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GOE 423 AIRFOIL (goe423-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 423 AIRFOIL (goe423-il)
Reynolds number: 200,000
Max Cl/Cd: 70.48 at α=7.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe423-il-200000-n5.txt
Download as CSV file: xf-goe423-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 423 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
  ------ -------- --------- --------- -------- -------- --------
 -12.500  -0.2261   0.11188   0.10772  -0.0816   0.9676   0.0478
 -12.250  -0.2275   0.10635   0.10217  -0.0851   0.9610   0.0482
 -12.000  -0.2409   0.09795   0.09374  -0.0906   0.9556   0.0492
 -11.750  -0.2280   0.09610   0.09189  -0.0916   0.9470   0.0497
 -11.500  -0.2180   0.09324   0.08901  -0.0935   0.9395   0.0502
 -11.250  -0.2171   0.08937   0.08512  -0.0953   0.9290   0.0506
 -11.000  -0.2209   0.08445   0.08019  -0.0980   0.9190   0.0509
 -10.750  -0.4229   0.04533   0.04046  -0.1261   0.8951   0.0521
 -10.500  -0.4491   0.04077   0.03548  -0.1242   0.8808   0.0526
 -10.250  -0.4573   0.03726   0.03154  -0.1223   0.8688   0.0532
 -10.000  -0.4563   0.03444   0.02829  -0.1206   0.8571   0.0537
  -9.750  -0.4498   0.03215   0.02560  -0.1188   0.8451   0.0543
  -9.500  -0.4387   0.03023   0.02324  -0.1173   0.8337   0.0549
  -9.250  -0.4225   0.02879   0.02151  -0.1162   0.8215   0.0555
  -9.000  -0.4020   0.02782   0.02045  -0.1155   0.8083   0.0560
  -8.750  -0.3809   0.02695   0.01944  -0.1148   0.7946   0.0566
  -8.500  -0.3599   0.02608   0.01839  -0.1140   0.7793   0.0571
  -8.250  -0.3387   0.02521   0.01733  -0.1131   0.7621   0.0577
  -8.000  -0.3174   0.02438   0.01628  -0.1123   0.7432   0.0583
  -7.750  -0.2957   0.02361   0.01528  -0.1114   0.7236   0.0589
  -7.500  -0.2736   0.02289   0.01433  -0.1106   0.7050   0.0596
  -7.250  -0.2511   0.02226   0.01345  -0.1098   0.6893   0.0605
  -6.750  -0.2047   0.02119   0.01189  -0.1083   0.6659   0.0621
  -6.500  -0.1809   0.02058   0.01117  -0.1078   0.6573   0.0628
  -6.250  -0.1565   0.02007   0.01060  -0.1074   0.6497   0.0635
  -6.000  -0.1320   0.01964   0.01009  -0.1069   0.6431   0.0643
  -5.750  -0.1071   0.01925   0.00962  -0.1065   0.6375   0.0651
  -5.500  -0.0821   0.01886   0.00916  -0.1061   0.6320   0.0660
  -5.250  -0.0570   0.01853   0.00873  -0.1057   0.6268   0.0672
  -5.000  -0.0317   0.01824   0.00832  -0.1053   0.6223   0.0685
  -4.750  -0.0060   0.01796   0.00794  -0.1049   0.6181   0.0697
  -4.500   0.0190   0.01757   0.00757  -0.1045   0.6140   0.0709
  -4.250   0.0442   0.01727   0.00726  -0.1041   0.6103   0.0722
  -4.000   0.0696   0.01703   0.00698  -0.1038   0.6069   0.0736
  -3.750   0.0954   0.01683   0.00672  -0.1035   0.6039   0.0752
  -3.500   0.1214   0.01665   0.00647  -0.1032   0.6011   0.0770
  -3.250   0.1471   0.01644   0.00625  -0.1029   0.5982   0.0792
  -3.000   0.1725   0.01622   0.00607  -0.1026   0.5953   0.0818
  -2.750   0.1985   0.01606   0.00591  -0.1023   0.5925   0.0850
  -2.500   0.2246   0.01593   0.00575  -0.1020   0.5899   0.0884
  -2.250   0.2505   0.01578   0.00562  -0.1017   0.5873   0.0930
  -2.000   0.2770   0.01569   0.00551  -0.1016   0.5848   0.1000
  -1.500   0.3295   0.01548   0.00543  -0.1012   0.5800   0.1298
  -1.250   0.3555   0.01539   0.00540  -0.1010   0.5777   0.1497
  -1.000   0.3816   0.01530   0.00537  -0.1007   0.5755   0.1693
  -0.750   0.4072   0.01516   0.00537  -0.1005   0.5733   0.1969
  -0.500   0.4325   0.01500   0.00539  -0.1002   0.5712   0.2474
  -0.250   0.4577   0.01482   0.00541  -0.0999   0.5693   0.3084
   0.000   0.4804   0.01445   0.00545  -0.0992   0.5675   0.4220
   0.250   0.5017   0.01406   0.00557  -0.0980   0.5658   0.5803
   0.500   0.5231   0.01370   0.00573  -0.0964   0.5642   0.7220
   0.750   0.5771   0.01372   0.00617  -0.1010   0.5622   0.9055
