0000
   6.500   1.2952   0.01710   0.01025  -0.1275   0.4451   1.0000
   6.750   1.3201   0.01739   0.01050  -0.1271   0.4373   1.0000
   7.000   1.3452   0.01773   0.01077  -0.1267   0.4303   1.0000
   7.250   1.3680   0.01805   0.01113  -0.1260   0.4221   1.0000
   7.750   1.4128   0.01876   0.01181  -0.1243   0.4059   1.0000
   8.000   1.4347   0.01915   0.01213  -0.1234   0.3980   1.0000
   8.250   1.4548   0.01955   0.01258  -0.1222   0.3897   1.0000
   8.500   1.4740   0.01996   0.01297  -0.1209   0.3811   1.0000
   8.750   1.4921   0.02041   0.01345  -0.1195   0.3725   1.0000
   9.000   1.5077   0.02088   0.01392  -0.1176   0.3634   1.0000
   9.250   1.5215   0.02139   0.01446  -0.1156   0.3545   1.0000
   9.500   1.5341   0.02199   0.01505  -0.1134   0.3450   1.0000
   9.750   1.5467   0.02264   0.01575  -0.1114   0.3355   1.0000
  10.000   1.5561   0.02345   0.01653  -0.1091   0.3252   1.0000
  10.250   1.5666   0.02429   0.01744  -0.1071   0.3138   1.0000
  10.500   1.5752   0.02529   0.01844  -0.1050   0.3030   1.0000
  10.750   1.5815   0.02649   0.01962  -0.1029   0.2913   1.0000
  11.000   1.5885   0.02776   0.02093  -0.1010   0.2786   1.0000
  11.250   1.5935   0.02925   0.02242  -0.0991   0.2660   1.0000
  11.500   1.5961   0.03099   0.02413  -0.0972   0.2535   1.0000
  11.750   1.5963   0.03299   0.02610  -0.0953   0.2413   1.0000
  12.000   1.5966   0.03510   0.02820  -0.0937   0.2280   1.0000
  12.250   1.5960   0.03739   0.03048  -0.0921   0.2162   1.0000
  12.500   1.5937   0.03988   0.03296  -0.0906   0.2062   1.0000
  12.750   1.5911   0.04251   0.03558  -0.0893   0.1969   1.0000
  13.000   1.5895   0.04515   0.03823  -0.0881   0.1884   1.0000
  13.250   1.5851   0.04815   0.04122  -0.0871   0.1808   1.0000
  13.500   1.5843   0.05090   0.04402  -0.0863   0.1733   1.0000
  13.750   1.5788   0.05422   0.04732  -0.0855   0.1663   1.0000
  14.000   1.5775   0.05717   0.05033  -0.0849   0.1590   1.0000
  14.250   1.5705   0.06081   0.05396  -0.0844   0.1521   1.0000
  14.500   1.5687   0.06397   0.05719  -0.0841   0.1444   1.0000
  14.750   1.5603   0.06790   0.06111  -0.0838   0.1377   1.0000
  15.000   1.5567   0.07141   0.06469  -0.0836   0.1296   1.0000
  15.250   1.5498   0.07535   0.06865  -0.0836   0.1228   1.0000
  15.500   1.5434   0.07928   0.07260  -0.0836   0.1161   1.0000
  15.750   1.5380   0.08312   0.07647  -0.0837   0.1106   1.0000
  16.000   1.5329   0.08698   0.08036  -0.0839   0.1059   1.0000
  16.250   1.5278   0.09083   0.08421  -0.0841   0.1025   1.0000
  16.500   1.5273   0.09410   0.08754  -0.0843   0.0992   1.0000
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