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GOE 281 (DAIMLER XII) AIRFOIL (goe281-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 281 (DAIMLER XII) AIRFOIL (goe281-il)
Reynolds number: 200,000
Max Cl/Cd: 75.23 at α=5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe281-il-200000-n5.txt
Download as CSV file: xf-goe281-il-200000-n5.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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.3308   0.09716   0.09389  -0.0293   1.0000   0.0203
  -7.750  -0.3373   0.09509   0.09189  -0.0286   1.0000   0.0203
  -7.500  -0.3400   0.09258   0.08943  -0.0288   1.0000   0.0203
  -7.250  -0.3328   0.08902   0.08590  -0.0316   0.9981   0.0203
  -7.000  -0.3088   0.08378   0.08062  -0.0389   0.9933   0.0204
  -6.750  -0.2833   0.07845   0.07526  -0.0462   0.9881   0.0204
  -6.500  -0.2562   0.07306   0.06981  -0.0533   0.9833   0.0204
  -6.250  -0.2398   0.06863   0.06539  -0.0552   0.9790   0.0209
  -6.000  -0.2179   0.06616   0.06290  -0.0569   0.9761   0.0234
  -5.750  -0.1690   0.06048   0.05700  -0.0703   0.9679   0.0265
  -5.500  -0.1334   0.05518   0.05151  -0.0772   0.9621   0.0267
  -5.250  -0.1010   0.05022   0.04633  -0.0822   0.9544   0.0267
  -4.750  -0.0559   0.04299   0.03902  -0.0867   0.9389   0.0294
  -4.500  -0.0265   0.03977   0.03560  -0.0892   0.9296   0.0316
  -4.250   0.0183   0.03721   0.03235  -0.0924   0.9221   0.0355
  -4.000   0.0392   0.01582   0.01140  -0.0890   0.8795   0.0387
  -3.750   0.0720   0.01513   0.01014  -0.0894   0.8667   0.0464
  -3.500   0.0929   0.01155   0.00645  -0.0907   0.8564   0.0485
  -3.250   0.1170   0.01010   0.00488  -0.0910   0.8448   0.0511
  -2.750   0.1813   0.02206   0.01574  -0.0964   0.8534   0.0433
  -2.500   0.2105   0.02005   0.01334  -0.0962   0.8398   0.0397
  -2.250   0.2392   0.01866   0.01159  -0.0959   0.8251   0.0388
  -2.000   0.2668   0.01782   0.01052  -0.0958   0.8104   0.0408
  -1.750   0.2952   0.01679   0.00920  -0.0955   0.7973   0.0395
  -1.500   0.3235   0.01593   0.00804  -0.0951   0.7843   0.0382
  -1.250   0.3514   0.01527   0.00716  -0.0948   0.7710   0.0376
  -1.000   0.3790   0.01469   0.00642  -0.0945   0.7576   0.0375
  -0.750   0.4065   0.01418   0.00579  -0.0943   0.7445   0.0376
  -0.500   0.4339   0.01373   0.00524  -0.0941   0.7322   0.0380
  -0.250   0.4611   0.01335   0.00480  -0.0938   0.7191   0.0386
   0.000   0.4881   0.01308   0.00449  -0.0936   0.7047   0.0408
   0.500   0.5420   0.01264   0.00390  -0.0931   0.6741   0.0417
   0.750   0.5691   0.01250   0.00368  -0.0929   0.6593   0.0416
   1.000   0.5961   0.01241   0.00351  -0.0927   0.6440   0.0417
   1.250   0.6232   0.01238   0.00339  -0.0925   0.6288   0.0419
   1.500   0.6502   0.01238   0.00330  -0.0923   0.6140   0.0423
   1.750   0.6774   0.01240   0.00324  -0.0921   0.6000   0.0431
   2.000   0.7045   0.01244   0.00322  -0.0919   0.5851   0.0441
   2.250   0.7315   0.01249   0.00322  -0.0917   0.5696   0.0458
   2.500   0.7585   0.01255   0.00326  -0.0916   0.5514   0.0494
   2.750   0.7823   0.01144   0.00349  -0.0914   0.5301   0.6478
   3.250   0.8325   0.01127   0.00357  -0.0899   0.4757   1.0000
   3.500   0.8575   0.01160   0.00373  -0.0894   0.4530   1.0000
   3.750   0.8829   0.01192   0.00393  -0.0890   0.4343   1.0000
