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GOE 308 (MVA H.40) AIRFOIL (goe308-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: GOE 308 (MVA H.40) AIRFOIL (goe308-il)
Reynolds number: 1,000,000
Max Cl/Cd: 115.13 at α=5.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe308-il-1000000-n5.txt
Download as CSV file: xf-goe308-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 308 (MVA H.40) 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
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.3327   0.10129   0.09970  -0.0299   0.9990   0.0051
  -8.750  -0.4755   0.01861   0.01531  -0.0879   0.9547   0.0079
  -8.500  -0.4493   0.01614   0.01248  -0.0889   0.9486   0.0083
  -8.250  -0.4196   0.01480   0.01095  -0.0899   0.9400   0.0091
  -8.000  -0.3878   0.01384   0.00984  -0.0911   0.9298   0.0102
  -7.750  -0.3561   0.01302   0.00885  -0.0923   0.9167   0.0112
  -7.500  -0.3254   0.01252   0.00820  -0.0929   0.8982   0.0123
  -7.250  -0.2959   0.01255   0.00818  -0.0932   0.8764   0.0133
  -7.000  -0.2694   0.01252   0.00805  -0.0928   0.8564   0.0144
  -6.750  -0.2451   0.01217   0.00752  -0.0920   0.8389   0.0154
  -6.500  -0.2204   0.01194   0.00716  -0.0913   0.8240   0.0161
  -6.250  -0.1936   0.01215   0.00737  -0.0909   0.8123   0.0167
  -6.000  -0.1672   0.01226   0.00746  -0.0905   0.8017   0.0172
  -5.750  -0.1411   0.01228   0.00743  -0.0901   0.7913   0.0178
  -5.500  -0.1154   0.01215   0.00721  -0.0895   0.7806   0.0186
  -5.250  -0.0901   0.01198   0.00694  -0.0889   0.7687   0.0194
  -5.000  -0.0648   0.01185   0.00671  -0.0883   0.7554   0.0202
  -4.750  -0.0396   0.01167   0.00641  -0.0877   0.7420   0.0207
  -4.500  -0.0140   0.01164   0.00629  -0.0871   0.7267   0.0212
  -4.250   0.0109   0.01149   0.00601  -0.0864   0.7078   0.0214
  -4.000   0.0355   0.01148   0.00587  -0.0856   0.6852   0.0216
  -3.750   0.0573   0.01041   0.00456  -0.0845   0.6637   0.0227
  -3.500   0.0816   0.01011   0.00413  -0.0837   0.6442   0.0233
  -3.000   0.1313   0.00983   0.00364  -0.0823   0.6081   0.0245
  -2.750   0.1563   0.00966   0.00337  -0.0816   0.5897   0.0249
  -2.500   0.1813   0.00952   0.00311  -0.0810   0.5714   0.0254
  -2.250   0.2062   0.00938   0.00287  -0.0803   0.5527   0.0257
  -2.000   0.2310   0.00927   0.00265  -0.0796   0.5329   0.0261
  -1.750   0.2558   0.00918   0.00245  -0.0789   0.5110   0.0263
  -1.500   0.2805   0.00912   0.00227  -0.0782   0.4920   0.0265
  -1.000   0.3306   0.00899   0.00197  -0.0769   0.4619   0.0270
  -0.750   0.3559   0.00893   0.00185  -0.0763   0.4506   0.0272
  -0.500   0.3814   0.00891   0.00177  -0.0757   0.4410   0.0277
  -0.250   0.4068   0.00887   0.00168  -0.0752   0.4322   0.0279
   0.000   0.4326   0.00883   0.00160  -0.0746   0.4259   0.0282
   0.250   0.4582   0.00881   0.00154  -0.0741   0.4190   0.0285
   0.500   0.4839   0.00881   0.00150  -0.0736   0.4120   0.0290
   0.750   0.5095   0.00882   0.00148  -0.0731   0.4041   0.0295
   1.000   0.5352   0.00885   0.00148  -0.0726   0.3968   0.0299
   1.250   0.5610   0.00885   0.00145  -0.0722   0.3908   0.0319
   1.500   0.5865   0.00888   0.00145  -0.0717   0.3857   0.0354
   1.750   0.6124   0.00888   0.00147  -0.0712   0.3806   0.0391
   2.000   0.6373   0.00884   0.00154  -0.0707   0.3743   0.0857
   2.250   0.6630   0.00891   0.00159  -0.0702   0.3680   0.0903
   2.500   0.6888   0.00894   0.00164  -0.0698   0.3620   0.0957
   2.750   0.7143   0.00901   0.00171  -0.0693   0.3562   0.1004
   3.000   0.7401   0.00907   0.00177  -0.0689   0.3511   0.1037
   3.250   0.7657   0.00911   0.00183  -0.0685   0.3460   0.1084
