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GOE 282 (DAIMLER XIII) AIRFOIL (goe282-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 282 (DAIMLER XIII) AIRFOIL (goe282-il)
Reynolds number: 500,000
Max Cl/Cd: 102.51 at α=4°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe282-il-500000.txt
Download as CSV file: xf-goe282-il-500000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3269   0.10059   0.09843  -0.0276   1.0000   0.0224
  -8.500  -0.3334   0.09864   0.09652  -0.0258   1.0000   0.0229
  -8.250  -0.3423   0.09678   0.09471  -0.0238   1.0000   0.0234
  -8.000  -0.3412   0.09275   0.09070  -0.0281   0.9979   0.0249
  -7.750  -0.3249   0.08687   0.08482  -0.0378   0.9936   0.0254
  -7.500  -0.3039   0.08092   0.07886  -0.0462   0.9892   0.0255
  -7.250  -0.2790   0.07433   0.07224  -0.0559   0.9858   0.0255
  -7.000  -0.2616   0.06816   0.06605  -0.0621   0.9838   0.0265
  -6.750  -0.2400   0.06643   0.06431  -0.0639   0.9802   0.0274
  -6.500  -0.2129   0.06288   0.06074  -0.0696   0.9765   0.0295
  -6.250  -0.1636   0.02284   0.01881  -0.1086   0.9716   0.0255
  -6.000  -0.1292   0.01981   0.01546  -0.1119   0.9708   0.0275
  -5.750  -0.1017   0.01942   0.01505  -0.1120   0.9656   0.0291
  -5.500  -0.0670   0.01799   0.01334  -0.1138   0.9631   0.0309
  -5.250  -0.0313   0.01737   0.01249  -0.1153   0.9607   0.0325
  -5.000   0.0021   0.01505   0.00988  -0.1172   0.9586   0.0350
  -4.750   0.0339   0.01437   0.00912  -0.1180   0.9550   0.0367
  -4.500   0.0628   0.01372   0.00837  -0.1181   0.9491   0.0384
  -4.250   0.0950   0.01317   0.00770  -0.1188   0.9448   0.0404
  -4.000   0.1239   0.01271   0.00713  -0.1187   0.9387   0.0415
  -3.750   0.1528   0.01192   0.00621  -0.1187   0.9319   0.0426
  -3.500   0.1810   0.01094   0.00515  -0.1187   0.9250   0.0450
  -3.250   0.2089   0.01046   0.00462  -0.1184   0.9161   0.0467
  -3.000   0.2363   0.01007   0.00418  -0.1180   0.9055   0.0484
  -2.750   0.2640   0.00973   0.00378  -0.1176   0.8934   0.0503
  -2.500   0.2915   0.00948   0.00345  -0.1172   0.8797   0.0524
  -2.250   0.3190   0.00921   0.00310  -0.1168   0.8642   0.0543
  -2.000   0.3466   0.00889   0.00273  -0.1165   0.8465   0.0589
  -1.750   0.3741   0.00871   0.00246  -0.1161   0.8253   0.0648
  -1.500   0.4011   0.00847   0.00229  -0.1157   0.7976   0.1049
  -1.250   0.4276   0.00855   0.00230  -0.1152   0.7654   0.1399
  -1.000   0.4542   0.00871   0.00228  -0.1146   0.7362   0.1524
  -0.750   0.4811   0.00885   0.00230  -0.1143   0.7121   0.1622
  -0.500   0.5082   0.00893   0.00230  -0.1140   0.6909   0.1695
  -0.250   0.5355   0.00902   0.00230  -0.1138   0.6696   0.1767
   0.000   0.5626   0.00909   0.00230  -0.1136   0.6483   0.1849
   0.250   0.5898   0.00920   0.00231  -0.1134   0.6271   0.1939
   0.500   0.6169   0.00925   0.00233  -0.1132   0.6067   0.2048
   0.750   0.6440   0.00933   0.00236  -0.1130   0.5888   0.2165
   1.000   0.6712   0.00941   0.00238  -0.1128   0.5730   0.2283
   1.250   0.6985   0.00946   0.00243  -0.1127   0.5586   0.2464
   1.500   0.7259   0.00946   0.00250  -0.1127   0.5455   0.2849
   1.750   0.7464   0.00798   0.00263  -0.1112   0.5345   1.0000
   2.000   0.7737   0.00815   0.00270  -0.1111   0.5237   1.0000
   2.250   0.8010   0.00833   0.00279  -0.1109   0.5130   1.0000
   2.500   0.8285   0.00847   0.00287  -0.1108   0.5023   1.0000
