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GOE 282 (DAIMLER XIII) AIRFOIL (goe282-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 282 (DAIMLER XIII) AIRFOIL (goe282-il)
Reynolds number: 1,000,000
Max Cl/Cd: 118.34 at α=3°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe282-il-1000000.txt
Download as CSV file: xf-goe282-il-1000000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.3311   0.11336   0.11171  -0.0298   1.0000   0.0130
 -10.000  -0.3284   0.11079   0.10916  -0.0299   1.0000   0.0134
  -9.750  -0.5568   0.02248   0.01956  -0.1042   0.9872   0.0113
  -9.500  -0.5260   0.02025   0.01704  -0.1066   0.9861   0.0117
  -9.250  -0.4940   0.01888   0.01547  -0.1085   0.9852   0.0119
  -9.000  -0.4633   0.01640   0.01265  -0.1108   0.9845   0.0129
  -8.750  -0.4295   0.01584   0.01204  -0.1123   0.9839   0.0135
  -8.500  -0.3977   0.01537   0.01151  -0.1134   0.9824   0.0141
  -8.250  -0.3684   0.01481   0.01084  -0.1139   0.9795   0.0148
  -8.000  -0.3372   0.01430   0.01022  -0.1147   0.9772   0.0154
  -7.750  -0.3062   0.01324   0.00902  -0.1158   0.9751   0.0165
  -7.500  -0.2739   0.01315   0.00894  -0.1167   0.9729   0.0174
  -7.250  -0.2420   0.01310   0.00889  -0.1174   0.9707   0.0184
  -7.000  -0.2151   0.01288   0.00860  -0.1171   0.9658   0.0193
  -6.750  -0.1862   0.01274   0.00840  -0.1172   0.9616   0.0199
  -6.500  -0.1580   0.01174   0.00728  -0.1175   0.9581   0.0214
  -6.250  -0.1302   0.01165   0.00719  -0.1174   0.9533   0.0223
  -6.000  -0.1024   0.01151   0.00702  -0.1172   0.9481   0.0235
  -5.750  -0.0740   0.01142   0.00688  -0.1171   0.9436   0.0246
  -5.500  -0.0461   0.01138   0.00680  -0.1169   0.9376   0.0254
  -5.250  -0.0192   0.01033   0.00559  -0.1168   0.9316   0.0270
  -5.000   0.0088   0.01008   0.00532  -0.1168   0.9256   0.0281
  -4.750   0.0366   0.00994   0.00515  -0.1166   0.9186   0.0294
  -4.500   0.0647   0.00970   0.00485  -0.1165   0.9118   0.0306
  -4.250   0.0926   0.00947   0.00456  -0.1163   0.9034   0.0317
  -4.000   0.1207   0.00939   0.00443  -0.1161   0.8940   0.0325
  -3.750   0.1483   0.00891   0.00383  -0.1159   0.8827   0.0334
  -3.500   0.1760   0.00840   0.00323  -0.1158   0.8695   0.0351
  -3.250   0.2039   0.00819   0.00296  -0.1156   0.8543   0.0366
  -3.000   0.2319   0.00801   0.00271  -0.1155   0.8356   0.0378
  -2.750   0.2594   0.00789   0.00248  -0.1152   0.8113   0.0392
  -2.500   0.2865   0.00785   0.00227  -0.1148   0.7787   0.0405
  -2.250   0.3134   0.00789   0.00214  -0.1145   0.7455   0.0416
  -2.000   0.3406   0.00789   0.00197  -0.1142   0.7162   0.0432
  -1.750   0.3681   0.00783   0.00178  -0.1140   0.6910   0.0471
  -1.500   0.3961   0.00780   0.00168  -0.1139   0.6694   0.0512
  -1.250   0.4239   0.00777   0.00157  -0.1138   0.6477   0.0622
  -1.000   0.4517   0.00766   0.00157  -0.1139   0.6242   0.1199
  -0.750   0.4793   0.00776   0.00160  -0.1138   0.5999   0.1339
  -0.500   0.5070   0.00785   0.00163  -0.1137   0.5783   0.1440
  -0.250   0.5348   0.00796   0.00165  -0.1136   0.5609   0.1494
   0.000   0.5627   0.00801   0.00167  -0.1136   0.5467   0.1570
   0.250   0.5907   0.00809   0.00170  -0.1136   0.5343   0.1628
   0.500   0.6187   0.00815   0.00173  -0.1136   0.5232   0.1706
   1.000   0.6749   0.00825   0.00182  -0.1136   0.5041   0.1905
   1.250   0.7029   0.00830   0.00187  -0.1136   0.4953   0.2026
   1.500   0.7311   0.00833   0.00191  -0.1137   0.4863   0.2165
   1.750   0.7592   0.00836   0.00197  -0.1137   0.4775   0.2383
   2.000   0.7871   0.00834   0.00205  -0.1138   0.4676   0.2921