   1.000   0.6253   0.01392   0.00638  -0.1051   0.5600   0.9456
   1.250   0.6640   0.01411   0.00655  -0.1074   0.5579   0.9658
   1.500   0.7072   0.01431   0.00670  -0.1107   0.5560   0.9806
   1.750   0.7532   0.01446   0.00682  -0.1148   0.5541   0.9902
   2.000   0.7984   0.01460   0.00693  -0.1187   0.5523   0.9979
   2.250   0.8283   0.01475   0.00704  -0.1194   0.5506   1.0000
   2.500   0.8509   0.01489   0.00716  -0.1186   0.5489   1.0000
   2.750   0.8739   0.01505   0.00727  -0.1179   0.5472   1.0000
   3.000   0.8977   0.01522   0.00740  -0.1173   0.5456   1.0000
   3.250   0.9217   0.01543   0.00758  -0.1167   0.5441   1.0000
   3.500   0.9425   0.01563   0.00782  -0.1155   0.5425   1.0000
   3.750   0.9634   0.01583   0.00806  -0.1144   0.5407   1.0000
   4.000   0.9844   0.01603   0.00830  -0.1133   0.5386   1.0000
   4.250   1.0058   0.01624   0.00854  -0.1122   0.5365   1.0000
   4.500   1.0277   0.01644   0.00877  -0.1112   0.5345   1.0000
   4.750   1.0497   0.01659   0.00891  -0.1102   0.5315   1.0000
   5.000   1.0732   0.01665   0.00892  -0.1094   0.5277   1.0000
   5.250   1.0909   0.01676   0.00905  -0.1075   0.5225   1.0000
   5.500   1.1069   0.01683   0.00918  -0.1053   0.5164   1.0000
   5.750   1.1269   0.01685   0.00917  -0.1038   0.5112   1.0000
   6.000   1.1475   0.01694   0.00924  -0.1025   0.5064   1.0000
   6.250   1.1625   0.01710   0.00950  -0.1002   0.5011   1.0000
   6.500   1.1807   0.01722   0.00966  -0.0984   0.4963   1.0000
   6.750   1.2017   0.01729   0.00969  -0.0972   0.4915   1.0000
   7.000   1.2164   0.01748   0.00998  -0.0949   0.4856   1.0000
   7.250   1.2320   0.01765   0.01021  -0.0928   0.4796   1.0000
   7.500   1.2504   0.01774   0.01028  -0.0911   0.4740   1.0000
   7.750   1.2612   0.01799   0.01065  -0.0881   0.4664   1.0000
   8.000   1.2738   0.01817   0.01085  -0.0855   0.4590   1.0000
   8.250   1.2851   0.01847   0.01123  -0.0828   0.4506   1.0000
   8.500   1.2965   0.01876   0.01152  -0.0801   0.4408   1.0000
   8.750   1.3054   0.01918   0.01199  -0.0772   0.4265   1.0000
   9.000   1.3123   0.01972   0.01253  -0.0741   0.4054   1.0000
   9.250   1.3134   0.02054   0.01322  -0.0703   0.3767   1.0000
   9.500   1.3067   0.02190   0.01438  -0.0658   0.3443   1.0000
   9.750   1.2968   0.02373   0.01603  -0.0614   0.3160   1.0000
  10.000   1.2880   0.02578   0.01796  -0.0577   0.2905   1.0000
  10.250   1.2775   0.02818   0.02025  -0.0542   0.2660   1.0000
  10.500   1.2655   0.03091   0.02288  -0.0511   0.2396   1.0000
  10.750   1.2539   0.03387   0.02574  -0.0485   0.2152   1.0000
  11.000   1.2402   0.03724   0.02900  -0.0461   0.1865   1.0000
  11.250   1.2130   0.04209   0.03358  -0.0435   0.1383   1.0000
  11.500   1.1932   0.04645   0.03774  -0.0417   0.1069   1.0000
  11.750   1.1791   0.05040   0.04153  -0.0402   0.0735   1.0000
  12.000   1.1715   0.05378   0.04481  -0.0391   0.0602   1.0000
  12.250   1.1717   0.05644   0.04747  -0.0383   0.0558   1.0000
  12.500   1.1730   0.05904   0.05010  -0.0376   0.0531   1.0000
  12.750   1.1765   0.06144   0.05257  -0.0371   0.0512   1.0000
  13.000   1.1794   0.06392   0.05511  -0.0366   0.0497   1.0000
  13.250   1.1812   0.06655   0.05780  -0.0361   0.0484   1.0000
  13.500   1.1819   0.06935   0.06065  -0.0357   0.0473   1.0000
  13.750   1.1845   0.07197   0.06334  -0.0354   0.0463   1.0000
  14.000   1.1877   0.07454   0.06599  -0.0351   0.0454   1.0000
  14.250   1.1903   0.07719   0.06872  -0.0348   0.0446   1.0000
  14.500   1.1922   0.07996   0.07156  -0.0346   0.0438   1.0000
  14.750   1.1942   0.08274   0.07441  -0.0345   0.0432   1.0000
  15.000   1.1954   0.08564   0.07737  -0.0344   0.0426   1.0000
  15.250   1.1966   0.08854   0.08033  -0.0344   0.0421   1.0000
  15.500   1.1972   0.09150   0.08333  -0.0343   0.0416   1.0000
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