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GOE 282 (DAIMLER XIII) AIRFOIL (goe282-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: GOE 282 (DAIMLER XIII) AIRFOIL (goe282-il)
Reynolds number: 500,000
Max Cl/Cd: 94.77 at α=3°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe282-il-500000-n5.txt
Download as CSV file: xf-goe282-il-500000-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 =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.3345   0.11822   0.11588  -0.0303   1.0000   0.0074
 -10.500  -0.3337   0.11470   0.11238  -0.0309   1.0000   0.0074
  -9.000  -0.4390   0.02273   0.01899  -0.1115   0.9752   0.0090
  -8.750  -0.4133   0.02008   0.01601  -0.1131   0.9710   0.0096
  -8.500  -0.3839   0.01865   0.01438  -0.1144   0.9682   0.0104
  -8.250  -0.3533   0.01748   0.01300  -0.1156   0.9660   0.0112
  -8.000  -0.3234   0.01642   0.01173  -0.1166   0.9631   0.0120
  -7.750  -0.2959   0.01548   0.01059  -0.1169   0.9582   0.0128
  -7.500  -0.2660   0.01485   0.00989  -0.1175   0.9547   0.0142
  -7.250  -0.2348   0.01444   0.00941  -0.1183   0.9516   0.0157
  -7.000  -0.2072   0.01400   0.00885  -0.1183   0.9456   0.0173
  -6.750  -0.1776   0.01371   0.00852  -0.1186   0.9403   0.0189
  -6.500  -0.1476   0.01361   0.00839  -0.1190   0.9357   0.0205
  -6.250  -0.1196   0.01334   0.00803  -0.1190   0.9296   0.0223
  -6.000  -0.0904   0.01310   0.00769  -0.1191   0.9242   0.0237
  -5.750  -0.0621   0.01268   0.00716  -0.1192   0.9183   0.0251
  -5.500  -0.0338   0.01237   0.00680  -0.1193   0.9116   0.0266
  -5.250  -0.0052   0.01220   0.00658  -0.1194   0.9056   0.0281
  -5.000   0.0229   0.01196   0.00627  -0.1193   0.8979   0.0296
  -4.750   0.0513   0.01172   0.00593  -0.1193   0.8902   0.0311
  -4.500   0.0794   0.01148   0.00560  -0.1192   0.8808   0.0321
  -4.250   0.1075   0.01129   0.00531  -0.1191   0.8712   0.0328
  -4.000   0.1355   0.01074   0.00465  -0.1191   0.8604   0.0340
  -3.750   0.1634   0.01032   0.00413  -0.1190   0.8472   0.0349
  -3.500   0.1913   0.01003   0.00375  -0.1189   0.8312   0.0358
  -3.250   0.2189   0.00981   0.00342  -0.1186   0.8088   0.0367
  -3.000   0.2459   0.00969   0.00314  -0.1182   0.7795   0.0379
  -2.750   0.2726   0.00965   0.00291  -0.1178   0.7491   0.0394
  -2.500   0.2996   0.00962   0.00272  -0.1175   0.7234   0.0409
  -2.250   0.3268   0.00961   0.00255  -0.1172   0.7013   0.0422
  -2.000   0.3543   0.00960   0.00241  -0.1170   0.6806   0.0436
  -1.750   0.3818   0.00958   0.00228  -0.1168   0.6582   0.0461
  -1.500   0.4090   0.00957   0.00215  -0.1166   0.6322   0.0514
  -1.250   0.4356   0.00964   0.00207  -0.1163   0.5994   0.0585
  -1.000   0.4622   0.00961   0.00206  -0.1161   0.5707   0.1013
  -0.750   0.4894   0.00969   0.00209  -0.1160   0.5520   0.1206
  -0.500   0.5171   0.00975   0.00210  -0.1159   0.5396   0.1315
  -0.250   0.5448   0.00982   0.00213  -0.1159   0.5290   0.1415
   0.250   0.6004   0.00993   0.00220  -0.1158   0.5101   0.1587
   0.500   0.6281   0.00999   0.00224  -0.1158   0.5016   0.1678
   0.750   0.6559   0.01003   0.00230  -0.1157   0.4927   0.1791
   1.000   0.6837   0.01010   0.00234  -0.1157   0.4840   0.1870
   1.250   0.7112   0.01017   0.00240  -0.1156   0.4740   0.1951
   1.500   0.7389   0.01022   0.00246  -0.1156   0.4635   0.2048
   2.000   0.7938   0.01036   0.00261  -0.1155   0.4418   0.2358
