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GOE 279 (DAIMLER X) AIRFOIL (goe279-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 279 (DAIMLER X) AIRFOIL (goe279-il)
Reynolds number: 100,000
Max Cl/Cd: 58.35 at α=3.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe279-il-100000.txt
Download as CSV file: xf-goe279-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 279 (DAIMLER X) AIRFOIL                     
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.500  -0.3501   0.09431   0.08959  -0.0235   1.0000   0.0507
  -7.250  -0.3530   0.09216   0.08752  -0.0233   1.0000   0.0519
  -7.000  -0.3555   0.09005   0.08548  -0.0237   1.0000   0.0530
  -6.750  -0.3568   0.08809   0.08356  -0.0253   1.0000   0.0542
  -6.500  -0.3535   0.08655   0.08203  -0.0298   1.0000   0.0552
  -6.250  -0.3432   0.08515   0.08051  -0.0355   1.0000   0.0557
  -6.000  -0.3387   0.08081   0.07621  -0.0353   1.0000   0.0563
  -5.750  -0.3396   0.07647   0.07197  -0.0309   1.0000   0.0573
  -5.500  -0.3354   0.07338   0.06893  -0.0290   1.0000   0.0587
  -5.250  -0.3271   0.07049   0.06604  -0.0290   1.0000   0.0606
  -5.000  -0.3145   0.06755   0.06306  -0.0304   1.0000   0.0632
  -4.750  -0.2732   0.06667   0.06166  -0.0400   1.0000   0.0685
  -4.500  -0.2673   0.06115   0.05630  -0.0389   1.0000   0.0697
  -4.250  -0.2604   0.05782   0.05308  -0.0372   1.0000   0.0722
  -4.000  -0.2207   0.05778   0.05243  -0.0427   1.0000   0.0826
  -3.750  -0.2143   0.05204   0.04697  -0.0417   1.0000   0.0849
  -3.500  -0.1987   0.04936   0.04431  -0.0416   1.0000   0.0901
  -3.250  -0.1692   0.04668   0.04135  -0.0446   1.0000   0.0996
  -2.750  -0.1251   0.04186   0.03638  -0.0464   1.0000   0.1192
  -2.500  -0.0963   0.04024   0.03443  -0.0486   1.0000   0.1430
  -2.250  -0.0766   0.03780   0.03211  -0.0490   1.0000   0.1637
  -1.000   0.1891   0.02690   0.01938  -0.0746   0.9644   0.1903
  -0.750   0.2496   0.02520   0.01697  -0.0783   0.9578   0.1320
  -0.500   0.2954   0.02416   0.01546  -0.0804   0.9469   0.1136
  -0.250   0.3408   0.02338   0.01447  -0.0830   0.9364   0.1119
   0.000   0.3920   0.02204   0.01309  -0.0868   0.9290   0.1105
   0.250   0.4335   0.02110   0.01216  -0.0888   0.9171   0.1102
   0.500   0.4769   0.02005   0.01125  -0.0912   0.9063   0.1149
   0.750   0.5263   0.01906   0.01029  -0.0944   0.8986   0.1219
   1.000   0.5646   0.01837   0.00957  -0.0955   0.8848   0.1298
   1.250   0.6019   0.01764   0.00894  -0.0963   0.8705   0.1574
   1.500   0.6319   0.01537   0.00848  -0.0952   0.8560   1.0000
   1.750   0.6657   0.01501   0.00788  -0.0949   0.8392   1.0000
   2.000   0.6936   0.01479   0.00753  -0.0938   0.8170   1.0000
   2.250   0.7235   0.01450   0.00711  -0.0930   0.7950   1.0000
   2.500   0.7502   0.01433   0.00684  -0.0918   0.7672   1.0000
   2.750   0.7771   0.01420   0.00657  -0.0906   0.7363   1.0000
   3.000   0.8035   0.01415   0.00637  -0.0893   0.7009   1.0000
   3.250   0.8293   0.01427   0.00622  -0.0880   0.6626   1.0000
   3.500   0.8542   0.01464   0.00629  -0.0868   0.6241   1.0000
   3.750   0.8786   0.01514   0.00656  -0.0857   0.5885   1.0000
