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GOE 526 AIRFOIL (goe526-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: GOE 526 AIRFOIL (goe526-il)
Reynolds number: 50,000
Max Cl/Cd: 24.83 at α=10.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe526-il-50000.txt
Download as CSV file: xf-goe526-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 526 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
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.2886   0.12150   0.11392  -0.0343   1.0000   0.2069
 -10.000  -0.3025   0.12121   0.11374  -0.0346   1.0000   0.2133
  -9.750  -0.3213   0.12069   0.11339  -0.0348   1.0000   0.2156
  -9.500  -0.2888   0.11443   0.10708  -0.0328   1.0000   0.2221
  -9.250  -0.2929   0.11279   0.10553  -0.0319   1.0000   0.2287
  -9.000  -0.3284   0.11442   0.10737  -0.0311   1.0000   0.2326
  -8.750  -0.3046   0.10875   0.10171  -0.0294   1.0000   0.2371
  -8.500  -0.3019   0.10649   0.09952  -0.0273   1.0000   0.2440
  -8.250  -0.3293   0.10687   0.10007  -0.0250   1.0000   0.2496
  -8.000  -0.3757   0.10874   0.10216  -0.0215   1.0000   0.2511
  -7.750  -0.3300   0.10203   0.09539  -0.0199   1.0000   0.2609
  -7.500  -0.3579   0.10218   0.09568  -0.0166   1.0000   0.2669
  -7.250  -0.4023   0.10331   0.09699  -0.0126   1.0000   0.2688
  -7.000  -0.3701   0.09828   0.09194  -0.0109   1.0000   0.2793
  -6.750  -0.4024   0.09833   0.09213  -0.0072   1.0000   0.2849
  -6.500  -0.4541   0.09925   0.09322  -0.0045   1.0000   0.2874
  -6.250  -0.4204   0.09453   0.08848  -0.0012   1.0000   0.2984
  -6.000  -0.4676   0.09490   0.08898   0.0001   1.0000   0.3054
  -5.750  -0.4457   0.09094   0.08505   0.0038   1.0000   0.3149
  -5.500  -0.4785   0.08994   0.08413   0.0045   1.0000   0.3255
  -5.250  -0.4664   0.08709   0.08132   0.0083   1.0000   0.3373
  -5.000  -0.4725   0.08471   0.07900   0.0105   1.0000   0.3491
  -4.750  -0.4816   0.08261   0.07695   0.0126   1.0000   0.3650
  -4.500  -0.4854   0.08044   0.07483   0.0152   1.0000   0.3831
  -4.250  -0.4841   0.07825   0.07270   0.0190   1.0000   0.4046
  -4.000  -0.4955   0.07670   0.07120   0.0219   1.0000   0.4357
  -3.750  -0.4866   0.07431   0.06888   0.0277   1.0000   0.4631
  -3.500  -0.4873   0.07250   0.06715   0.0335   1.0000   0.5012
  -2.750  -0.3734   0.05058   0.04260  -0.0169   1.0000   0.2129
  -2.500  -0.3558   0.04813   0.03996  -0.0168   1.0000   0.2093
  -2.250  -0.3357   0.04563   0.03707  -0.0170   1.0000   0.2037
  -2.000  -0.3164   0.04382   0.03491  -0.0169   1.0000   0.2037
  -1.750  -0.2978   0.04245   0.03325  -0.0164   1.0000   0.2065
  -1.500  -0.2553   0.04136   0.03162  -0.0200   0.9909   0.2109
  -1.250  -0.2079   0.04060   0.03055  -0.0244   0.9762   0.2205
  -1.000  -0.1632   0.04021   0.02970  -0.0280   0.9618   0.2324
  -0.750  -0.1216   0.03976   0.02917  -0.0311   0.9473   0.2474
  -0.500  -0.0794   0.03950   0.02875  -0.0342   0.9329   0.2665
  -0.250  -0.0362   0.03931   0.02847  -0.0372   0.9183   0.2903
   0.000   0.0169   0.03930   0.02843  -0.0419   0.9045   0.3262
   0.250   0.0572   0.03907   0.02837  -0.0445   0.8895   0.3666
