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GOE 281 (DAIMLER XII) AIRFOIL (goe281-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: GOE 281 (DAIMLER XII) AIRFOIL (goe281-il)
Reynolds number: 50,000
Max Cl/Cd: 36.68 at α=6.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe281-il-50000.txt
Download as CSV file: xf-goe281-il-50000.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 =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.3453   0.10716   0.10051  -0.0225   1.0000   0.1357
  -8.000  -0.3522   0.10601   0.09948  -0.0236   1.0000   0.1409
  -7.750  -0.3660   0.10602   0.09966  -0.0265   1.0000   0.1424
  -7.500  -0.3473   0.09996   0.09359  -0.0225   1.0000   0.1532
  -7.250  -0.3596   0.09974   0.09353  -0.0261   1.0000   0.1567
  -7.000  -0.3462   0.09459   0.08838  -0.0221   1.0000   0.1654
  -6.750  -0.3558   0.09411   0.08803  -0.0261   1.0000   0.1713
  -6.500  -0.3459   0.08948   0.08346  -0.0219   1.0000   0.1799
  -6.250  -0.3524   0.08858   0.08265  -0.0266   1.0000   0.1871
  -6.000  -0.3459   0.08484   0.07898  -0.0225   1.0000   0.1989
  -5.750  -0.3431   0.08178   0.07600  -0.0209   1.0000   0.2084
  -5.250  -0.3394   0.07676   0.07110  -0.0205   1.0000   0.2347
  -5.000  -0.3364   0.07417   0.06859  -0.0186   1.0000   0.2521
  -4.750  -0.3333   0.07224   0.06668  -0.0200   1.0000   0.2766
  -4.500  -0.3316   0.06932   0.06387  -0.0149   1.0000   0.2984
  -4.250   0.0556   0.04103   0.03449  -0.0314   1.0000   1.0000
  -4.000   0.0639   0.03943   0.03294  -0.0317   1.0000   1.0000
  -3.750   0.0713   0.03795   0.03155  -0.0318   1.0000   1.0000
  -3.500   0.0773   0.03661   0.03029  -0.0315   1.0000   1.0000
  -3.250   0.0561   0.03666   0.03052  -0.0249   1.0000   0.9903
  -3.000  -0.0008   0.03829   0.03242  -0.0106   1.0000   0.9647
  -2.750  -0.0525   0.03934   0.03373   0.0016   1.0000   0.9432
  -2.500  -0.1048   0.04022   0.03487   0.0134   1.0000   0.9263
  -2.250  -0.1539   0.04064   0.03552   0.0238   1.0000   0.9089
  -2.000  -0.2074   0.04092   0.03602   0.0346   1.0000   0.8919
  -1.250   0.0180   0.03649   0.02795  -0.0575   1.0000   0.2142
  -1.000   0.0483   0.03522   0.02627  -0.0587   1.0000   0.1960
  -0.750   0.0775   0.03434   0.02494  -0.0595   1.0000   0.1794
  -0.500   0.1041   0.03383   0.02402  -0.0599   1.0000   0.1681
  -0.250   0.1370   0.03340   0.02317  -0.0614   0.9976   0.1591
   0.000   0.1947   0.03286   0.02226  -0.0672   0.9859   0.1533
   0.250   0.2489   0.03257   0.02165  -0.0721   0.9733   0.1532
   0.500   0.3005   0.03245   0.02129  -0.0766   0.9598   0.1579
   0.750   0.3505   0.03224   0.02101  -0.0810   0.9456   0.1620
   1.000   0.3992   0.03222   0.02092  -0.0851   0.9305   0.1705
   1.250   0.4487   0.03207   0.02090  -0.0894   0.9149   0.1922
   1.500   0.4894   0.03024   0.02099  -0.0916   0.8996   1.0000
   1.750   0.5304   0.03076   0.02107  -0.0937   0.8816   1.0000
   2.000   0.5677   0.03124   0.02127  -0.0953   0.8625   1.0000
   2.250   0.6129   0.03139   0.02122  -0.0979   0.8444   1.0000
   2.500   0.6647   0.03107   0.02075  -0.1009   0.8271   1.0000
