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GOE 190 (MVA MK.18) AIRFOIL (goe190-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 190 (MVA MK.18) AIRFOIL (goe190-il)
Reynolds number: 200,000
Max Cl/Cd: 74.23 at α=7°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe190-il-200000-n5.txt
Download as CSV file: xf-goe190-il-200000-n5.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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.3745   0.09733   0.09375  -0.0377   1.0000   0.0289
  -9.750  -0.3657   0.09339   0.08982  -0.0409   0.9982   0.0296
  -9.250  -0.4946   0.04742   0.04341  -0.0874   0.9762   0.0308
  -9.000  -0.4611   0.03549   0.03063  -0.1125   0.9694   0.0327
  -8.750  -0.4310   0.03155   0.02620  -0.1192   0.9639   0.0340
  -8.500  -0.3973   0.03023   0.02479  -0.1223   0.9608   0.0349
  -8.250  -0.3601   0.02876   0.02315  -0.1261   0.9583   0.0363
  -8.000  -0.3369   0.02734   0.02152  -0.1267   0.9510   0.0377
  -7.750  -0.3032   0.02570   0.01954  -0.1294   0.9470   0.0393
  -7.500  -0.2673   0.02416   0.01775  -0.1321   0.9442   0.0405
  -7.250  -0.2448   0.02325   0.01683  -0.1315   0.9359   0.0416
  -7.000  -0.2114   0.02235   0.01585  -0.1331   0.9310   0.0430
  -6.750  -0.1833   0.02144   0.01482  -0.1335   0.9238   0.0444
  -6.500  -0.1555   0.02055   0.01380  -0.1337   0.9161   0.0456
  -6.250  -0.1310   0.01984   0.01297  -0.1331   0.9064   0.0469
  -5.750  -0.0804   0.01825   0.01129  -0.1323   0.8854   0.0494
  -5.500  -0.0546   0.01757   0.01060  -0.1319   0.8732   0.0507
  -5.250  -0.0242   0.01691   0.00990  -0.1323   0.8618   0.0521
  -5.000   0.0111   0.01625   0.00916  -0.1336   0.8514   0.0543
  -4.750   0.0509   0.01563   0.00844  -0.1358   0.8409   0.0566
  -4.500   0.0940   0.01495   0.00768  -0.1387   0.8297   0.0588
  -4.250   0.1407   0.01427   0.00691  -0.1426   0.8174   0.0619
  -4.000   0.1859   0.01378   0.00625  -0.1460   0.8024   0.0659
  -3.750   0.2260   0.01341   0.00568  -0.1483   0.7857   0.0706
  -3.500   0.2606   0.01305   0.00516  -0.1496   0.7697   0.0773
  -3.250   0.2921   0.01276   0.00474  -0.1503   0.7548   0.0881
  -3.000   0.3202   0.01198   0.00431  -0.1508   0.7405   0.1991
  -2.750   0.3482   0.01205   0.00441  -0.1506   0.7263   0.2565
  -2.500   0.3759   0.01218   0.00440  -0.1503   0.7127   0.2748
  -2.250   0.4029   0.01234   0.00446  -0.1498   0.6983   0.2876
  -2.000   0.4291   0.01251   0.00454  -0.1491   0.6827   0.2985
  -1.750   0.4551   0.01263   0.00450  -0.1484   0.6665   0.3078
  -1.500   0.4805   0.01277   0.00461  -0.1476   0.6502   0.3148
  -1.250   0.5061   0.01291   0.00463  -0.1469   0.6343   0.3234
  -1.000   0.5314   0.01304   0.00470  -0.1461   0.6184   0.3299
  -0.750   0.5567   0.01319   0.00477  -0.1453   0.6035   0.3364
  -0.250   0.6077   0.01334   0.00469  -0.1439   0.5777   0.3448
   0.000   0.6332   0.01344   0.00472  -0.1432   0.5673   0.3476
   0.250   0.6587   0.01354   0.00473  -0.1426   0.5577   0.3506
   0.500   0.6848   0.01363   0.00475  -0.1420   0.5492   0.3536
   0.750   0.7109   0.01373   0.00476  -0.1415   0.5416   0.3568
   1.000   0.7373   0.01383   0.00478  -0.1411   0.5348   0.3601
   1.250   0.7634   0.01393   0.00488  -0.1406   0.5276   0.3627
   1.500   0.7894   0.01409   0.00499  -0.1401   0.5212   0.3659
   1.750   0.8156   0.01419   0.00510  -0.1396   0.5144   0.3695
   2.000   0.8418   0.01433   0.00520  -0.1391   0.5083   0.3731
   2.250   0.8682   0.01447   0.00529  -0.1387   0.5028   0.3768
   2.500   0.8941   0.01457   0.00544  -0.1382   0.4963   0.3797
   2.750   0.9198   0.01472   0.00559  -0.1376   0.4901   0.3829