   4.000   0.9027   0.01567   0.00687  -0.0847   0.5567   1.0000
   4.250   0.9268   0.01617   0.00722  -0.0838   0.5286   1.0000
   4.500   0.9512   0.01667   0.00758  -0.0831   0.5050   1.0000
   4.750   0.9758   0.01716   0.00803  -0.0824   0.4838   1.0000
   5.000   1.0005   0.01766   0.00844  -0.0817   0.4652   1.0000
   5.250   1.0252   0.01818   0.00888  -0.0811   0.4480   1.0000
   5.500   1.0495   0.01870   0.00939  -0.0805   0.4305   1.0000
   5.750   1.0733   0.01921   0.00993  -0.0798   0.4125   1.0000
   6.000   1.0968   0.01974   0.01043  -0.0790   0.3944   1.0000
   6.250   1.1199   0.02030   0.01095  -0.0782   0.3765   1.0000
   6.500   1.1430   0.02091   0.01150  -0.0774   0.3589   1.0000
   6.750   1.1651   0.02152   0.01217  -0.0765   0.3404   1.0000
   7.000   1.1866   0.02213   0.01282  -0.0755   0.3214   1.0000
   7.250   1.2082   0.02276   0.01349  -0.0745   0.3037   1.0000
   7.500   1.2294   0.02339   0.01416  -0.0735   0.2868   1.0000
   7.750   1.2498   0.02395   0.01480  -0.0723   0.2703   1.0000
   8.000   1.2703   0.02454   0.01549  -0.0712   0.2552   1.0000
   8.250   1.2891   0.02503   0.01606  -0.0698   0.2391   1.0000
   8.500   1.3064   0.02547   0.01670  -0.0682   0.2204   1.0000
   8.750   1.3219   0.02595   0.01731  -0.0664   0.1988   1.0000
   9.000   1.3343   0.02676   0.01812  -0.0642   0.1706   1.0000
   9.250   1.3408   0.02844   0.01960  -0.0613   0.1378   1.0000
   9.500   1.3471   0.03048   0.02146  -0.0584   0.1165   1.0000
   9.750   1.3570   0.03228   0.02325  -0.0560   0.1036   1.0000
  10.000   1.3694   0.03407   0.02513  -0.0539   0.0951   1.0000
  10.250   1.3814   0.03584   0.02679  -0.0521   0.0883   1.0000
  10.500   1.3932   0.03735   0.02860  -0.0499   0.0823   1.0000
  10.750   1.4047   0.03902   0.03022  -0.0480   0.0776   1.0000
  11.000   1.4154   0.04099   0.03243  -0.0459   0.0732   1.0000
  11.250   1.4252   0.04283   0.03441  -0.0438   0.0693   1.0000
  11.500   1.4430   0.04552   0.03704  -0.0431   0.0654   1.0000
  11.750   1.4457   0.04784   0.03976  -0.0403   0.0629   1.0000
  12.000   1.4483   0.05034   0.04253  -0.0378   0.0603   1.0000
  12.250   1.4532   0.05311   0.04550  -0.0358   0.0583   1.0000
  12.500   1.4660   0.05697   0.04938  -0.0351   0.0558   1.0000
  12.750   1.4550   0.06053   0.05328  -0.0322   0.0550   1.0000
  13.000   1.4391   0.06394   0.05705  -0.0296   0.0544   1.0000
  13.250   1.4217   0.06788   0.06134  -0.0277   0.0540   1.0000
  13.500   1.4022   0.07235   0.06613  -0.0267   0.0537   1.0000
  13.750   1.3807   0.07742   0.07149  -0.0267   0.0536   1.0000
  14.000   1.3576   0.08314   0.07749  -0.0277   0.0536   1.0000
  14.250   1.3330   0.08961   0.08420  -0.0298   0.0539   1.0000
  14.500   1.3073   0.09687   0.09168  -0.0331   0.0542   1.0000
  14.750   1.2814   0.10482   0.09982  -0.0372   0.0547   1.0000
  15.000   1.2556   0.11345   0.10859  -0.0421   0.0552   1.0000
  15.250   1.0726   0.17430   0.16949  -0.0834   0.0779   1.0000
  15.500   1.0768   0.17881   0.17402  -0.0847   0.0772   1.0000
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