   2.250   0.8084   0.00694   0.00222  -0.1127   0.4557   1.0000
   2.500   0.8357   0.00712   0.00229  -0.1126   0.4362   1.0000
   2.750   0.8630   0.00730   0.00236  -0.1125   0.4131   1.0000
   3.000   0.8899   0.00752   0.00247  -0.1123   0.3914   1.0000
   3.250   0.9164   0.00779   0.00259  -0.1121   0.3647   1.0000
   3.500   0.9425   0.00810   0.00275  -0.1118   0.3360   1.0000
   3.750   0.9679   0.00848   0.00295  -0.1115   0.3046   1.0000
   4.000   0.9933   0.00885   0.00317  -0.1111   0.2760   1.0000
   4.250   1.0192   0.00917   0.00337  -0.1108   0.2555   1.0000
   4.500   1.0454   0.00943   0.00356  -0.1106   0.2420   1.0000
   4.750   1.0715   0.00970   0.00375  -0.1104   0.2302   1.0000
   5.000   1.0976   0.00996   0.00395  -0.1101   0.2184   1.0000
   5.250   1.1238   0.01020   0.00414  -0.1099   0.2070   1.0000
   5.500   1.1496   0.01047   0.00434  -0.1096   0.1939   1.0000
   5.750   1.1744   0.01084   0.00460  -0.1092   0.1732   1.0000
   6.000   1.1893   0.01225   0.00544  -0.1073   0.0825   1.0000
   6.250   1.2114   0.01287   0.00591  -0.1064   0.0594   1.0000
   6.500   1.2307   0.01376   0.00655  -0.1051   0.0229   1.0000
   6.750   1.2537   0.01426   0.00705  -0.1043   0.0148   1.0000
   7.000   1.2773   0.01467   0.00750  -0.1036   0.0132   1.0000
   7.250   1.3008   0.01506   0.00795  -0.1028   0.0122   1.0000
   7.500   1.3239   0.01547   0.00840  -0.1021   0.0115   1.0000
   7.750   1.3461   0.01594   0.00892  -0.1012   0.0109   1.0000
   8.000   1.3672   0.01649   0.00953  -0.1001   0.0103   1.0000
   8.250   1.3865   0.01719   0.01029  -0.0987   0.0097   1.0000
   8.500   1.4021   0.01817   0.01138  -0.0967   0.0092   1.0000
   8.750   1.4225   0.01866   0.01191  -0.0955   0.0090   1.0000
   9.000   1.4416   0.01922   0.01252  -0.0942   0.0086   1.0000
   9.250   1.4592   0.01983   0.01318  -0.0926   0.0082   1.0000
   9.500   1.4750   0.02052   0.01393  -0.0907   0.0078   1.0000
   9.750   1.4879   0.02129   0.01475  -0.0883   0.0075   1.0000
  10.000   1.4974   0.02213   0.01565  -0.0853   0.0073   1.0000
  10.250   1.5048   0.02314   0.01674  -0.0822   0.0071   1.0000
  10.500   1.5083   0.02445   0.01813  -0.0787   0.0069   1.0000
  10.750   1.5046   0.02629   0.02008  -0.0745   0.0067   1.0000
  11.000   1.4942   0.02874   0.02264  -0.0700   0.0066   1.0000
  11.250   1.5036   0.02991   0.02388  -0.0681   0.0065   1.0000
  11.500   1.5107   0.03130   0.02535  -0.0662   0.0064   1.0000
  11.750   1.5160   0.03291   0.02704  -0.0642   0.0063   1.0000
  12.000   1.5191   0.03481   0.02902  -0.0623   0.0062   1.0000
  12.250   1.5211   0.03690   0.03120  -0.0606   0.0061   1.0000
  12.500   1.5216   0.03927   0.03367  -0.0592   0.0060   1.0000
  12.750   1.5213   0.04187   0.03636  -0.0580   0.0059   1.0000
  13.000   1.5200   0.04470   0.03929  -0.0570   0.0058   1.0000
  13.250   1.5181   0.04773   0.04241  -0.0563   0.0057   1.0000
  13.500   1.5162   0.05089   0.04566  -0.0559   0.0056   1.0000
  13.750   1.5148   0.05409   0.04895  -0.0557   0.0054   1.0000
  14.000   1.5123   0.05752   0.05247  -0.0558   0.0053   1.0000
  14.250   1.5093   0.06113   0.05617  -0.0560   0.0052   1.0000
  14.500   1.5061   0.06490   0.06002  -0.0564   0.0051   1.0000
  14.750   1.5017   0.06887   0.06408  -0.0570   0.0051   1.0000
  15.000   1.4970   0.07297   0.06827  -0.0577   0.0050   1.0000
  15.250   1.4916   0.07722   0.07261  -0.0585   0.0049   1.0000
  15.500   1.4857   0.08155   0.07702  -0.0594   0.0049   1.0000
  15.750   1.4798   0.08582   0.08138  -0.0601   0.0048   1.0000
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