   0.500   0.0935   0.03881   0.02848  -0.0463   0.8747   0.4244
   0.750   0.1850   0.03741   0.02858  -0.0577   0.8606   1.0000
   1.000   0.2188   0.03824   0.02901  -0.0590   0.8453   1.0000
   1.250   0.2529   0.03906   0.02956  -0.0604   0.8307   1.0000
   1.500   0.2983   0.03983   0.03009  -0.0633   0.8179   1.0000
   1.750   0.3172   0.04065   0.03077  -0.0624   0.8025   1.0000
   2.000   0.3355   0.04158   0.03158  -0.0616   0.7879   1.0000
   2.250   0.3577   0.04252   0.03241  -0.0612   0.7744   1.0000
   2.500   0.3971   0.04324   0.03301  -0.0630   0.7636   1.0000
   2.750   0.4115   0.04431   0.03401  -0.0617   0.7504   1.0000
   3.000   0.4223   0.04559   0.03522  -0.0602   0.7382   1.0000
   3.250   0.4618   0.04625   0.03581  -0.0617   0.7285   1.0000
   3.500   0.4650   0.04778   0.03730  -0.0594   0.7166   1.0000
   3.750   0.4796   0.04915   0.03863  -0.0585   0.7067   1.0000
   4.000   0.5050   0.05018   0.03963  -0.0585   0.6972   1.0000
   4.250   0.5073   0.05200   0.04142  -0.0566   0.6872   1.0000
   4.500   0.5382   0.05297   0.04238  -0.0571   0.6790   1.0000
   4.750   0.5338   0.05513   0.04452  -0.0548   0.6694   1.0000
   5.000   0.5693   0.05594   0.04534  -0.0557   0.6611   1.0000
   5.250   0.5590   0.05846   0.04785  -0.0532   0.6523   1.0000
   5.500   0.5969   0.05897   0.04838  -0.0538   0.6413   1.0000
   5.750   0.6156   0.05989   0.04931  -0.0527   0.6276   1.0000
   6.000   0.6287   0.06100   0.05044  -0.0512   0.6128   1.0000
   6.250   0.6454   0.06200   0.05146  -0.0499   0.5984   1.0000
   6.500   0.6657   0.06294   0.05244  -0.0490   0.5854   1.0000
   6.750   0.7087   0.06255   0.05213  -0.0490   0.5737   1.0000
   7.000   0.7163   0.06427   0.05389  -0.0475   0.5606   1.0000
   7.250   0.7183   0.06649   0.05615  -0.0460   0.5471   1.0000
   7.500   0.7326   0.06788   0.05760  -0.0448   0.5332   1.0000
   7.750   0.7550   0.06863   0.05843  -0.0437   0.5190   1.0000
   8.000   0.7878   0.06848   0.05837  -0.0426   0.5051   1.0000
   8.250   0.8297   0.06730   0.05732  -0.0414   0.4916   1.0000
   8.500   0.8385   0.06897   0.05907  -0.0398   0.4755   1.0000
   8.750   0.8401   0.07153   0.06168  -0.0383   0.4596   1.0000
   9.000   0.8365   0.07485   0.06504  -0.0372   0.4440   1.0000
   9.250   1.1529   0.04653   0.03716  -0.0411   0.4220   1.0000
   9.500   1.1126   0.05055   0.04123  -0.0345   0.4095   1.0000
   9.750   1.1822   0.04775   0.03843  -0.0361   0.3847   1.0000
  10.000   1.1990   0.04831   0.03900  -0.0339   0.3667   1.0000
  10.250   1.2147   0.04893   0.03966  -0.0316   0.3495   1.0000
  10.500   1.2290   0.04961   0.04034  -0.0293   0.3327   1.0000
  10.750   1.0551   0.06623   0.05714  -0.0211   0.3422   1.0000
  11.000   0.9158   0.08972   0.08045  -0.0272   0.3359   1.0000
  11.250   0.8511   0.10275   0.09339  -0.0314   0.3283   1.0000
  11.500   0.8606   0.10504   0.09576  -0.0306   0.3165   1.0000
  11.750   0.8954   0.10353   0.09436  -0.0279   0.3034   1.0000
  12.000   0.8424   0.11552   0.10629  -0.0325   0.2987   1.0000
  12.250   0.8682   0.11572   0.10659  -0.0306   0.2868   1.0000
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