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GOE 190 (MVA MK.18) AIRFOIL (goe190-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 190 (MVA MK.18) AIRFOIL (goe190-il)
Reynolds number: 100,000
Max Cl/Cd: 57.68 at α=8.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe190-il-100000-n5.txt
Download as CSV file: xf-goe190-il-100000-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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.3540   0.09416   0.08925  -0.0389   1.0000   0.0468
  -8.750  -0.3669   0.08997   0.08514  -0.0391   1.0000   0.0469
  -8.500  -0.3888   0.08499   0.08025  -0.0394   1.0000   0.0472
  -8.250  -0.4213   0.07905   0.07441  -0.0399   0.9994   0.0474
  -8.000  -0.4354   0.05342   0.04830  -0.0790   0.9831   0.0475
  -7.750  -0.3995   0.04282   0.03694  -0.0995   0.9743   0.0487
  -7.500  -0.3661   0.03942   0.03327  -0.1052   0.9680   0.0501
  -7.250  -0.3308   0.03683   0.03043  -0.1100   0.9616   0.0524
  -7.000  -0.2945   0.03391   0.02702  -0.1150   0.9552   0.0547
  -6.750  -0.2599   0.03148   0.02411  -0.1184   0.9477   0.0562
  -6.500  -0.2216   0.02952   0.02175  -0.1219   0.9435   0.0583
  -6.250  -0.1970   0.02811   0.02035  -0.1219   0.9338   0.0602
  -6.000  -0.1616   0.02681   0.01892  -0.1239   0.9288   0.0621
  -5.750  -0.1358   0.02574   0.01774  -0.1238   0.9185   0.0637
  -5.500  -0.1002   0.02472   0.01656  -0.1254   0.9130   0.0662
  -5.250  -0.0746   0.02395   0.01565  -0.1250   0.9012   0.0686
  -5.000  -0.0479   0.02309   0.01482  -0.1247   0.8907   0.0707
  -4.750  -0.0151   0.02230   0.01406  -0.1255   0.8837   0.0731
  -4.500   0.0116   0.02171   0.01345  -0.1252   0.8719   0.0758
  -4.250   0.0412   0.02111   0.01275  -0.1255   0.8613   0.0800
  -4.000   0.0758   0.02033   0.01190  -0.1267   0.8533   0.0850
  -3.750   0.1090   0.01957   0.01106  -0.1278   0.8426   0.0910
  -3.500   0.1447   0.01874   0.01016  -0.1295   0.8327   0.1009
  -3.250   0.1853   0.01747   0.00912  -0.1325   0.8248   0.1542
  -3.000   0.2225   0.01737   0.00934  -0.1339   0.8135   0.2536
  -2.750   0.2633   0.01752   0.00929  -0.1358   0.8026   0.2896
  -2.500   0.3053   0.01763   0.00919  -0.1379   0.7914   0.3087
  -2.250   0.3414   0.01794   0.00943  -0.1388   0.7777   0.3218
  -2.000   0.3768   0.01817   0.00957  -0.1397   0.7637   0.3325
  -1.750   0.4115   0.01837   0.00961  -0.1405   0.7495   0.3452
  -1.500   0.4444   0.01867   0.00983  -0.1409   0.7353   0.3558
  -1.250   0.4771   0.01866   0.00963  -0.1416   0.7211   0.3625
  -1.000   0.5061   0.01867   0.00953  -0.1415   0.7061   0.3661
  -0.750   0.5340   0.01864   0.00938  -0.1413   0.6912   0.3704
  -0.500   0.5619   0.01856   0.00913  -0.1412   0.6768   0.3749
  -0.250   0.5893   0.01852   0.00895  -0.1410   0.6633   0.3787
   0.000   0.6163   0.01855   0.00892  -0.1406   0.6508   0.3819
   0.250   0.6431   0.01856   0.00885  -0.1402   0.6386   0.3854
   0.500   0.6693   0.01855   0.00876  -0.1398   0.6265   0.3892
   0.750   0.6965   0.01855   0.00861  -0.1396   0.6155   0.3936
   1.000   0.7235   0.01859   0.00859  -0.1392   0.6056   0.3969
   1.250   0.7493   0.01866   0.00865  -0.1387   0.5951   0.4004
   1.500   0.7762   0.01874   0.00865  -0.1383   0.5859   0.4046
   1.750   0.8027   0.01882   0.00864  -0.1379   0.5767   0.4089
   2.000   0.8293   0.01892   0.00866  -0.1376   0.5683   0.4127
   2.250   0.8553   0.01904   0.00879  -0.1371   0.5600   0.4162
   2.500   0.8815   0.01920   0.00891  -0.1366   0.5521   0.4207
   2.750   0.9075   0.01937   0.00902  -0.1362   0.5438   0.4261