   3.500   0.7910   0.00918   0.00191  -0.0680   0.3411   0.1129
   3.750   0.8165   0.00922   0.00199  -0.0676   0.3368   0.1211
   4.250   0.8660   0.00930   0.00221  -0.0664   0.3251   0.1935
   4.500   0.8909   0.00934   0.00233  -0.0659   0.3186   0.2263
   4.750   0.8946   0.00826   0.00249  -0.0611   0.3131   0.8151
   5.000   0.9449   0.00829   0.00282  -0.0663   0.2947   0.9660
   5.250   0.9855   0.00856   0.00304  -0.0694   0.2789   0.9764
   5.500   1.0179   0.00893   0.00328  -0.0708   0.2526   0.9823
   5.750   1.0461   0.00941   0.00359  -0.0714   0.2190   0.9877
   6.000   1.0722   0.01006   0.00401  -0.0716   0.1785   0.9914
   6.250   1.0997   0.01056   0.00438  -0.0720   0.1550   0.9951
   6.500   1.1284   0.01106   0.00475  -0.0727   0.1303   0.9977
   6.750   1.1423   0.01291   0.00599  -0.0711   0.0211   1.0000
   7.000   1.1598   0.01323   0.00631  -0.0691   0.0154   1.0000
   7.250   1.1771   0.01356   0.00665  -0.0672   0.0128   1.0000
   7.500   1.1948   0.01389   0.00700  -0.0653   0.0110   1.0000
   7.750   1.2129   0.01418   0.00732  -0.0636   0.0103   1.0000
   8.000   1.2303   0.01451   0.00768  -0.0617   0.0094   1.0000
   8.250   1.2470   0.01489   0.00808  -0.0597   0.0084   1.0000
   8.500   1.2628   0.01532   0.00854  -0.0576   0.0075   1.0000
   8.750   1.2795   0.01569   0.00895  -0.0557   0.0072   1.0000
   9.000   1.2956   0.01608   0.00937  -0.0537   0.0067   1.0000
   9.250   1.3091   0.01649   0.00981  -0.0512   0.0062   1.0000
   9.500   1.3215   0.01691   0.01027  -0.0485   0.0059   1.0000
   9.750   1.3334   0.01740   0.01078  -0.0459   0.0055   1.0000
  10.000   1.3426   0.01807   0.01153  -0.0428   0.0051   1.0000
  10.250   1.3549   0.01862   0.01213  -0.0404   0.0050   1.0000
  10.500   1.3681   0.01914   0.01270  -0.0383   0.0047   1.0000
  10.750   1.3782   0.01986   0.01350  -0.0358   0.0046   1.0000
  11.000   1.3894   0.02054   0.01424  -0.0336   0.0044   1.0000
  11.250   1.4009   0.02124   0.01498  -0.0315   0.0042   1.0000
  11.500   1.4121   0.02198   0.01576  -0.0296   0.0039   1.0000
  11.750   1.4214   0.02287   0.01670  -0.0275   0.0038   1.0000
  12.000   1.4283   0.02396   0.01788  -0.0254   0.0036   1.0000
  12.250   1.4333   0.02526   0.01926  -0.0232   0.0035   1.0000
  12.500   1.4331   0.02704   0.02114  -0.0209   0.0034   1.0000
  12.750   1.4396   0.02842   0.02260  -0.0194   0.0033   1.0000
  13.000   1.4456   0.02991   0.02417  -0.0181   0.0032   1.0000
  13.250   1.4457   0.03202   0.02639  -0.0167   0.0032   1.0000
  13.500   1.4469   0.03415   0.02863  -0.0156   0.0031   1.0000
  13.750   1.4450   0.03673   0.03131  -0.0147   0.0031   1.0000
  14.000   1.4436   0.03941   0.03409  -0.0142   0.0030   1.0000
  14.250   1.4419   0.04227   0.03705  -0.0139   0.0030   1.0000
  14.500   1.4422   0.04502   0.03989  -0.0139   0.0029   1.0000
  14.750   1.4376   0.04848   0.04347  -0.0141   0.0028   1.0000
  15.000   1.4271   0.05284   0.04795  -0.0147   0.0029   1.0000
  15.250   1.4218   0.05663   0.05185  -0.0153   0.0027   1.0000
  15.500   1.4143   0.06086   0.05620  -0.0161   0.0028   1.0000
  15.750   1.4083   0.06494   0.06037  -0.0171   0.0027   1.0000
  16.000   1.3960   0.06998   0.06554  -0.0183   0.0027   1.0000
  16.250   1.3904   0.07414   0.06978  -0.0194   0.0026   1.0000
  16.500   1.3800   0.07903   0.07477  -0.0207   0.0026   1.0000
  16.750   1.3635   0.08481   0.08068  -0.0222   0.0027   1.0000
  17.000   1.3591   0.08894   0.08488  -0.0234   0.0026   1.0000
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