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GOE 190 (MVA MK.18) AIRFOIL (goe190-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 190 (MVA MK.18) AIRFOIL (goe190-il)
Reynolds number: 100,000
Max Cl/Cd: 52.5 at α=9°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe190-il-100000.txt
Download as CSV file: xf-goe190-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 190 (MVA MK.18) 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
  ------ -------- --------- --------- -------- -------- --------
  -7.500  -0.3016   0.09954   0.09502  -0.0226   1.0000   0.1616
  -7.250  -0.3334   0.09996   0.09560  -0.0207   1.0000   0.1665
  -7.000  -0.3859   0.10179   0.09765  -0.0192   1.0000   0.1676
  -6.750  -0.3555   0.09660   0.09244  -0.0151   1.0000   0.1703
  -6.500  -0.3502   0.09489   0.09077  -0.0121   1.0000   0.1744
  -6.250  -0.3682   0.09444   0.09041  -0.0089   1.0000   0.1775
  -6.000  -0.3687   0.05614   0.05169  -0.0686   0.9866   0.1097
  -5.750  -0.3042   0.03653   0.03008  -0.0980   0.9843   0.0957
  -5.500  -0.2644   0.03329   0.02651  -0.1025   0.9777   0.0977
  -5.250  -0.2207   0.03116   0.02404  -0.1067   0.9710   0.1001
  -5.000  -0.1810   0.02935   0.02188  -0.1096   0.9625   0.1017
  -4.750  -0.1355   0.02801   0.02021  -0.1132   0.9558   0.1057
  -4.500  -0.0984   0.02699   0.01888  -0.1150   0.9457   0.1089
  -4.250  -0.0541   0.02567   0.01770  -0.1180   0.9400   0.1134
  -4.000  -0.0201   0.02490   0.01691  -0.1190   0.9286   0.1197
  -3.750   0.0184   0.02408   0.01614  -0.1208   0.9191   0.1281
  -3.500   0.0618   0.02324   0.01533  -0.1234   0.9108   0.1405
  -3.250   0.0972   0.02229   0.01455  -0.1249   0.8993   0.1689
  -3.000   0.1367   0.02274   0.01556  -0.1260   0.8878   0.2915
  -2.750   0.1819   0.02456   0.01756  -0.1267   0.8796   0.3301
  -2.500   0.2144   0.02554   0.01862  -0.1258   0.8667   0.3492
  -2.250   0.2485   0.02619   0.01931  -0.1253   0.8551   0.3679
  -2.000   0.2958   0.02612   0.01922  -0.1272   0.8499   0.3867
  -1.750   0.3311   0.02605   0.01913  -0.1274   0.8381   0.4025
  -1.500   0.3773   0.02569   0.01864  -0.1300   0.8295   0.4244
  -1.250   0.4200   0.02510   0.01800  -0.1317   0.8195   0.4395
  -1.000   0.4584   0.02435   0.01717  -0.1331   0.8066   0.4469
  -0.750   0.5021   0.02362   0.01622  -0.1361   0.7939   0.4535
  -0.500   0.5435   0.02298   0.01539  -0.1386   0.7810   0.4596
  -0.250   0.5811   0.02256   0.01481  -0.1402   0.7679   0.4649
   0.000   0.6122   0.02240   0.01446  -0.1410   0.7532   0.4703
   0.250   0.6409   0.02225   0.01418  -0.1412   0.7395   0.4747
   0.500   0.6700   0.02213   0.01397  -0.1414   0.7273   0.4785
   0.750   0.7026   0.02204   0.01370  -0.1422   0.7164   0.4835
   1.000   0.7277   0.02213   0.01367  -0.1419   0.7038   0.4882
   1.250   0.7538   0.02207   0.01358  -0.1415   0.6930   0.4917
   1.500   0.7831   0.02202   0.01344  -0.1416   0.6829   0.4957
   1.750   0.8068   0.02214   0.01352  -0.1410   0.6715   0.5003
   2.000   0.8357   0.02215   0.01343  -0.1410   0.6623   0.5054
   2.250   0.8599   0.02219   0.01348  -0.1403   0.6518   0.5100
   2.500   0.8858   0.02229   0.01354  -0.1399   0.6418   0.5147
   2.750   0.9151   0.02233   0.01346  -0.1400   0.6326   0.5197
   3.000   0.9378   0.02244   0.01365  -0.1391   0.6224   0.5245
   3.250   0.9681   0.02247   0.01357  -0.1393   0.6143   0.5314
   3.500   0.9901   0.02266   0.01382  -0.1382   0.6035   0.5372
   3.750   1.0166   0.02277   0.01392  -0.1378   0.5945   0.5434
   4.000   1.0431   0.02296   0.01409  -0.1375   0.5851   0.5500
