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GOE 281 (DAIMLER XII) AIRFOIL (goe281-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 281 (DAIMLER XII) AIRFOIL (goe281-il)
Reynolds number: 1,000,000
Max Cl/Cd: 118.23 at α=3.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe281-il-1000000.txt
Download as CSV file: xf-goe281-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 281 (DAIMLER XII) 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
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.3861   0.12231   0.12067  -0.0142   1.0000   0.0092
 -10.250  -0.3804   0.11878   0.11715  -0.0158   1.0000   0.0093
 -10.000  -0.3765   0.11445   0.11283  -0.0166   1.0000   0.0094
  -9.750  -0.3698   0.11141   0.10979  -0.0174   1.0000   0.0095
  -9.500  -0.3628   0.10851   0.10690  -0.0186   1.0000   0.0097
  -9.250  -0.3558   0.10562   0.10403  -0.0198   1.0000   0.0099
  -9.000  -0.3490   0.10269   0.10111  -0.0212   1.0000   0.0102
  -8.750  -0.3424   0.09970   0.09813  -0.0226   1.0000   0.0107
  -8.500  -0.3364   0.09657   0.09501  -0.0241   1.0000   0.0115
  -8.000  -0.2341   0.07408   0.07265  -0.0401   0.9944   0.0123
  -7.750  -0.2293   0.06869   0.06727  -0.0422   0.9906   0.0125
  -7.500  -0.2182   0.06512   0.06370  -0.0440   0.9861   0.0127
  -7.250  -0.2089   0.06173   0.06031  -0.0463   0.9793   0.0129
  -7.000  -0.2014   0.05817   0.05674  -0.0490   0.9703   0.0132
  -6.750  -0.1939   0.05458   0.05314  -0.0518   0.9601   0.0135
  -6.500  -0.1841   0.05084   0.04937  -0.0549   0.9507   0.0141
  -5.250  -0.1024   0.03976   0.03761  -0.0836   0.9305   0.0163
  -5.000  -0.0828   0.03823   0.03604  -0.0839   0.9205   0.0166
  -4.750  -0.0603   0.03639   0.03411  -0.0846   0.9092   0.0172
  -4.500  -0.0349   0.03404   0.03160  -0.0857   0.8960   0.0184
  -4.250   0.0007   0.03081   0.02803  -0.0864   0.8821   0.0203
  -4.000   0.0282   0.02774   0.02465  -0.0869   0.8661   0.0204
  -3.750   0.0526   0.02220   0.01867  -0.0880   0.8496   0.0211
  -3.500   0.0777   0.02098   0.01731  -0.0882   0.8311   0.0215
  -3.250   0.1037   0.01993   0.01609  -0.0884   0.8131   0.0221
  -3.000   0.1307   0.01882   0.01478  -0.0885   0.7953   0.0231
  -2.750   0.1606   0.01884   0.01455  -0.0880   0.7776   0.0261
  -2.500   0.1891   0.01801   0.01342  -0.0878   0.7585   0.0263
  -2.250   0.2171   0.01691   0.01204  -0.0878   0.7388   0.0264
  -2.000   0.2448   0.01375   0.00848  -0.0882   0.7206   0.0273
  -1.750   0.2725   0.01291   0.00754  -0.0884   0.7038   0.0280
  -1.500   0.3003   0.01234   0.00687  -0.0886   0.6883   0.0289
  -1.250   0.3284   0.01189   0.00630  -0.0886   0.6745   0.0304
  -1.000   0.3568   0.01162   0.00590  -0.0886   0.6626   0.0324
  -0.750   0.3853   0.01216   0.00632  -0.0885   0.6507   0.0340
  -0.500   0.4134   0.01036   0.00439  -0.0888   0.6404   0.0370
  -0.250   0.4415   0.01002   0.00403  -0.0889   0.6303   0.0392
   1.000   0.5829   0.00879   0.00250  -0.0888   0.5695   0.0348
   1.250   0.6110   0.00847   0.00213  -0.0889   0.5519   0.0324
   1.500   0.6388   0.00840   0.00196  -0.0889   0.5238   0.0327
   1.750   0.6660   0.00849   0.00188  -0.0888   0.4847   0.0334
   2.000   0.6931   0.00863   0.00188  -0.0888   0.4548   0.0339
   2.250   0.7206   0.00873   0.00189  -0.0888   0.4366   0.0342
   2.500   0.7482   0.00879   0.00188  -0.0888   0.4217   0.0347
   2.750   0.7759   0.00885   0.00189  -0.0889   0.4099   0.0361
   3.000   0.8037   0.00892   0.00193  -0.0889   0.3999   0.0369
   3.250   0.8313   0.00903   0.00199  -0.0889   0.3898   0.0381
   3.500   0.8591   0.00910   0.00206  -0.0890   0.3800   0.0430
