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GOE 144 (MVA H.21) AIRFOIL (goe144-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 144 (MVA H.21) AIRFOIL (goe144-il)
Reynolds number: 50,000
Max Cl/Cd: 41.55 at α=6.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe144-il-50000-n5.txt
Download as CSV file: xf-goe144-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 144 (MVA H.21) 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.3345   0.11063   0.10384  -0.0268   1.0000   0.0887
  -8.250  -0.3408   0.10918   0.10251  -0.0275   1.0000   0.0892
  -8.000  -0.3456   0.10731   0.10076  -0.0275   1.0000   0.0893
  -7.750  -0.3304   0.10182   0.09528  -0.0259   1.0000   0.0912
  -7.500  -0.3302   0.09913   0.09264  -0.0252   1.0000   0.0919
  -7.250  -0.3330   0.09676   0.09038  -0.0247   1.0000   0.0919
  -7.000  -0.3378   0.09462   0.08837  -0.0265   1.0000   0.0905
  -6.750  -0.3352   0.08900   0.08277  -0.0278   1.0000   0.0627
  -6.500  -0.3324   0.08583   0.07963  -0.0273   1.0000   0.0610
  -6.250  -0.3302   0.08279   0.07665  -0.0280   1.0000   0.0602
  -6.000  -0.3269   0.07965   0.07356  -0.0293   1.0000   0.0605
  -5.750  -0.3215   0.07637   0.07031  -0.0312   1.0000   0.0612
  -5.500  -0.3136   0.07277   0.06671  -0.0336   1.0000   0.0619
  -5.250  -0.3032   0.06897   0.06290  -0.0360   1.0000   0.0620
  -5.000  -0.2907   0.06509   0.05897  -0.0383   1.0000   0.0617
  -4.750  -0.2749   0.06090   0.05469  -0.0412   1.0000   0.0617
  -4.500  -0.2522   0.05575   0.04933  -0.0461   1.0000   0.0632
  -4.250  -0.2389   0.05386   0.04744  -0.0458   1.0000   0.0676
  -4.000  -0.2174   0.05026   0.04366  -0.0482   1.0000   0.0700
  -3.750  -0.1914   0.04591   0.03901  -0.0516   1.0000   0.0714
  -3.500  -0.1484   0.04085   0.03339  -0.0581   0.9953   0.0781
  -3.250  -0.1048   0.03777   0.02988  -0.0631   0.9870   0.0834
  -3.000  -0.0579   0.03297   0.02421  -0.0686   0.9795   0.0881
  -2.750  -0.0168   0.03085   0.02170  -0.0720   0.9699   0.0940
  -2.500   0.0231   0.02979   0.02033  -0.0749   0.9587   0.1080
  -2.250   0.0638   0.02818   0.01825  -0.0777   0.9481   0.1203
  -2.000   0.1059   0.02698   0.01665  -0.0805   0.9377   0.1354
  -1.750   0.1448   0.02668   0.01618  -0.0829   0.9255   0.1592
  -1.500   0.1824   0.02595   0.01519  -0.0848   0.9128   0.1743
  -1.250   0.2207   0.02514   0.01408  -0.0867   0.9006   0.1851
  -1.000   0.2599   0.02443   0.01315  -0.0886   0.8886   0.1937
  -0.750   0.3003   0.02381   0.01233  -0.0906   0.8766   0.2040
  -0.500   0.3373   0.02334   0.01176  -0.0920   0.8630   0.2189
  -0.250   0.3720   0.02291   0.01123  -0.0930   0.8482   0.2338
   0.000   0.4053   0.02250   0.01075  -0.0936   0.8329   0.2484
   0.250   0.4377   0.02213   0.01035  -0.0942   0.8174   0.2651
   0.500   0.4698   0.02176   0.01001  -0.0946   0.8021   0.2928
   0.750   0.5020   0.02132   0.00966  -0.0952   0.7873   0.3259
   1.000   0.5339   0.02076   0.00934  -0.0957   0.7730   0.3688
   1.250   0.5698   0.01920   0.00905  -0.0965   0.7590   1.0000
   1.500   0.6016   0.01930   0.00886  -0.0967   0.7444   1.0000
   1.750   0.6326   0.01944   0.00879  -0.0967   0.7298   1.0000
   2.000   0.6626   0.01963   0.00879  -0.0966   0.7150   1.0000
   2.250   0.6916   0.01987   0.00887  -0.0964   0.6999   1.0000
   2.500   0.7197   0.02014   0.00903  -0.0960   0.6842   1.0000
   2.750   0.7469   0.02043   0.00921  -0.0955   0.6683   1.0000
