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GOE 401 AIRFOIL (goe401-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: GOE 401 AIRFOIL (goe401-il)
Reynolds number: 50,000
Max Cl/Cd: 32.93 at α=10.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe401-il-50000.txt
Download as CSV file: xf-goe401-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 401 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  -0.3230   0.10648   0.09949  -0.0199   1.0000   0.1296
  -8.000  -0.3281   0.10559   0.09871  -0.0207   1.0000   0.1323
  -7.750  -0.3404   0.10587   0.09916  -0.0222   1.0000   0.1335
  -7.500  -0.3311   0.10093   0.09427  -0.0211   1.0000   0.1356
  -7.250  -0.3194   0.09673   0.09010  -0.0196   1.0000   0.1398
  -7.000  -0.3179   0.09445   0.08790  -0.0197   1.0000   0.1439
  -6.750  -0.3217   0.09366   0.08723  -0.0225   1.0000   0.1477
  -6.500  -0.3205   0.09132   0.08499  -0.0241   1.0000   0.1498
  -6.250  -0.3108   0.08689   0.08061  -0.0205   1.0000   0.1553
  -6.000  -0.3095   0.08529   0.07909  -0.0221   1.0000   0.1614
  -5.750  -0.3080   0.08336   0.07724  -0.0241   1.0000   0.1646
  -5.500  -0.3030   0.07973   0.07369  -0.0207   1.0000   0.1697
  -5.250  -0.3006   0.07869   0.07266  -0.0232   1.0000   0.1769
  -5.000  -0.2984   0.07571   0.06976  -0.0221   1.0000   0.1801
  -4.750  -0.2958   0.07306   0.06718  -0.0197   1.0000   0.1856
  -4.500  -0.2893   0.07168   0.06575  -0.0226   1.0000   0.1934
  -4.250  -0.2874   0.06860   0.06277  -0.0194   1.0000   0.1987
  -4.000  -0.2785   0.06671   0.06083  -0.0213   1.0000   0.2087
  -3.750  -0.2669   0.06527   0.05931  -0.0231   1.0000   0.2217
  -3.500  -0.2653   0.06181   0.05599  -0.0194   1.0000   0.2282
  -3.250  -0.2565   0.05955   0.05372  -0.0193   1.0000   0.2434
  -3.000  -0.2446   0.05767   0.05178  -0.0205   1.0000   0.2677
  -2.750  -0.2394   0.05507   0.04928  -0.0183   1.0000   0.2873
  -2.500  -0.2324   0.05292   0.04717  -0.0170   1.0000   0.3180
  -2.000  -0.2255   0.04873   0.04318  -0.0113   1.0000   0.4002
  -1.750  -0.2225   0.04666   0.04120  -0.0082   1.0000   0.4438
  -1.500  -0.1942   0.04416   0.03873  -0.0096   0.9901   0.5019
  -1.250  -0.1511   0.04124   0.03584  -0.0132   0.9737   0.5501
  -1.000  -0.0950   0.03871   0.03319  -0.0205   0.9557   0.5783
  -0.750  -0.0243   0.03641   0.03065  -0.0318   0.9361   0.5750
  -0.500   0.1364   0.03660   0.02904  -0.0634   0.9138   0.3370
  -0.250   0.2140   0.03629   0.02763  -0.0709   0.8932   0.2186
   0.000   0.2724   0.03503   0.02583  -0.0752   0.8750   0.1903
   0.250   0.3294   0.03345   0.02392  -0.0794   0.8579   0.1826
   0.500   0.3854   0.03225   0.02229  -0.0830   0.8413   0.1761
   0.750   0.4351   0.03106   0.02080  -0.0854   0.8246   0.1766
   1.000   0.4887   0.02984   0.01933  -0.0886   0.8080   0.1891
   1.250   0.5359   0.02870   0.01808  -0.0905   0.7915   0.2100
   1.500   0.5735   0.02748   0.01696  -0.0910   0.7754   0.2553
   1.750   0.6297   0.02489   0.01569  -0.0946   0.7596   1.0000
   2.000   0.6566   0.02532   0.01577  -0.0936   0.7424   1.0000