   3.750   0.8820   0.00746   0.00235  -0.0886   0.3660   1.0000
   4.000   0.9089   0.00770   0.00246  -0.0885   0.3414   1.0000
   4.250   0.9357   0.00795   0.00259  -0.0884   0.3162   1.0000
   4.500   0.9612   0.00837   0.00280  -0.0882   0.2754   1.0000
   4.750   0.9864   0.00882   0.00306  -0.0880   0.2398   1.0000
   5.000   1.0121   0.00919   0.00330  -0.0878   0.2176   1.0000
   5.250   1.0381   0.00950   0.00353  -0.0876   0.1986   1.0000
   5.500   1.0626   0.01000   0.00383  -0.0873   0.1631   1.0000
   5.750   1.0845   0.01085   0.00433  -0.0866   0.1084   1.0000
   6.000   1.1017   0.01231   0.00528  -0.0852   0.0217   1.0000
   6.250   1.1271   0.01266   0.00566  -0.0848   0.0167   1.0000
   6.500   1.1520   0.01303   0.00609  -0.0844   0.0152   1.0000
   6.750   1.1761   0.01352   0.00663  -0.0839   0.0133   1.0000
   7.000   1.1995   0.01407   0.00726  -0.0832   0.0122   1.0000
   7.250   1.2235   0.01450   0.00773  -0.0827   0.0117   1.0000
   7.500   1.2469   0.01500   0.00830  -0.0820   0.0111   1.0000
   7.750   1.2696   0.01555   0.00890  -0.0813   0.0105   1.0000
   8.000   1.2916   0.01616   0.00956  -0.0805   0.0099   1.0000
   8.250   1.3123   0.01686   0.01031  -0.0795   0.0094   1.0000
   8.500   1.3246   0.01840   0.01200  -0.0772   0.0086   1.0000
   8.750   1.3443   0.01908   0.01275  -0.0760   0.0083   1.0000
   9.000   1.3635   0.01977   0.01350  -0.0748   0.0080   1.0000
   9.250   1.3805   0.02060   0.01440  -0.0732   0.0078   1.0000
   9.500   1.3957   0.02153   0.01540  -0.0714   0.0075   1.0000
   9.750   1.4091   0.02252   0.01646  -0.0694   0.0073   1.0000
  10.000   1.4203   0.02355   0.01755  -0.0670   0.0071   1.0000
  10.250   1.4278   0.02458   0.01867  -0.0641   0.0069   1.0000
  10.500   1.4347   0.02569   0.01985  -0.0612   0.0067   1.0000
  10.750   1.4417   0.02687   0.02110  -0.0586   0.0065   1.0000
  11.000   1.4479   0.02818   0.02248  -0.0561   0.0063   1.0000
  11.250   1.4521   0.02972   0.02409  -0.0536   0.0062   1.0000
  11.500   1.4536   0.03161   0.02605  -0.0512   0.0060   1.0000
  11.750   1.4507   0.03415   0.02866  -0.0485   0.0059   1.0000
  12.000   1.4458   0.03762   0.03223  -0.0454   0.0056   1.0000
  12.250   1.4514   0.03910   0.03385  -0.0442   0.0055   1.0000
  12.500   1.4559   0.04101   0.03587  -0.0431   0.0054   1.0000
  12.750   1.4588   0.04325   0.03823  -0.0419   0.0053   1.0000
  13.000   1.4599   0.04583   0.04094  -0.0407   0.0052   1.0000
  13.250   1.4599   0.04863   0.04386  -0.0396   0.0052   1.0000
  13.500   1.4590   0.05161   0.04697  -0.0387   0.0051   1.0000
  13.750   1.4563   0.05486   0.05037  -0.0379   0.0051   1.0000
  14.000   1.4520   0.05839   0.05404  -0.0374   0.0050   1.0000
  14.250   1.4458   0.06228   0.05808  -0.0372   0.0050   1.0000
  14.500   1.4378   0.06642   0.06238  -0.0373   0.0050   1.0000
  14.750   1.4284   0.07091   0.06703  -0.0379   0.0050   1.0000
  15.000   1.4169   0.07591   0.07219  -0.0388   0.0050   1.0000
  15.250   1.4047   0.08114   0.07758  -0.0401   0.0050   1.0000
  15.500   1.3916   0.08677   0.08337  -0.0420   0.0050   1.0000
  15.750   1.3771   0.09293   0.08968  -0.0444   0.0050   1.0000
  16.000   1.3620   0.09942   0.09633  -0.0472   0.0050   1.0000
  16.250   1.3471   0.10617   0.10323  -0.0505   0.0050   1.0000
  16.500   1.3321   0.11325   0.11046  -0.0541   0.0050   1.0000
  16.750   1.3160   0.12079   0.11814  -0.0582   0.0050   1.0000
  17.000   1.3003   0.12849   0.12598  -0.0626   0.0050   1.0000
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