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GOE 534 AIRFOIL (goe534-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 534 AIRFOIL (goe534-il)
Reynolds number: 200,000
Max Cl/Cd: 67.37 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe534-il-200000-n5.txt
Download as CSV file: xf-goe534-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 534 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.500  -0.6935   0.04695   0.04234  -0.0696   1.0000   0.0403
 -11.250  -0.7185   0.03877   0.03393  -0.0780   1.0000   0.0404
 -11.000  -0.7136   0.03437   0.02936  -0.0826   1.0000   0.0408
 -10.750  -0.7033   0.03182   0.02668  -0.0841   1.0000   0.0412
 -10.500  -0.6782   0.02964   0.02435  -0.0871   0.9963   0.0418
 -10.250  -0.6418   0.02759   0.02211  -0.0914   0.9870   0.0427
 -10.000  -0.6075   0.02579   0.02009  -0.0947   0.9772   0.0437
  -9.750  -0.5737   0.02432   0.01847  -0.0973   0.9676   0.0448
  -9.500  -0.5413   0.02341   0.01752  -0.0989   0.9558   0.0459
  -9.250  -0.5075   0.02247   0.01648  -0.1007   0.9439   0.0472
  -9.000  -0.4729   0.02146   0.01532  -0.1026   0.9315   0.0488
  -8.750  -0.4361   0.02071   0.01450  -0.1045   0.9185   0.0503
  -8.500  -0.4002   0.02011   0.01382  -0.1062   0.9030   0.0521
  -8.250  -0.3652   0.01937   0.01293  -0.1076   0.8861   0.0546
  -8.000  -0.3308   0.01904   0.01252  -0.1087   0.8685   0.0570
  -7.750  -0.2992   0.01856   0.01185  -0.1092   0.8508   0.0607
  -7.500  -0.2691   0.01831   0.01146  -0.1093   0.8339   0.0642
  -7.250  -0.2406   0.01801   0.01097  -0.1091   0.8184   0.0678
  -7.000  -0.2130   0.01779   0.01057  -0.1087   0.8032   0.0713
  -6.750  -0.1861   0.01750   0.01011  -0.1082   0.7889   0.0744
  -6.500  -0.1593   0.01729   0.00980  -0.1077   0.7758   0.0771
  -6.250  -0.1324   0.01707   0.00938  -0.1071   0.7628   0.0802
  -6.000  -0.1061   0.01678   0.00899  -0.1066   0.7499   0.0826
  -5.750  -0.0796   0.01657   0.00871  -0.1060   0.7375   0.0852
  -5.500  -0.0530   0.01634   0.00837  -0.1054   0.7246   0.0878
  -5.250  -0.0261   0.01616   0.00800  -0.1048   0.7122   0.0901
  -5.000  -0.0001   0.01583   0.00765  -0.1041   0.6991   0.0924
  -4.750   0.0265   0.01561   0.00740  -0.1035   0.6852   0.0949
  -4.500   0.0532   0.01543   0.00712  -0.1029   0.6717   0.0977
  -4.250   0.0800   0.01530   0.00683  -0.1022   0.6571   0.1001
  -4.000   0.1061   0.01498   0.00652  -0.1016   0.6412   0.1025
  -3.750   0.1326   0.01479   0.00627  -0.1009   0.6252   0.1047
  -3.500   0.1591   0.01462   0.00603  -0.1003   0.6091   0.1068
  -3.250   0.1856   0.01448   0.00578  -0.0995   0.5929   0.1084
  -3.000   0.2120   0.01436   0.00554  -0.0988   0.5776   0.1100
  -2.750   0.2385   0.01427   0.00534  -0.0981   0.5629   0.1114
  -2.500   0.2649   0.01412   0.00514  -0.0975   0.5492   0.1132
  -2.250   0.2913   0.01404   0.00499  -0.0969   0.5366   0.1150
  -2.000   0.3178   0.01400   0.00486  -0.0962   0.5240   0.1172
  -1.750   0.3447   0.01395   0.00475  -0.0956   0.5121   0.1197
  -1.500   0.3713   0.01396   0.00465  -0.0950   0.5015   0.1228
  -1.250   0.3983   0.01389   0.00458  -0.0945   0.4913   0.1274
  -1.000   0.4250   0.01389   0.00452  -0.0939   0.4825   0.1346
  -0.750   0.4522   0.01380   0.00449  -0.0935   0.4736   0.1488
  -0.500   0.4787   0.01373   0.00449  -0.0929   0.4649   0.1782
  -0.250   0.5056   0.01367   0.00453  -0.0925   0.4567   0.2168
   0.000   0.5324   0.01367   0.00459  -0.0920   0.4485   0.2481
   0.250   0.5591   0.01374   0.00466  -0.0914   0.4410   0.2730
   0.500   0.5861   0.01378   0.00474  -0.0909   0.4325   0.2938
   0.750   0.6125   0.01389   0.00482  -0.0903   0.4245   0.3124
   1.000   0.6394   0.01396   0.00493  -0.0898   0.4165   0.3326
   1.250   0.6658   0.01406   0.00504  -0.0892   0.4087   0.3539
   1.500   0.6922   0.01417   0.00517  -0.0886   0.4012   0.3713
   1.750   0.7185   0.01428   0.00530  -0.0880   0.3927   0.3880
   2.000   0.7443   0.01442   0.00542  -0.0873   0.3848   0.4037
   2.250   0.7708   0.01453   0.00555  -0.0867   0.3762   0.4173
   2.500   0.7963   0.01469   0.00568  -0.0860   0.3685   0.4326
