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GOE 182 (MVA H.27) AIRFOIL (goe182-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: GOE 182 (MVA H.27) AIRFOIL (goe182-il)
Reynolds number: 1,000,000
Max Cl/Cd: 119.84 at α=7°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe182-il-1000000-n5.txt
Download as CSV file: xf-goe182-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 182 (MVA H.27) 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.7290   0.02448   0.02195  -0.0957   0.9979   0.0149
 -11.000  -0.6982   0.02216   0.01941  -0.0987   0.9954   0.0156
 -10.750  -0.6679   0.02038   0.01743  -0.1009   0.9926   0.0162
 -10.500  -0.6384   0.01891   0.01575  -0.1024   0.9885   0.0167
 -10.250  -0.6064   0.01790   0.01462  -0.1040   0.9846   0.0172
 -10.000  -0.5765   0.01760   0.01431  -0.1044   0.9785   0.0177
  -9.750  -0.5457   0.01739   0.01410  -0.1050   0.9737   0.0182
  -9.500  -0.5178   0.01708   0.01374  -0.1050   0.9678   0.0187
  -9.250  -0.4897   0.01657   0.01314  -0.1052   0.9618   0.0191
  -9.000  -0.4630   0.01598   0.01244  -0.1051   0.9543   0.0196
  -8.750  -0.4364   0.01540   0.01174  -0.1050   0.9460   0.0201
  -8.500  -0.4100   0.01491   0.01114  -0.1047   0.9360   0.0205
  -8.250  -0.3837   0.01449   0.01060  -0.1043   0.9230   0.0208
  -8.000  -0.3583   0.01380   0.00974  -0.1039   0.9029   0.0212
  -7.750  -0.3334   0.01338   0.00914  -0.1032   0.8672   0.0216
  -7.250  -0.2827   0.01329   0.00856  -0.1018   0.7604   0.0224
  -6.750  -0.2286   0.01297   0.00789  -0.1012   0.7035   0.0232
  -6.500  -0.2012   0.01265   0.00741  -0.1011   0.6809   0.0237
  -6.250  -0.1736   0.01235   0.00695  -0.1009   0.6608   0.0241
  -6.000  -0.1459   0.01206   0.00651  -0.1008   0.6401   0.0246
  -5.750  -0.1180   0.01173   0.00604  -0.1007   0.6220   0.0249
  -5.500  -0.0902   0.01145   0.00561  -0.1005   0.6026   0.0252
  -5.250  -0.0623   0.01122   0.00523  -0.1004   0.5814   0.0254
  -5.000  -0.0344   0.01103   0.00489  -0.1003   0.5606   0.0256
  -4.750  -0.0067   0.01068   0.00440  -0.1001   0.5421   0.0260
  -4.500   0.0212   0.01035   0.00394  -0.1000   0.5262   0.0266
  -4.250   0.0493   0.01013   0.00363  -0.0999   0.5114   0.0270
  -4.000   0.0774   0.00997   0.00337  -0.0998   0.4969   0.0274
  -3.750   0.1055   0.00984   0.00315  -0.0997   0.4817   0.0278
  -3.500   0.1337   0.00972   0.00294  -0.0996   0.4662   0.0282
  -3.250   0.1619   0.00962   0.00275  -0.0994   0.4508   0.0286
  -3.000   0.1901   0.00954   0.00258  -0.0993   0.4351   0.0291
  -2.750   0.2182   0.00947   0.00242  -0.0992   0.4175   0.0296
  -2.500   0.2463   0.00944   0.00228  -0.0991   0.3982   0.0301
  -2.250   0.2743   0.00944   0.00217  -0.0989   0.3788   0.0307
  -2.000   0.3023   0.00945   0.00208  -0.0988   0.3609   0.0312
  -1.750   0.3303   0.00945   0.00200  -0.0987   0.3451   0.0316
  -1.500   0.3584   0.00941   0.00188  -0.0985   0.3315   0.0328
  -1.250   0.3865   0.00940   0.00181  -0.0984   0.3195   0.0340
  -1.000   0.4147   0.00940   0.00177  -0.0983   0.3100   0.0353
  -0.750   0.4428   0.00942   0.00174  -0.0982   0.3009   0.0369
  -0.500   0.4710   0.00943   0.00171  -0.0981   0.2931   0.0385
  -0.250   0.4991   0.00945   0.00170  -0.0980   0.2855   0.0429
   0.000   0.5273   0.00946   0.00171  -0.0979   0.2793   0.0483
   0.250   0.5553   0.00949   0.00173  -0.0977   0.2725   0.0561
   0.500   0.5834   0.00951   0.00175  -0.0976   0.2674   0.0635
   0.750   0.6115   0.00956   0.00178  -0.0975   0.2624   0.0680
   1.000   0.6395   0.00960   0.00180  -0.0974   0.2571   0.0742
   1.250   0.6675   0.00965   0.00184  -0.0973   0.2529   0.0799
   1.500   0.6955   0.00966   0.00188  -0.0972   0.2492   0.0925
   1.750   0.7233   0.00965   0.00197  -0.0972   0.2444   0.1446
