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GOE 282 (DAIMLER XIII) AIRFOIL (goe282-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: GOE 282 (DAIMLER XIII) AIRFOIL (goe282-il)
Reynolds number: 1,000,000
Max Cl/Cd: 105.1 at α=4.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe282-il-1000000-n5.txt
Download as CSV file: xf-goe282-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 282 (DAIMLER XIII) 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
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.3617   0.11369   0.11204  -0.0312   1.0000   0.0049
 -10.750  -0.3618   0.11011   0.10848  -0.0319   1.0000   0.0050
 -10.500  -0.5839   0.02577   0.02288  -0.1119   0.9789   0.0054
 -10.250  -0.5606   0.02046   0.01717  -0.1152   0.9763   0.0056
 -10.000  -0.5357   0.01869   0.01519  -0.1160   0.9718   0.0058
  -9.750  -0.5088   0.01736   0.01366  -0.1167   0.9676   0.0060
  -9.500  -0.4807   0.01629   0.01243  -0.1174   0.9640   0.0062
  -9.250  -0.4545   0.01544   0.01143  -0.1175   0.9584   0.0064
  -9.000  -0.4273   0.01445   0.01029  -0.1178   0.9539   0.0068
  -8.750  -0.3999   0.01364   0.00935  -0.1181   0.9498   0.0073
  -8.500  -0.3728   0.01300   0.00860  -0.1181   0.9443   0.0078
  -8.250  -0.3452   0.01244   0.00793  -0.1182   0.9391   0.0082
  -8.000  -0.3175   0.01196   0.00735  -0.1183   0.9339   0.0088
  -7.750  -0.2898   0.01151   0.00680  -0.1183   0.9278   0.0094
  -7.250  -0.2342   0.01066   0.00580  -0.1183   0.9159   0.0120
  -7.000  -0.2063   0.01034   0.00540  -0.1182   0.9088   0.0135
  -6.750  -0.1781   0.01009   0.00514  -0.1182   0.9024   0.0157
  -6.500  -0.1499   0.00987   0.00487  -0.1182   0.8958   0.0174
  -6.250  -0.1215   0.00971   0.00470  -0.1183   0.8899   0.0192
  -6.000  -0.0931   0.00963   0.00461  -0.1183   0.8827   0.0211
  -5.750  -0.0647   0.00953   0.00447  -0.1183   0.8749   0.0226
  -5.500  -0.0364   0.00944   0.00431  -0.1182   0.8652   0.0236
  -5.250  -0.0080   0.00937   0.00419  -0.1182   0.8549   0.0241
  -5.000   0.0202   0.00913   0.00387  -0.1182   0.8427   0.0251
  -4.750   0.0482   0.00890   0.00355  -0.1181   0.8259   0.0265
  -4.500   0.0759   0.00882   0.00337  -0.1180   0.8036   0.0277
  -4.250   0.1031   0.00882   0.00323  -0.1177   0.7738   0.0288
  -4.000   0.1302   0.00883   0.00308  -0.1174   0.7418   0.0297
  -3.750   0.1575   0.00881   0.00289  -0.1172   0.7148   0.0304
  -3.500   0.1855   0.00873   0.00269  -0.1171   0.6950   0.0308
  -3.250   0.2136   0.00866   0.00252  -0.1171   0.6763   0.0313
  -3.000   0.2415   0.00862   0.00236  -0.1170   0.6542   0.0317
  -2.750   0.2694   0.00860   0.00222  -0.1170   0.6293   0.0322
  -2.500   0.2969   0.00866   0.00213  -0.1169   0.5976   0.0327
  -2.250   0.3242   0.00872   0.00203  -0.1167   0.5657   0.0334
  -2.000   0.3520   0.00871   0.00188  -0.1166   0.5421   0.0357
  -1.750   0.3799   0.00872   0.00181  -0.1166   0.5241   0.0381
  -1.500   0.4082   0.00872   0.00176  -0.1166   0.5121   0.0406
  -1.250   0.4365   0.00872   0.00171  -0.1167   0.5037   0.0430
  -1.000   0.4650   0.00870   0.00167  -0.1168   0.4964   0.0476
  -0.500   0.5218   0.00854   0.00163  -0.1170   0.4819   0.1022
  -0.250   0.5501   0.00856   0.00165  -0.1171   0.4741   0.1159
   0.000   0.5785   0.00858   0.00167  -0.1172   0.4661   0.1260
   0.250   0.6066   0.00863   0.00170  -0.1172   0.4566   0.1341
   0.500   0.6348   0.00868   0.00173  -0.1172   0.4462   0.1407
   0.750   0.6629   0.00872   0.00176  -0.1173   0.4365   0.1488
   1.000   0.6909   0.00879   0.00181  -0.1173   0.4256   0.1581
   1.250   0.7187   0.00886   0.00187  -0.1173   0.4127   0.1698
   1.500   0.7463   0.00896   0.00193  -0.1173   0.3979   0.1758
   1.750   0.7738   0.00908   0.00201  -0.1172   0.3810   0.1836