   2.750   0.8224   0.01481   0.00585  -0.0854   0.3603   0.4485
   3.000   0.8477   0.01497   0.00600  -0.0847   0.3517   0.4650
   3.250   0.8733   0.01511   0.00617  -0.0840   0.3433   0.4819
   3.500   0.8984   0.01528   0.00635  -0.0833   0.3349   0.4995
   3.750   0.9236   0.01543   0.00653  -0.0826   0.3271   0.5163
   4.000   0.9484   0.01560   0.00672  -0.0819   0.3185   0.5338
   4.250   0.9726   0.01577   0.00691  -0.0810   0.3108   0.5532
   4.500   0.9977   0.01592   0.00713  -0.0803   0.3025   0.5796
   4.750   1.0220   0.01607   0.00736  -0.0796   0.2953   0.6229
   5.250   1.0867   0.01619   0.00789  -0.0814   0.2793   1.0000
   5.500   1.1110   0.01649   0.00817  -0.0806   0.2725   1.0000
   5.750   1.1340   0.01685   0.00846  -0.0797   0.2659   1.0000
   6.000   1.1568   0.01722   0.00878  -0.0787   0.2602   1.0000
   6.250   1.1800   0.01756   0.00912  -0.0778   0.2542   1.0000
   6.500   1.2018   0.01796   0.00947  -0.0768   0.2487   1.0000
   6.750   1.2236   0.01837   0.00984  -0.0757   0.2439   1.0000
   7.000   1.2459   0.01874   0.01023  -0.0747   0.2389   1.0000
   7.250   1.2670   0.01916   0.01062  -0.0736   0.2340   1.0000
   7.500   1.2865   0.01965   0.01106  -0.0722   0.2296   1.0000
   7.750   1.3078   0.02005   0.01150  -0.0711   0.2255   1.0000
   8.000   1.3280   0.02047   0.01195  -0.0699   0.2211   1.0000
   8.250   1.3467   0.02096   0.01241  -0.0685   0.2168   1.0000
   8.500   1.3635   0.02153   0.01294  -0.0669   0.2130   1.0000
   8.750   1.3822   0.02196   0.01344  -0.0655   0.2092   1.0000
   9.000   1.3987   0.02244   0.01397  -0.0637   0.2053   1.0000
   9.250   1.4131   0.02299   0.01452  -0.0617   0.2015   1.0000
   9.500   1.4256   0.02364   0.01515  -0.0596   0.1981   1.0000
   9.750   1.4401   0.02423   0.01579  -0.0578   0.1946   1.0000
  10.000   1.4546   0.02483   0.01646  -0.0560   0.1908   1.0000
  10.250   1.4670   0.02553   0.01719  -0.0542   0.1870   1.0000
  10.500   1.4773   0.02637   0.01803  -0.0522   0.1836   1.0000
  10.750   1.4886   0.02721   0.01892  -0.0505   0.1802   1.0000
  11.000   1.5008   0.02804   0.01983  -0.0490   0.1764   1.0000
  11.250   1.5107   0.02903   0.02087  -0.0475   0.1726   1.0000
  11.500   1.5184   0.03019   0.02205  -0.0459   0.1694   1.0000
  11.750   1.5267   0.03141   0.02332  -0.0446   0.1663   1.0000
  12.000   1.5366   0.03260   0.02460  -0.0434   0.1628   1.0000
  12.250   1.5442   0.03398   0.02605  -0.0423   0.1595   1.0000
  12.500   1.5495   0.03559   0.02770  -0.0413   0.1564   1.0000
  12.750   1.5538   0.03736   0.02950  -0.0404   0.1537   1.0000
  13.000   1.5610   0.03898   0.03123  -0.0397   0.1506   1.0000
  13.250   1.5660   0.04083   0.03318  -0.0390   0.1476   1.0000
  13.500   1.5690   0.04292   0.03533  -0.0385   0.1448   1.0000
  13.750   1.5695   0.04529   0.03773  -0.0381   0.1423   1.0000
  14.000   1.5718   0.04760   0.04012  -0.0378   0.1399   1.0000
  14.250   1.5740   0.04998   0.04262  -0.0376   0.1372   1.0000
  14.500   1.5738   0.05268   0.04541  -0.0376   0.1344   1.0000
  14.750   1.5720   0.05563   0.04842  -0.0378   0.1319   1.0000
  15.000   1.5684   0.05885   0.05168  -0.0382   0.1297   1.0000
  15.250   1.5673   0.06192   0.05486  -0.0386   0.1274   1.0000
  15.500   1.5655   0.06520   0.05826  -0.0391   0.1250   1.0000
  15.750   1.5620   0.06874   0.06190  -0.0399   0.1227   1.0000
  16.000   1.5576   0.07243   0.06566  -0.0408   0.1206   1.0000
  16.250   1.5528   0.07623   0.06950  -0.0417   0.1186   1.0000
  16.500   1.5491   0.07997   0.07332  -0.0427   0.1168   1.0000
  16.750   1.5440   0.08403   0.07753  -0.0439   0.1147   1.0000
  17.000   1.5379   0.08829   0.08191  -0.0453   0.1127   1.0000
  17.250   1.5320   0.09257   0.08627  -0.0468   0.1107   1.0000
  17.500   1.5266   0.09676   0.09052  -0.0482   0.1089   1.0000
  17.750   1.5239   0.10049   0.09425  -0.0495   0.1072   1.0000
  18.000   1.5166   0.10516   0.09906  -0.0513   0.1055   1.0000
  18.250   1.5073   0.11028   0.10433  -0.0535   0.1035   1.0000
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