   3.000   0.9340   0.01955   0.00918  -0.1358   0.5364   0.4304
   3.250   0.9596   0.01975   0.00941  -0.1353   0.5285   0.4345
   3.500   0.9874   0.01998   0.00956  -0.1352   0.5217   0.4395
   3.750   1.0125   0.02021   0.00984  -0.1346   0.5133   0.4451
   4.000   1.0396   0.02045   0.01008  -0.1344   0.5062   0.4499
   4.250   1.0651   0.02072   0.01039  -0.1339   0.4986   0.4559
   4.500   1.0912   0.02098   0.01068  -0.1335   0.4911   0.4619
   4.750   1.1172   0.02125   0.01098  -0.1331   0.4838   0.4674
   5.000   1.1416   0.02152   0.01130  -0.1325   0.4752   0.4737
   5.250   1.1665   0.02176   0.01159  -0.1319   0.4669   0.4800
   5.500   1.1892   0.02199   0.01189  -0.1308   0.4566   0.4871
   5.750   1.2118   0.02222   0.01219  -0.1298   0.4467   0.4942
   6.000   1.2352   0.02244   0.01248  -0.1290   0.4380   0.5018
   6.250   1.2578   0.02272   0.01288  -0.1280   0.4295   0.5095
   6.500   1.2810   0.02297   0.01320  -0.1271   0.4217   0.5180
   6.750   1.3029   0.02326   0.01365  -0.1261   0.4130   0.5271
   7.000   1.3252   0.02353   0.01398  -0.1250   0.4051   0.5376
   7.250   1.3463   0.02384   0.01447  -0.1239   0.3966   0.5484
   7.500   1.3678   0.02412   0.01484  -0.1228   0.3890   0.5612
   7.750   1.3876   0.02446   0.01539  -0.1214   0.3801   0.5775
   8.000   1.4078   0.02471   0.01577  -0.1201   0.3723   0.6036
   8.250   1.4265   0.02473   0.01632  -0.1186   0.3626   1.0000
   8.500   1.4438   0.02520   0.01677  -0.1168   0.3533   1.0000
   8.750   1.4587   0.02570   0.01732  -0.1146   0.3423   1.0000
   9.000   1.4718   0.02625   0.01792  -0.1122   0.3305   1.0000
   9.250   1.4834   0.02683   0.01850  -0.1095   0.3197   1.0000
   9.500   1.4944   0.02746   0.01915  -0.1068   0.3093   1.0000
   9.750   1.5052   0.02816   0.01995  -0.1042   0.2991   1.0000
  10.000   1.5148   0.02891   0.02073  -0.1014   0.2893   1.0000
  10.250   1.5233   0.02974   0.02164  -0.0987   0.2785   1.0000
  10.500   1.5312   0.03064   0.02264  -0.0959   0.2681   1.0000
  10.750   1.5374   0.03164   0.02367  -0.0931   0.2577   1.0000
  11.000   1.5424   0.03275   0.02486  -0.0903   0.2467   1.0000
  11.250   1.5468   0.03397   0.02620  -0.0877   0.2359   1.0000
  11.500   1.5495   0.03536   0.02763  -0.0850   0.2254   1.0000
  11.750   1.5501   0.03695   0.02925  -0.0824   0.2152   1.0000
  12.000   1.5511   0.03867   0.03107  -0.0801   0.2048   1.0000
  12.250   1.5500   0.04065   0.03310  -0.0779   0.1954   1.0000
  12.500   1.5466   0.04293   0.03539  -0.0759   0.1863   1.0000
  12.750   1.5437   0.04537   0.03793  -0.0743   0.1770   1.0000
  13.000   1.5381   0.04819   0.04076  -0.0729   0.1686   1.0000
  13.250   1.5319   0.05125   0.04392  -0.0718   0.1596   1.0000
  13.500   1.5249   0.05457   0.04731  -0.0710   0.1510   1.0000
  13.750   1.5156   0.05828   0.05106  -0.0705   0.1428   1.0000
  14.000   1.5081   0.06203   0.05494  -0.0703   0.1344   1.0000
  14.250   1.4970   0.06633   0.05924  -0.0705   0.1272   1.0000
  14.500   1.4888   0.07054   0.06362  -0.0709   0.1189   1.0000
  14.750   1.4781   0.07518   0.06830  -0.0716   0.1126   1.0000
  15.000   1.4692   0.07975   0.07300  -0.0724   0.1059   1.0000
  15.250   1.4581   0.08471   0.07799  -0.0734   0.1008   1.0000
  15.500   1.4499   0.08941   0.08282  -0.0745   0.0952   1.0000
  15.750   1.4389   0.09458   0.08803  -0.0759   0.0905   1.0000
  16.000   1.4302   0.09951   0.09306  -0.0773   0.0859   1.0000
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