   3.000   0.7735   0.02075   0.00945  -0.0949   0.6524   1.0000
   3.250   0.7995   0.02108   0.00975  -0.0942   0.6369   1.0000
   3.500   0.8251   0.02145   0.01009  -0.0935   0.6220   1.0000
   3.750   0.8503   0.02183   0.01047  -0.0928   0.6075   1.0000
   4.000   0.8753   0.02223   0.01092  -0.0921   0.5934   1.0000
   4.250   0.9001   0.02265   0.01139  -0.0914   0.5797   1.0000
   4.500   0.9246   0.02308   0.01188  -0.0906   0.5660   1.0000
   4.750   0.9490   0.02352   0.01240  -0.0898   0.5523   1.0000
   5.000   0.9732   0.02399   0.01299  -0.0889   0.5388   1.0000
   5.250   0.9972   0.02446   0.01357  -0.0881   0.5252   1.0000
   5.500   1.0210   0.02496   0.01418  -0.0872   0.5113   1.0000
   5.750   1.0440   0.02545   0.01480  -0.0861   0.4965   1.0000
   6.000   1.0659   0.02591   0.01543  -0.0848   0.4796   1.0000
   6.250   1.0870   0.02630   0.01593  -0.0833   0.4610   1.0000
   6.500   1.1074   0.02665   0.01635  -0.0817   0.4412   1.0000
   6.750   1.1254   0.02711   0.01697  -0.0798   0.4197   1.0000
   7.000   1.1449   0.02757   0.01756  -0.0782   0.4007   1.0000
   7.250   1.1603   0.02800   0.01816  -0.0759   0.3751   1.0000
   7.500   1.1728   0.02843   0.01859  -0.0733   0.3439   1.0000
   7.750   1.1863   0.02905   0.01927  -0.0710   0.3158   1.0000
   8.000   1.1952   0.02986   0.01995  -0.0682   0.2789   1.0000
   8.250   1.2065   0.03083   0.02094  -0.0659   0.2513   1.0000
   8.500   1.2143   0.03206   0.02211  -0.0633   0.2155   1.0000
   8.750   1.2209   0.03349   0.02349  -0.0608   0.1735   1.0000
   9.000   1.2207   0.03539   0.02511  -0.0578   0.1276   1.0000
   9.250   1.2175   0.03768   0.02717  -0.0547   0.0981   1.0000
   9.500   1.2143   0.04016   0.02964  -0.0520   0.0663   1.0000
   9.750   1.2097   0.04287   0.03225  -0.0497   0.0503   1.0000
  10.000   1.2047   0.04574   0.03510  -0.0479   0.0450   1.0000
  10.250   1.1982   0.04896   0.03836  -0.0465   0.0415   1.0000
  10.500   1.1914   0.05243   0.04189  -0.0457   0.0394   1.0000
  10.750   1.1864   0.05594   0.04560  -0.0453   0.0380   1.0000
  11.000   1.1811   0.05971   0.04957  -0.0453   0.0370   1.0000
  11.250   1.1757   0.06366   0.05372  -0.0456   0.0361   1.0000
  11.500   1.1704   0.06773   0.05796  -0.0461   0.0353   1.0000
  11.750   1.1652   0.07190   0.06229  -0.0467   0.0345   1.0000
  12.000   1.1604   0.07607   0.06661  -0.0473   0.0338   1.0000
  12.250   1.1558   0.08026   0.07092  -0.0480   0.0330   1.0000
  12.500   1.1516   0.08439   0.07515  -0.0485   0.0322   1.0000
  12.750   1.1506   0.08815   0.07904  -0.0488   0.0313   1.0000
  13.000   1.1512   0.09180   0.08293  -0.0491   0.0305   1.0000
  13.250   1.1514   0.09564   0.08700  -0.0496   0.0296   1.0000
  13.500   1.1516   0.09960   0.09119  -0.0502   0.0290   1.0000
  13.750   1.1510   0.10382   0.09564  -0.0511   0.0285   1.0000
  14.000   1.1494   0.10839   0.10045  -0.0523   0.0282   1.0000
  14.250   1.1458   0.11352   0.10583  -0.0540   0.0280   1.0000
  14.500   1.1399   0.11933   0.11188  -0.0565   0.0280   1.0000
  14.750   1.1319   0.12583   0.11861  -0.0597   0.0280   1.0000
  15.000   1.1219   0.13308   0.12609  -0.0636   0.0281   1.0000
  15.250   1.1101   0.14122   0.13445  -0.0683   0.0284   1.0000
  15.500   1.0970   0.15030   0.14371  -0.0737   0.0287   1.0000
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