   2.750   0.6963   0.03120   0.02080  -0.1008   0.8059   1.0000
   3.000   0.7352   0.03093   0.02051  -0.1013   0.7877   1.0000
   3.250   0.7735   0.03061   0.02016  -0.1016   0.7708   1.0000
   3.500   0.8101   0.03030   0.01985  -0.1016   0.7546   1.0000
   3.750   0.8354   0.03061   0.02018  -0.1004   0.7350   1.0000
   4.000   0.8648   0.03063   0.02027  -0.0994   0.7166   1.0000
   4.250   0.8968   0.03042   0.02009  -0.0985   0.6990   1.0000
   4.500   0.9299   0.03005   0.01974  -0.0975   0.6816   1.0000
   4.750   0.9518   0.03056   0.02036  -0.0958   0.6596   1.0000
   5.000   0.9824   0.03030   0.02012  -0.0943   0.6395   1.0000
   5.250   1.0063   0.03053   0.02040  -0.0924   0.6155   1.0000
   5.500   1.0351   0.03020   0.02005  -0.0905   0.5916   1.0000
   5.750   1.0598   0.03021   0.02011  -0.0885   0.5657   1.0000
   6.000   1.0822   0.03048   0.02043  -0.0866   0.5394   1.0000
   6.250   1.1058   0.03076   0.02074  -0.0849   0.5144   1.0000
   6.500   1.1327   0.03088   0.02079  -0.0834   0.4915   1.0000
   6.750   1.1544   0.03165   0.02169  -0.0819   0.4676   1.0000
   7.000   1.1787   0.03249   0.02253  -0.0807   0.4464   1.0000
   7.250   1.2001   0.03360   0.02374  -0.0793   0.4247   1.0000
   7.500   1.2217   0.03427   0.02440  -0.0777   0.4011   1.0000
   7.750   1.2424   0.03432   0.02432  -0.0757   0.3746   1.0000
   8.000   1.2579   0.03481   0.02499  -0.0736   0.3510   1.0000
   8.250   1.2785   0.03519   0.02540  -0.0721   0.3329   1.0000
   8.500   1.2924   0.03566   0.02609  -0.0699   0.3134   1.0000
   8.750   1.3088   0.03619   0.02682  -0.0680   0.2975   1.0000
   9.000   1.3203   0.03603   0.02666  -0.0653   0.2762   1.0000
   9.250   1.3288   0.03664   0.02756  -0.0625   0.2571   1.0000
   9.500   1.3326   0.03727   0.02828  -0.0592   0.2346   1.0000
   9.750   1.3288   0.03842   0.02955  -0.0553   0.2080   1.0000
  10.000   1.3219   0.04008   0.03130  -0.0513   0.1800   1.0000
  10.250   1.3101   0.04231   0.03349  -0.0473   0.1515   1.0000
  10.500   1.2988   0.04530   0.03629  -0.0442   0.1269   1.0000
  10.750   1.2898   0.04857   0.03937  -0.0418   0.1111   1.0000
  11.000   1.2852   0.05180   0.04257  -0.0400   0.0991   1.0000
  11.250   1.2839   0.05493   0.04578  -0.0384   0.0906   1.0000
  11.500   1.2830   0.05798   0.04878  -0.0370   0.0849   1.0000
  11.750   1.2904   0.06080   0.05183  -0.0353   0.0801   1.0000
  12.000   1.2980   0.06360   0.05485  -0.0337   0.0765   1.0000
  12.250   1.3111   0.06610   0.05733  -0.0320   0.0734   1.0000
  12.500   1.3214   0.06958   0.06108  -0.0306   0.0717   1.0000
  12.750   1.3191   0.07393   0.06582  -0.0299   0.0708   1.0000
  13.000   1.3098   0.07887   0.07110  -0.0298   0.0703   1.0000
  13.250   1.2952   0.08442   0.07696  -0.0305   0.0702   1.0000
  13.500   1.2767   0.09064   0.08347  -0.0321   0.0704   1.0000
  13.750   1.2552   0.09760   0.09068  -0.0347   0.0709   1.0000
  14.000   1.2322   0.10525   0.09853  -0.0381   0.0715   1.0000
  14.250   1.2092   0.11347   0.10690  -0.0423   0.0722   1.0000
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