   2.250   0.8212   0.01040   0.00271  -0.1155   0.4293   0.2693
   2.500   0.8413   0.00918   0.00296  -0.1142   0.4166   0.8720
   3.000   0.8946   0.00944   0.00311  -0.1137   0.3778   1.0000
   3.250   0.9198   0.00980   0.00329  -0.1132   0.3448   1.0000
   3.500   0.9445   0.01021   0.00350  -0.1128   0.3129   1.0000
   3.750   0.9698   0.01056   0.00372  -0.1124   0.2903   1.0000
   4.000   0.9954   0.01087   0.00394  -0.1121   0.2729   1.0000
   4.250   1.0210   0.01117   0.00416  -0.1117   0.2592   1.0000
   4.500   1.0462   0.01150   0.00440  -0.1114   0.2440   1.0000
   4.750   1.0711   0.01185   0.00467  -0.1109   0.2277   1.0000
   5.000   1.0962   0.01217   0.00492  -0.1106   0.2155   1.0000
   5.250   1.1212   0.01250   0.00518  -0.1102   0.2034   1.0000
   5.500   1.1459   0.01283   0.00545  -0.1097   0.1894   1.0000
   5.750   1.1698   0.01324   0.00575  -0.1092   0.1651   1.0000
   6.000   1.1833   0.01470   0.00665  -0.1071   0.0794   1.0000
   6.250   1.2048   0.01532   0.00716  -0.1062   0.0609   1.0000
   6.500   1.2224   0.01630   0.00789  -0.1046   0.0211   1.0000
   6.750   1.2438   0.01687   0.00849  -0.1036   0.0141   1.0000
   7.000   1.2658   0.01737   0.00905  -0.1026   0.0122   1.0000
   7.250   1.2878   0.01782   0.00957  -0.1017   0.0111   1.0000
   7.500   1.3092   0.01831   0.01011  -0.1007   0.0101   1.0000
   7.750   1.3296   0.01885   0.01073  -0.0995   0.0092   1.0000
   8.000   1.3480   0.01954   0.01153  -0.0980   0.0085   1.0000
   8.250   1.3668   0.02014   0.01220  -0.0966   0.0081   1.0000
   8.500   1.3849   0.02074   0.01288  -0.0951   0.0077   1.0000
   8.750   1.4019   0.02138   0.01359  -0.0934   0.0072   1.0000
   9.000   1.4172   0.02204   0.01432  -0.0915   0.0067   1.0000
   9.250   1.4296   0.02279   0.01513  -0.0891   0.0063   1.0000
   9.500   1.4388   0.02379   0.01622  -0.0862   0.0060   1.0000
   9.750   1.4481   0.02480   0.01733  -0.0836   0.0059   1.0000
  10.000   1.4579   0.02581   0.01843  -0.0811   0.0057   1.0000
  10.250   1.4661   0.02696   0.01968  -0.0785   0.0055   1.0000
  10.500   1.4730   0.02823   0.02105  -0.0760   0.0053   1.0000
  10.750   1.4785   0.02966   0.02258  -0.0735   0.0051   1.0000
  11.000   1.4828   0.03124   0.02427  -0.0711   0.0050   1.0000
  11.250   1.4862   0.03297   0.02610  -0.0689   0.0048   1.0000
  11.500   1.4891   0.03484   0.02807  -0.0669   0.0047   1.0000
  11.750   1.4912   0.03688   0.03020  -0.0651   0.0046   1.0000
  12.000   1.4928   0.03909   0.03250  -0.0636   0.0044   1.0000
  12.250   1.4930   0.04157   0.03511  -0.0623   0.0043   1.0000
  12.500   1.4890   0.04466   0.03831  -0.0613   0.0042   1.0000
  12.750   1.4801   0.04852   0.04229  -0.0606   0.0041   1.0000
  13.000   1.4794   0.05161   0.04551  -0.0603   0.0040   1.0000
  13.250   1.4753   0.05523   0.04925  -0.0602   0.0040   1.0000
  13.500   1.4694   0.05923   0.05339  -0.0603   0.0039   1.0000
  13.750   1.4623   0.06355   0.05783  -0.0608   0.0038   1.0000
  14.000   1.4549   0.06801   0.06241  -0.0614   0.0038   1.0000
  14.250   1.4470   0.07264   0.06717  -0.0622   0.0037   1.0000
  14.500   1.4390   0.07736   0.07200  -0.0631   0.0037   1.0000
  14.750   1.4310   0.08213   0.07688  -0.0640   0.0036   1.0000
  15.000   1.4230   0.08690   0.08176  -0.0650   0.0036   1.0000
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