   2.250   0.6819   0.02581   0.01603  -0.0926   0.7260   1.0000
   2.500   0.7076   0.02627   0.01631  -0.0916   0.7106   1.0000
   2.750   0.7344   0.02668   0.01657  -0.0907   0.6963   1.0000
   3.000   0.7586   0.02722   0.01699  -0.0896   0.6817   1.0000
   3.250   0.7806   0.02793   0.01763  -0.0884   0.6672   1.0000
   3.500   0.8024   0.02867   0.01832  -0.0872   0.6530   1.0000
   3.750   0.8233   0.02950   0.01912  -0.0860   0.6395   1.0000
   4.000   0.8447   0.03034   0.01994  -0.0848   0.6264   1.0000
   4.250   0.8677   0.03108   0.02065  -0.0837   0.6141   1.0000
   4.500   0.8962   0.03145   0.02099  -0.0830   0.6033   1.0000
   4.750   0.9146   0.03256   0.02214  -0.0817   0.5903   1.0000
   5.000   0.9309   0.03391   0.02356  -0.0804   0.5779   1.0000
   5.250   0.9496   0.03515   0.02486  -0.0792   0.5665   1.0000
   5.500   0.9789   0.03553   0.02525  -0.0785   0.5568   1.0000
   5.750   0.9913   0.03733   0.02718  -0.0771   0.5450   1.0000
   6.000   1.0022   0.03937   0.02934  -0.0758   0.5340   1.0000
   6.250   1.0274   0.04022   0.03025  -0.0749   0.5249   1.0000
   6.500   1.0362   0.04254   0.03274  -0.0736   0.5146   1.0000
   6.750   1.0372   0.04567   0.03602  -0.0721   0.5050   1.0000
   7.000   1.0693   0.04601   0.03644  -0.0714   0.4970   1.0000
   7.250   1.0378   0.05228   0.04285  -0.0697   0.4873   1.0000
   7.500   1.0843   0.05149   0.04219  -0.0692   0.4808   1.0000
   7.750   0.9759   0.06519   0.05578  -0.0681   0.4745   1.0000
   8.000   0.9619   0.07025   0.06085  -0.0681   0.4691   1.0000
   8.250   0.9724   0.07323   0.06392  -0.0678   0.4640   1.0000
   8.500   0.9457   0.07997   0.07064  -0.0689   0.4639   1.0000
   8.750   0.9339   0.08538   0.07608  -0.0699   0.4644   1.0000
   9.000   0.9291   0.09032   0.08109  -0.0709   0.4655   1.0000
   9.750   1.2755   0.05390   0.04618  -0.0516   0.3551   1.0000
  10.000   1.1970   0.06550   0.05779  -0.0496   0.3579   1.0000
  10.250   1.3436   0.04080   0.03271  -0.0411   0.2487   1.0000
  10.500   1.3336   0.04131   0.03275  -0.0356   0.2082   1.0000
  10.750   1.3217   0.04319   0.03436  -0.0309   0.1816   1.0000
  11.000   1.3108   0.04565   0.03672  -0.0272   0.1624   1.0000
  11.250   1.3051   0.04826   0.03927  -0.0244   0.1472   1.0000
  11.500   1.3035   0.05100   0.04194  -0.0222   0.1347   1.0000
  11.750   1.3062   0.05370   0.04453  -0.0204   0.1240   1.0000
  12.000   1.3212   0.05625   0.04689  -0.0190   0.1136   1.0000
  12.250   1.3192   0.05993   0.05098  -0.0176   0.1096   1.0000
  12.500   1.3241   0.06324   0.05445  -0.0165   0.1047   1.0000
  12.750   1.3337   0.06680   0.05806  -0.0155   0.1000   1.0000
  13.000   1.3182   0.07129   0.06290  -0.0151   0.0990   1.0000
  13.250   1.3003   0.07635   0.06828  -0.0154   0.0985   1.0000
  13.500   1.2788   0.08222   0.07442  -0.0167   0.0986   1.0000
  13.750   1.2537   0.08898   0.08143  -0.0190   0.0991   1.0000
  14.000   1.2278   0.09655   0.08920  -0.0223   0.1001   1.0000
  14.250   1.2010   0.10502   0.09781  -0.0264   0.1010   1.0000
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