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GOE 180 (MVA H.26) AIRFOIL (goe180-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 180 (MVA H.26) AIRFOIL (goe180-il)
Reynolds number: 1,000,000
Max Cl/Cd: 126.61 at α=4.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe180-il-1000000.txt
Download as CSV file: xf-goe180-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 180 (MVA H.26) AIRFOIL                      
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.3586   0.09187   0.09026  -0.0257   1.0000   0.0151
  -8.250  -0.3576   0.08921   0.08762  -0.0259   1.0000   0.0156
  -8.000  -0.3606   0.08644   0.08489  -0.0258   1.0000   0.0165
  -7.000  -0.3115   0.06015   0.05856  -0.0587   0.9885   0.0178
  -6.750  -0.2845   0.05814   0.05653  -0.0623   0.9858   0.0182
  -6.500  -0.2573   0.05519   0.05354  -0.0669   0.9812   0.0187
  -6.250  -0.2273   0.05081   0.04910  -0.0732   0.9746   0.0199
  -5.750  -0.1431   0.00758   0.00443  -0.0941   0.9298   0.0216
  -5.500  -0.1327   0.01652   0.01267  -0.0969   0.9421   0.0226
  -5.250  -0.1009   0.01659   0.01282  -0.0979   0.9298   0.0234
  -5.000  -0.0718   0.01652   0.01271  -0.0983   0.9164   0.0245
  -4.750  -0.0450   0.01496   0.01083  -0.0982   0.9039   0.0251
  -4.500  -0.0183   0.01375   0.00936  -0.0980   0.8923   0.0257
  -4.250   0.0088   0.01296   0.00836  -0.0978   0.8812   0.0263
  -4.000   0.0370   0.01368   0.00898  -0.0974   0.8692   0.0275
  -3.750   0.0628   0.01181   0.00681  -0.0972   0.8562   0.0278
  -3.500   0.0894   0.01088   0.00572  -0.0968   0.8397   0.0280
  -3.250   0.1158   0.01009   0.00478  -0.0964   0.8185   0.0283
  -3.000   0.1419   0.00954   0.00409  -0.0960   0.7915   0.0288
  -2.750   0.1678   0.00927   0.00368  -0.0954   0.7564   0.0297
  -2.500   0.1935   0.00909   0.00331  -0.0948   0.7168   0.0303
  -2.250   0.2192   0.00895   0.00298  -0.0943   0.6763   0.0308
  -2.000   0.2456   0.00883   0.00269  -0.0939   0.6415   0.0313
  -1.750   0.2723   0.00871   0.00244  -0.0935   0.6127   0.0317
  -1.500   0.2993   0.00861   0.00222  -0.0933   0.5888   0.0321
  -1.250   0.3266   0.00852   0.00202  -0.0931   0.5694   0.0326
  -1.000   0.3541   0.00845   0.00187  -0.0929   0.5523   0.0332
  -0.750   0.3816   0.00842   0.00175  -0.0928   0.5369   0.0340
  -0.250   0.4372   0.00828   0.00148  -0.0925   0.5137   0.0359
   0.000   0.4651   0.00825   0.00139  -0.0924   0.5035   0.0376
   0.250   0.4927   0.00826   0.00135  -0.0923   0.4925   0.0398
   0.500   0.5207   0.00824   0.00132  -0.0923   0.4831   0.0430
   0.750   0.5485   0.00815   0.00133  -0.0922   0.4753   0.0908
   1.000   0.5763   0.00791   0.00139  -0.0923   0.4678   0.2129
   1.250   0.6036   0.00752   0.00148  -0.0925   0.4612   0.4170
   1.500   0.6278   0.00624   0.00161  -0.0918   0.4550   1.0000
   2.000   0.6834   0.00642   0.00168  -0.0916   0.4425   1.0000
   2.250   0.7111   0.00652   0.00174  -0.0915   0.4355   1.0000
   2.500   0.7389   0.00661   0.00179  -0.0914   0.4291   1.0000
   2.750   0.7666   0.00671   0.00185  -0.0914   0.4223   1.0000
   3.000   0.7942   0.00682   0.00192  -0.0913   0.4156   1.0000
   3.250   0.8219   0.00691   0.00200  -0.0912   0.4087   1.0000
   3.500   0.8493   0.00703   0.00208  -0.0911   0.4014   1.0000
   3.750   0.8770   0.00713   0.00216  -0.0910   0.3924   1.0000
   4.000   0.9043   0.00726   0.00226  -0.0909   0.3826   1.0000