   3.000   0.9455   0.01487   0.00576  -0.1371   0.4841   0.3868
   3.250   0.9711   0.01499   0.00591  -0.1365   0.4777   0.3915
   3.500   0.9966   0.01516   0.00607  -0.1359   0.4720   0.3957
   3.750   1.0218   0.01530   0.00628  -0.1353   0.4656   0.3995
   4.000   1.0463   0.01543   0.00645  -0.1345   0.4577   0.4037
   4.500   1.0946   0.01572   0.00679  -0.1329   0.4408   0.4127
   4.750   1.1183   0.01588   0.00699  -0.1320   0.4327   0.4170
   5.000   1.1416   0.01603   0.00719  -0.1310   0.4234   0.4223
   5.250   1.1650   0.01621   0.00740  -0.1301   0.4147   0.4282
   5.500   1.1876   0.01638   0.00763  -0.1290   0.4061   0.4328
   5.750   1.2105   0.01657   0.00787  -0.1280   0.3980   0.4382
   6.000   1.2328   0.01679   0.00811  -0.1269   0.3900   0.4440
   6.250   1.2552   0.01700   0.00840  -0.1258   0.3825   0.4489
   6.500   1.2771   0.01725   0.00868  -0.1246   0.3746   0.4550
   6.750   1.2992   0.01751   0.00900  -0.1235   0.3666   0.4615
   7.000   1.3205   0.01779   0.00933  -0.1223   0.3582   0.4677
   7.250   1.3418   0.01809   0.00967  -0.1211   0.3496   0.4748
   7.500   1.3613   0.01843   0.01003  -0.1196   0.3405   0.4808
   7.750   1.3812   0.01874   0.01041  -0.1182   0.3306   0.4878
   8.000   1.3986   0.01910   0.01080  -0.1164   0.3209   0.4948
   8.250   1.4157   0.01948   0.01122  -0.1145   0.3104   0.5028
   8.500   1.4332   0.01988   0.01168  -0.1127   0.3002   0.5111
   8.750   1.4488   0.02035   0.01219  -0.1106   0.2906   0.5204
   9.000   1.4665   0.02075   0.01270  -0.1090   0.2807   0.5304
   9.250   1.4821   0.02124   0.01325  -0.1070   0.2703   0.5425
   9.500   1.4961   0.02178   0.01386  -0.1049   0.2597   0.5594
   9.750   1.5117   0.02225   0.01451  -0.1031   0.2477   0.5988
  10.250   1.5440   0.02334   0.01602  -0.1004   0.2214   1.0000
  10.500   1.5533   0.02421   0.01687  -0.0978   0.2086   1.0000
  10.750   1.5605   0.02521   0.01785  -0.0951   0.1955   1.0000
  11.000   1.5659   0.02636   0.01898  -0.0923   0.1832   1.0000
  11.500   1.5738   0.02902   0.02162  -0.0869   0.1597   1.0000
  11.750   1.5772   0.03051   0.02311  -0.0844   0.1488   1.0000
  12.000   1.5788   0.03219   0.02480  -0.0821   0.1385   1.0000
  12.250   1.5801   0.03401   0.02663  -0.0799   0.1278   1.0000
  12.500   1.5826   0.03585   0.02852  -0.0781   0.1173   1.0000
  12.750   1.5831   0.03796   0.03068  -0.0765   0.1079   1.0000
  13.000   1.5815   0.04039   0.03312  -0.0750   0.0996   1.0000
  13.250   1.5793   0.04300   0.03577  -0.0738   0.0916   1.0000
  13.500   1.5765   0.04581   0.03862  -0.0727   0.0855   1.0000
  13.750   1.5725   0.04885   0.04171  -0.0719   0.0799   1.0000
  14.000   1.5684   0.05202   0.04495  -0.0713   0.0754   1.0000
  14.250   1.5646   0.05528   0.04830  -0.0709   0.0706   1.0000
  14.500   1.5575   0.05904   0.05213  -0.0707   0.0668   1.0000
  14.750   1.5547   0.06241   0.05561  -0.0706   0.0626   1.0000
  15.000   1.5484   0.06632   0.05961  -0.0709   0.0583   1.0000
  15.250   1.5419   0.07038   0.06376  -0.0712   0.0547   1.0000
  15.500   1.5361   0.07443   0.06791  -0.0717   0.0507   1.0000
  15.750   1.5270   0.07905   0.07260  -0.0725   0.0471   1.0000
  16.000   1.5208   0.08333   0.07698  -0.0733   0.0436   1.0000
  16.250   1.5108   0.08827   0.08198  -0.0744   0.0402   1.0000
  16.500   1.5028   0.09295   0.08677  -0.0755   0.0371   1.0000
  16.750   1.4930   0.09805   0.09195  -0.0769   0.0344   1.0000
  17.000   1.4838   0.10313   0.09712  -0.0784   0.0321   1.0000
  17.250   1.4748   0.10826   0.10235  -0.0801   0.0299   1.0000
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