   4.000   0.9082   0.01225   0.00415  -0.0887   0.4175   1.0000
   4.250   0.9337   0.01256   0.00440  -0.0883   0.4023   1.0000
   4.500   0.9593   0.01286   0.00467  -0.0880   0.3885   1.0000
   4.750   0.9849   0.01314   0.00495  -0.0878   0.3753   1.0000
   5.000   1.0104   0.01343   0.00523  -0.0874   0.3607   1.0000
   5.250   1.0348   0.01380   0.00554  -0.0870   0.3332   1.0000
   5.500   1.0573   0.01433   0.00585  -0.0863   0.2885   1.0000
   5.750   1.0788   0.01499   0.00628  -0.0855   0.2496   1.0000
   6.000   1.1007   0.01563   0.00677  -0.0848   0.2211   1.0000
   6.250   1.1228   0.01624   0.00729  -0.0841   0.1947   1.0000
   6.500   1.1441   0.01693   0.00783  -0.0833   0.1609   1.0000
   6.750   1.1623   0.01795   0.00853  -0.0822   0.1170   1.0000
   7.000   1.1763   0.01943   0.00956  -0.0805   0.0470   1.0000
   7.250   1.1920   0.02072   0.01072  -0.0788   0.0212   1.0000
   7.500   1.2124   0.02143   0.01160  -0.0776   0.0191   1.0000
   7.750   1.2314   0.02225   0.01258  -0.0763   0.0170   1.0000
   8.000   1.2484   0.02326   0.01375  -0.0748   0.0149   1.0000
   8.250   1.2637   0.02441   0.01512  -0.0730   0.0138   1.0000
   8.500   1.2766   0.02566   0.01658  -0.0709   0.0132   1.0000
   8.750   1.2900   0.02675   0.01786  -0.0689   0.0128   1.0000
   9.000   1.3010   0.02790   0.01916  -0.0666   0.0123   1.0000
   9.250   1.3083   0.02908   0.02048  -0.0638   0.0116   1.0000
   9.500   1.3140   0.03042   0.02194  -0.0610   0.0109   1.0000
   9.750   1.3175   0.03199   0.02363  -0.0583   0.0105   1.0000
  10.000   1.3194   0.03379   0.02553  -0.0556   0.0102   1.0000
  10.250   1.3205   0.03576   0.02761  -0.0532   0.0099   1.0000
  10.500   1.3213   0.03790   0.02985  -0.0510   0.0097   1.0000
  10.750   1.3218   0.04020   0.03224  -0.0492   0.0095   1.0000
  11.000   1.3224   0.04265   0.03480  -0.0475   0.0093   1.0000
  11.250   1.3234   0.04519   0.03742  -0.0459   0.0091   1.0000
  11.500   1.3256   0.04779   0.04006  -0.0444   0.0090   1.0000
  11.750   1.3310   0.05032   0.04263  -0.0427   0.0088   1.0000
  12.000   1.3397   0.05292   0.04528  -0.0410   0.0086   1.0000
  12.250   1.3410   0.05541   0.04799  -0.0403   0.0084   1.0000
  12.500   1.3416   0.05812   0.05091  -0.0397   0.0082   1.0000
  12.750   1.3414   0.06105   0.05405  -0.0393   0.0079   1.0000
  13.000   1.3406   0.06420   0.05740  -0.0391   0.0076   1.0000
  13.250   1.3387   0.06759   0.06098  -0.0389   0.0074   1.0000
  13.500   1.3357   0.07126   0.06484  -0.0388   0.0073   1.0000
  13.750   1.3310   0.07520   0.06901  -0.0391   0.0072   1.0000
  14.000   1.3246   0.07945   0.07346  -0.0396   0.0072   1.0000
  14.250   1.3168   0.08402   0.07822  -0.0406   0.0071   1.0000
  14.500   1.3079   0.08893   0.08333  -0.0419   0.0071   1.0000
  14.750   1.2979   0.09416   0.08877  -0.0437   0.0071   1.0000
  15.000   1.2871   0.09977   0.09457  -0.0460   0.0070   1.0000
  15.250   1.2758   0.10574   0.10074  -0.0487   0.0070   1.0000
  15.500   1.2640   0.11204   0.10723  -0.0518   0.0070   1.0000
  15.750   1.2518   0.11869   0.11406  -0.0554   0.0071   1.0000
  16.000   1.2393   0.12566   0.12121  -0.0594   0.0071   1.0000
  16.250   1.2269   0.13296   0.12868  -0.0637   0.0071   1.0000
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