   2.000   0.8010   0.00923   0.00210  -0.1171   0.3617   0.1922
   2.500   0.8530   0.00978   0.00241  -0.1166   0.2991   0.2168
   2.750   0.8788   0.01007   0.00259  -0.1164   0.2700   0.2362
   3.000   0.9054   0.01024   0.00276  -0.1163   0.2533   0.2723
   3.500   0.9532   0.00919   0.00317  -0.1150   0.2347   1.0000
   3.750   0.9802   0.00937   0.00331  -0.1149   0.2262   1.0000
   4.000   1.0067   0.00961   0.00348  -0.1148   0.2150   1.0000
   4.250   1.0329   0.00986   0.00366  -0.1145   0.2039   1.0000
   4.500   1.0594   0.01008   0.00383  -0.1144   0.1940   1.0000
   4.750   1.0855   0.01033   0.00402  -0.1141   0.1809   1.0000
   5.250   1.1265   0.01203   0.00507  -0.1120   0.0727   1.0000
   5.500   1.1506   0.01245   0.00540  -0.1114   0.0577   1.0000
   5.750   1.1743   0.01290   0.00576  -0.1108   0.0430   1.0000
   6.000   1.1952   0.01365   0.00637  -0.1097   0.0136   1.0000
   6.250   1.2200   0.01395   0.00669  -0.1092   0.0114   1.0000
   6.500   1.2446   0.01426   0.00702  -0.1087   0.0103   1.0000
   6.750   1.2685   0.01461   0.00740  -0.1081   0.0090   1.0000
   7.000   1.2922   0.01498   0.00780  -0.1075   0.0081   1.0000
   7.250   1.3158   0.01533   0.00817  -0.1068   0.0075   1.0000
   7.500   1.3389   0.01570   0.00857  -0.1061   0.0069   1.0000
   7.750   1.3614   0.01612   0.00901  -0.1053   0.0064   1.0000
   8.000   1.3829   0.01659   0.00954  -0.1043   0.0058   1.0000
   8.250   1.4048   0.01701   0.00998  -0.1034   0.0055   1.0000
   8.500   1.4258   0.01747   0.01048  -0.1024   0.0051   1.0000
   8.750   1.4462   0.01795   0.01099  -0.1013   0.0048   1.0000
   9.000   1.4658   0.01846   0.01153  -0.1000   0.0046   1.0000
   9.250   1.4837   0.01905   0.01218  -0.0985   0.0043   1.0000
   9.500   1.4994   0.01975   0.01294  -0.0966   0.0041   1.0000
   9.750   1.5155   0.02034   0.01359  -0.0947   0.0040   1.0000
  10.000   1.5286   0.02097   0.01428  -0.0923   0.0038   1.0000
  10.250   1.5414   0.02165   0.01501  -0.0900   0.0036   1.0000
  10.500   1.5542   0.02235   0.01578  -0.0878   0.0035   1.0000
  10.750   1.5663   0.02312   0.01660  -0.0855   0.0033   1.0000
  11.000   1.5784   0.02391   0.01744  -0.0834   0.0032   1.0000
  11.250   1.5896   0.02478   0.01839  -0.0813   0.0031   1.0000
  11.500   1.5994   0.02579   0.01945  -0.0790   0.0030   1.0000
  11.750   1.6070   0.02697   0.02071  -0.0767   0.0029   1.0000
  12.000   1.6108   0.02850   0.02234  -0.0741   0.0028   1.0000
  12.250   1.6150   0.03006   0.02400  -0.0717   0.0027   1.0000
  12.500   1.6201   0.03164   0.02567  -0.0697   0.0027   1.0000
  12.750   1.6238   0.03340   0.02753  -0.0677   0.0026   1.0000
  13.000   1.6263   0.03536   0.02959  -0.0660   0.0026   1.0000
  13.250   1.6272   0.03758   0.03192  -0.0644   0.0025   1.0000
  13.500   1.6267   0.04010   0.03455  -0.0630   0.0025   1.0000
  13.750   1.6246   0.04292   0.03748  -0.0620   0.0024   1.0000
  14.000   1.6217   0.04602   0.04070  -0.0613   0.0024   1.0000
  14.250   1.6172   0.04948   0.04429  -0.0609   0.0023   1.0000
  14.500   1.6111   0.05329   0.04822  -0.0608   0.0023   1.0000
  14.750   1.6037   0.05746   0.05251  -0.0610   0.0023   1.0000
  15.000   1.5951   0.06200   0.05718  -0.0616   0.0022   1.0000
  15.250   1.5857   0.06680   0.06210  -0.0625   0.0022   1.0000
  15.500   1.5731   0.07220   0.06763  -0.0636   0.0022   1.0000
  15.750   1.5615   0.07754   0.07310  -0.0649   0.0022   1.0000
  16.000   1.5475   0.08337   0.07905  -0.0664   0.0021   1.0000
  16.250   1.5330   0.08931   0.08511  -0.0680   0.0021   1.0000
  16.500   1.5175   0.09556   0.09148  -0.0699   0.0021   1.0000
  16.750   1.5033   0.10175   0.09779  -0.0719   0.0021   1.0000
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