   4.250   0.9314   0.00741   0.00237  -0.0908   0.3705   1.0000
   4.500   0.9584   0.00757   0.00248  -0.0906   0.3554   1.0000
   4.750   0.9849   0.00778   0.00262  -0.0904   0.3331   1.0000
   5.000   1.0100   0.00815   0.00282  -0.0900   0.2973   1.0000
   5.250   1.0346   0.00858   0.00308  -0.0895   0.2645   1.0000
   5.500   1.0594   0.00898   0.00335  -0.0890   0.2427   1.0000
   5.750   1.0848   0.00930   0.00361  -0.0887   0.2275   1.0000
   6.000   1.1107   0.00956   0.00383  -0.0884   0.2168   1.0000
   6.250   1.1364   0.00983   0.00406  -0.0881   0.2044   1.0000
   6.500   1.1622   0.01009   0.00429  -0.0878   0.1936   1.0000
   6.750   1.1877   0.01037   0.00453  -0.0875   0.1808   1.0000
   7.000   1.2123   0.01074   0.00480  -0.0870   0.1589   1.0000
   7.250   1.2355   0.01126   0.00517  -0.0864   0.1341   1.0000
   7.500   1.2589   0.01172   0.00556  -0.0858   0.1195   1.0000
   7.750   1.2828   0.01213   0.00593  -0.0852   0.1083   1.0000
   8.000   1.3061   0.01259   0.00633  -0.0846   0.0936   1.0000
   8.250   1.3191   0.01411   0.00742  -0.0825   0.0324   1.0000
   8.500   1.3395   0.01482   0.00809  -0.0814   0.0220   1.0000
   8.750   1.3603   0.01548   0.00875  -0.0803   0.0180   1.0000
   9.000   1.3827   0.01592   0.00924  -0.0795   0.0168   1.0000
   9.250   1.4040   0.01646   0.00981  -0.0786   0.0154   1.0000
   9.500   1.4224   0.01726   0.01067  -0.0771   0.0139   1.0000
   9.750   1.4431   0.01780   0.01127  -0.0761   0.0133   1.0000
  10.000   1.4633   0.01835   0.01187  -0.0750   0.0126   1.0000
  10.250   1.4825   0.01894   0.01250  -0.0739   0.0119   1.0000
  10.500   1.4998   0.01965   0.01326  -0.0724   0.0113   1.0000
  10.750   1.5113   0.02077   0.01447  -0.0700   0.0106   1.0000
  11.000   1.5238   0.02168   0.01548  -0.0679   0.0103   1.0000
  11.250   1.5365   0.02238   0.01624  -0.0656   0.0100   1.0000
  11.500   1.5473   0.02317   0.01711  -0.0632   0.0097   1.0000
  11.750   1.5568   0.02408   0.01810  -0.0607   0.0094   1.0000
  12.000   1.5651   0.02509   0.01918  -0.0583   0.0091   1.0000
  12.250   1.5725   0.02622   0.02039  -0.0560   0.0089   1.0000
  12.500   1.5786   0.02751   0.02176  -0.0538   0.0086   1.0000
  12.750   1.5831   0.02901   0.02334  -0.0517   0.0084   1.0000
  13.000   1.5834   0.03098   0.02539  -0.0497   0.0081   1.0000
  13.250   1.5758   0.03384   0.02838  -0.0476   0.0079   1.0000
  13.500   1.5601   0.03780   0.03250  -0.0458   0.0077   1.0000
  13.750   1.5663   0.03979   0.03459  -0.0454   0.0076   1.0000
  14.000   1.5690   0.04227   0.03716  -0.0451   0.0075   1.0000
  14.250   1.5682   0.04530   0.04031  -0.0450   0.0074   1.0000
  14.500   1.5661   0.04866   0.04377  -0.0453   0.0073   1.0000
  14.750   1.5620   0.05236   0.04759  -0.0457   0.0072   1.0000
  15.000   1.5563   0.05642   0.05177  -0.0465   0.0071   1.0000
  15.250   1.5499   0.06064   0.05610  -0.0473   0.0070   1.0000
  15.500   1.5418   0.06513   0.06070  -0.0483   0.0069   1.0000
  15.750   1.5332   0.06977   0.06546  -0.0494   0.0068   1.0000
  16.000   1.5239   0.07460   0.07040  -0.0507   0.0068   1.0000
  16.250   1.5136   0.07959   0.07550  -0.0521   0.0067   1.0000
  16.500   1.5028   0.08478   0.08079  -0.0536   0.0066   1.0000
  16.750   1.4921   0.09005   0.08616  -0.0552   0.0066   1.0000
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