   2.750   0.8558   0.00863   0.00297  -0.1107   0.4916   1.0000
   3.000   0.8828   0.00880   0.00308  -0.1105   0.4780   1.0000
   3.250   0.9095   0.00897   0.00319  -0.1103   0.4601   1.0000
   3.500   0.9360   0.00917   0.00330  -0.1100   0.4402   1.0000
   3.750   0.9623   0.00939   0.00342  -0.1097   0.4197   1.0000
   4.000   0.9882   0.00964   0.00358  -0.1094   0.3954   1.0000
   4.250   1.0134   0.00997   0.00376  -0.1090   0.3663   1.0000
   4.500   1.0375   0.01040   0.00400  -0.1084   0.3335   1.0000
   4.750   1.0615   0.01085   0.00428  -0.1078   0.3040   1.0000
   5.000   1.0861   0.01124   0.00456  -0.1073   0.2822   1.0000
   5.250   1.1105   0.01164   0.00485  -0.1068   0.2633   1.0000
   5.500   1.1354   0.01198   0.00512  -0.1064   0.2496   1.0000
   5.750   1.1602   0.01231   0.00541  -0.1059   0.2363   1.0000
   6.000   1.1847   0.01267   0.00569  -0.1055   0.2219   1.0000
   6.250   1.2089   0.01303   0.00599  -0.1049   0.2065   1.0000
   6.500   1.2326   0.01344   0.00630  -0.1044   0.1883   1.0000
   6.750   1.2530   0.01417   0.00674  -0.1033   0.1372   1.0000
   7.000   1.2654   0.01567   0.00776  -0.1011   0.0723   1.0000
   7.250   1.2860   0.01632   0.00829  -0.1000   0.0553   1.0000
   7.500   1.3053   0.01706   0.00888  -0.0987   0.0351   1.0000
   7.750   1.3223   0.01800   0.00973  -0.0970   0.0180   1.0000
   8.000   1.3433   0.01851   0.01032  -0.0958   0.0162   1.0000
   8.250   1.3632   0.01909   0.01100  -0.0946   0.0153   1.0000
   8.500   1.3819   0.01974   0.01176  -0.0931   0.0146   1.0000
   8.750   1.3990   0.02047   0.01260  -0.0913   0.0139   1.0000
   9.000   1.4140   0.02130   0.01355  -0.0893   0.0134   1.0000
   9.250   1.4255   0.02229   0.01466  -0.0867   0.0130   1.0000
   9.500   1.4310   0.02348   0.01596  -0.0831   0.0126   1.0000
   9.750   1.4353   0.02478   0.01736  -0.0796   0.0124   1.0000
  10.000   1.4456   0.02574   0.01840  -0.0771   0.0122   1.0000
  10.250   1.4540   0.02684   0.01960  -0.0745   0.0119   1.0000
  10.500   1.4604   0.02814   0.02098  -0.0719   0.0115   1.0000
  10.750   1.4646   0.02965   0.02260  -0.0692   0.0112   1.0000
  11.000   1.4669   0.03138   0.02443  -0.0666   0.0110   1.0000
  11.250   1.4680   0.03331   0.02646  -0.0641   0.0109   1.0000
  11.500   1.4680   0.03546   0.02870  -0.0619   0.0107   1.0000
  11.750   1.4672   0.03780   0.03115  -0.0600   0.0106   1.0000
  12.000   1.4656   0.04038   0.03382  -0.0583   0.0105   1.0000
  12.250   1.4636   0.04317   0.03670  -0.0570   0.0104   1.0000
  12.500   1.4611   0.04612   0.03974  -0.0559   0.0103   1.0000
  12.750   1.4587   0.04919   0.04289  -0.0550   0.0102   1.0000
  13.000   1.4564   0.05232   0.04610  -0.0543   0.0101   1.0000
  13.250   1.4548   0.05540   0.04928  -0.0536   0.0101   1.0000
  13.500   1.4538   0.05844   0.05239  -0.0530   0.0100   1.0000
  13.750   1.4539   0.06138   0.05540  -0.0524   0.0100   1.0000
  14.000   1.4552   0.06418   0.05827  -0.0516   0.0100   1.0000
  14.250   1.4567   0.06706   0.06125  -0.0511   0.0101   1.0000
  14.500   1.4579   0.07004   0.06435  -0.0507   0.0102   1.0000
  14.750   1.4589   0.07307   0.06749  -0.0504   0.0103   1.0000
  15.000   1.4603   0.07601   0.07052  -0.0499   0.0102   1.0000
  15.250   1.4629   0.07875   0.07333  -0.0494   0.0101   1.0000
  15.500   1.4646   0.08171   0.07638  -0.0491   0.0101   1.0000
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