   2.000   0.7510   0.00973   0.00205  -0.0971   0.2389   0.1611
   2.500   0.8067   0.00979   0.00222  -0.0969   0.2319   0.2129
   2.750   0.8345   0.00980   0.00232  -0.0968   0.2295   0.2609
   3.000   0.8621   0.00982   0.00243  -0.0967   0.2273   0.3076
   3.250   0.8896   0.00977   0.00258  -0.0967   0.2251   0.4041
   3.500   0.9170   0.00973   0.00274  -0.0966   0.2229   0.5028
   4.000   0.9706   0.00900   0.00302  -0.0962   0.2204   1.0000
   4.250   0.9982   0.00912   0.00314  -0.0960   0.2195   1.0000
   4.500   1.0257   0.00924   0.00326  -0.0959   0.2185   1.0000
   4.750   1.0531   0.00937   0.00338  -0.0957   0.2175   1.0000
   5.000   1.0804   0.00951   0.00352  -0.0956   0.2160   1.0000
   5.250   1.1075   0.00967   0.00366  -0.0954   0.2127   1.0000
   5.500   1.1344   0.00985   0.00381  -0.0952   0.2097   1.0000
   5.750   1.1613   0.01002   0.00398  -0.0950   0.2076   1.0000
   6.000   1.1882   0.01018   0.00415  -0.0949   0.2055   1.0000
   6.250   1.2153   0.01032   0.00431  -0.0947   0.2045   1.0000
   6.500   1.2423   0.01046   0.00448  -0.0945   0.2033   1.0000
   6.750   1.2691   0.01062   0.00465  -0.0943   0.2013   1.0000
   7.000   1.2955   0.01081   0.00483  -0.0941   0.1966   1.0000
   7.250   1.3215   0.01105   0.00505  -0.0939   0.1911   1.0000
   7.500   1.3477   0.01126   0.00524  -0.0936   0.1825   1.0000
   7.750   1.3713   0.01177   0.00558  -0.0931   0.1534   1.0000
   8.000   1.3891   0.01299   0.00651  -0.0919   0.1066   1.0000
   8.250   1.4123   0.01352   0.00700  -0.0913   0.0927   1.0000
   8.500   1.4305   0.01464   0.00789  -0.0901   0.0537   1.0000
   8.750   1.4533   0.01517   0.00840  -0.0894   0.0455   1.0000
   9.000   1.4762   0.01565   0.00888  -0.0888   0.0400   1.0000
   9.250   1.4989   0.01613   0.00936  -0.0881   0.0352   1.0000
   9.500   1.5206   0.01670   0.00991  -0.0874   0.0292   1.0000
   9.750   1.5414   0.01731   0.01049  -0.0865   0.0222   1.0000
  10.000   1.5617   0.01795   0.01111  -0.0856   0.0169   1.0000
  10.250   1.5820   0.01855   0.01172  -0.0846   0.0143   1.0000
  10.500   1.6022   0.01912   0.01232  -0.0837   0.0129   1.0000
  10.750   1.6211   0.01977   0.01299  -0.0826   0.0116   1.0000
  11.000   1.6400   0.02037   0.01364  -0.0815   0.0107   1.0000
  11.250   1.6579   0.02101   0.01432  -0.0803   0.0100   1.0000
  11.500   1.6742   0.02172   0.01507  -0.0789   0.0092   1.0000
  11.750   1.6880   0.02252   0.01592  -0.0771   0.0086   1.0000
  12.000   1.6994   0.02328   0.01675  -0.0750   0.0082   1.0000
  12.250   1.7100   0.02411   0.01764  -0.0728   0.0079   1.0000
  12.500   1.7192   0.02507   0.01867  -0.0707   0.0076   1.0000
  12.750   1.7271   0.02617   0.01983  -0.0687   0.0073   1.0000
  13.000   1.7334   0.02746   0.02119  -0.0668   0.0070   1.0000
  13.250   1.7382   0.02899   0.02280  -0.0651   0.0067   1.0000
  13.500   1.7408   0.03087   0.02477  -0.0636   0.0065   1.0000
  13.750   1.7409   0.03321   0.02720  -0.0626   0.0062   1.0000
  14.000   1.7427   0.03562   0.02972  -0.0621   0.0061   1.0000
  14.250   1.7430   0.03841   0.03261  -0.0620   0.0060   1.0000
  14.500   1.7410   0.04162   0.03593  -0.0621   0.0059   1.0000
  14.750   1.7363   0.04530   0.03972  -0.0626   0.0057   1.0000
  15.000   1.7287   0.04946   0.04400  -0.0632   0.0056   1.0000
  15.250   1.7176   0.05428   0.04895  -0.0642   0.0055   1.0000
  15.500   1.7030   0.05968   0.05448  -0.0654   0.0055   1.0000
  15.750   1.6852   0.06567   0.06061  -0.0669   0.0054   1.0000
  16.000   1.6646   0.07208   0.06716  -0.0685   0.0054   1.0000
  16.250   1.6423   0.07891   0.07412  -0.0704   0.0054   1.0000
  16.500   1.6197   0.08595   0.08129  -0.0724   0.0054   1.0000
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