   4.250   1.0680   0.02319   0.01437  -0.1369   0.5756   0.5565
   4.500   1.0983   0.02336   0.01445  -0.1372   0.5669   0.5656
   4.750   1.1218   0.02370   0.01490  -0.1364   0.5564   0.5736
   5.000   1.1520   0.02390   0.01501  -0.1366   0.5468   0.5835
   5.250   1.1776   0.02410   0.01525  -0.1361   0.5352   0.5929
   5.500   1.2021   0.02444   0.01568  -0.1355   0.5242   0.6035
   5.750   1.2344   0.02465   0.01582  -0.1361   0.5154   0.6178
   6.000   1.2542   0.02514   0.01654  -0.1348   0.5050   0.6324
   6.250   1.2850   0.02538   0.01685  -0.1352   0.4968   0.6529
   6.500   1.3040   0.02576   0.01756  -0.1337   0.4866   0.6819
   6.750   1.3328   0.02582   0.01796  -0.1338   0.4779   1.0000
   7.000   1.3544   0.02639   0.01859  -0.1328   0.4682   1.0000
   7.250   1.3781   0.02698   0.01919  -0.1320   0.4595   1.0000
   7.500   1.4013   0.02741   0.01964  -0.1310   0.4501   1.0000
   7.750   1.4208   0.02798   0.02030  -0.1295   0.4404   1.0000
   8.000   1.4487   0.02816   0.02039  -0.1292   0.4313   1.0000
   8.250   1.4632   0.02862   0.02100  -0.1268   0.4196   1.0000
   8.500   1.4830   0.02878   0.02118  -0.1251   0.4080   1.0000
   8.750   1.5067   0.02874   0.02104  -0.1239   0.3966   1.0000
   9.000   1.5231   0.02901   0.02139  -0.1217   0.3846   1.0000
   9.250   1.5376   0.02945   0.02194  -0.1193   0.3727   1.0000
   9.500   1.5552   0.02979   0.02229  -0.1174   0.3608   1.0000
   9.750   1.5748   0.03010   0.02253  -0.1158   0.3486   1.0000
  10.000   1.5894   0.03054   0.02301  -0.1134   0.3357   1.0000
  10.250   1.5984   0.03121   0.02377  -0.1103   0.3227   1.0000
  10.500   1.6080   0.03189   0.02452  -0.1073   0.3098   1.0000
  10.750   1.6173   0.03256   0.02520  -0.1043   0.2970   1.0000
  11.000   1.6256   0.03321   0.02582  -0.1012   0.2844   1.0000
  11.250   1.6282   0.03392   0.02656  -0.0973   0.2721   1.0000
  11.500   1.6235   0.03490   0.02767  -0.0925   0.2600   1.0000
  11.750   1.6202   0.03595   0.02878  -0.0883   0.2479   1.0000
  12.000   1.6165   0.03712   0.02996  -0.0844   0.2357   1.0000
  12.250   1.6120   0.03848   0.03130  -0.0807   0.2235   1.0000
  12.500   1.6050   0.04015   0.03300  -0.0772   0.2114   1.0000
  12.750   1.5961   0.04225   0.03519  -0.0741   0.1996   1.0000
  13.000   1.5886   0.04457   0.03753  -0.0714   0.1880   1.0000
  13.250   1.5816   0.04708   0.04003  -0.0693   0.1771   1.0000
  13.500   1.5765   0.04964   0.04247  -0.0675   0.1663   1.0000
  13.750   1.5658   0.05290   0.04591  -0.0660   0.1565   1.0000
  14.000   1.5578   0.05613   0.04917  -0.0648   0.1469   1.0000
  14.250   1.5526   0.05915   0.05207  -0.0638   0.1376   1.0000
  14.500   1.5393   0.06325   0.05640  -0.0634   0.1294   1.0000
  14.750   1.5309   0.06696   0.06011  -0.0630   0.1213   1.0000
  15.000   1.5206   0.07103   0.06423  -0.0630   0.1137   1.0000
  15.250   1.5108   0.07530   0.06860  -0.0632   0.1062   1.0000
  15.500   1.5062   0.07881   0.07194  -0.0632   0.0984   1.0000
  15.750   1.4933   0.08389   0.07726  -0.0641   0.0925   1.0000
  16.000   1.4924   0.08710   0.08032  -0.0639   0.0857   1.0000
  16.250   1.4826   0.09197   0.08541  -0.0649   0.0808   1.0000
  16.500   1.4896   0.09414   0.08740  -0.0640   0.0747   1.0000
  16.750   1.4778   0.09950   0.09305  -0.0655   0.0718   1.0000
  17.000   1.4748   0.10342   0.09706  -0.0663   0.0682   1.0000
  17.250   1.4848   0.10532   0.09884  -0.0655   0.0641   1.0000
  17.500   1.4723   0.11101   0.10483  -0.0676   0.0626   1.0000
  17.750   1.4608   0.11668   0.11075  -0.0698   0.0611   1.0000
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