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GOE 14 AIRFOIL (goe14-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 14 AIRFOIL (goe14-il)
Reynolds number: 200,000
Max Cl/Cd: 70.05 at α=8.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe14-il-200000-n5.txt
Download as CSV file: xf-goe14-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 14 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
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.1368   0.10315   0.09951  -0.0406   0.9002   0.0309
  -8.500  -0.1275   0.10005   0.09639  -0.0404   0.8863   0.0310
  -8.250  -0.1189   0.09738   0.09370  -0.0406   0.8727   0.0313
  -8.000  -0.1105   0.09492   0.09121  -0.0411   0.8602   0.0315
  -7.750  -0.1018   0.09253   0.08878  -0.0418   0.8480   0.0319
  -7.500  -0.0926   0.09012   0.08634  -0.0429   0.8363   0.0323
  -7.250  -0.0833   0.08772   0.08390  -0.0441   0.8254   0.0328
  -7.000  -0.0735   0.08536   0.08151  -0.0457   0.8141   0.0335
  -6.750  -0.0618   0.08295   0.07906  -0.0485   0.8039   0.0343
  -6.500  -0.0459   0.08036   0.07642  -0.0531   0.7932   0.0346
  -6.250  -0.0272   0.07769   0.07368  -0.0582   0.7831   0.0347
  -6.000  -0.0125   0.07471   0.07067  -0.0596   0.7730   0.0348
  -5.750   0.0025   0.07194   0.06787  -0.0606   0.7630   0.0351
  -5.500   0.0198   0.06936   0.06523  -0.0627   0.7526   0.0355
  -5.250   0.0395   0.06679   0.06262  -0.0653   0.7417   0.0360
  -5.000   0.0606   0.06423   0.05997  -0.0682   0.7311   0.0367
  -4.750   0.0840   0.06162   0.05729  -0.0716   0.7192   0.0376
  -4.500   0.1161   0.05901   0.05453  -0.0774   0.7075   0.0386
  -4.250   0.1410   0.05630   0.05170  -0.0803   0.6951   0.0389
  -4.000   0.1607   0.05384   0.04920  -0.0813   0.6814   0.0394
  -3.750   0.1846   0.05157   0.04684  -0.0832   0.6674   0.0400
  -3.500   0.2105   0.04937   0.04451  -0.0854   0.6524   0.0408
  -3.250   0.2383   0.04721   0.04220  -0.0877   0.6365   0.0418
  -3.000   0.2721   0.04519   0.03994  -0.0909   0.6199   0.0428
  -2.500   0.3256   0.04099   0.03541  -0.0938   0.5867   0.0434
  -2.250   0.3503   0.03922   0.03349  -0.0947   0.5708   0.0441
  -2.000   0.3774   0.03766   0.03177  -0.0957   0.5562   0.0456
  -1.750   0.4155   0.03658   0.03031  -0.0976   0.5431   0.0475
  -1.500   0.4389   0.03464   0.02825  -0.0980   0.5308   0.0478
  -1.250   0.4643   0.03305   0.02656  -0.0986   0.5191   0.0483
  -1.000   0.4914   0.03171   0.02505  -0.0991   0.5085   0.0489
  -0.750   0.5195   0.03045   0.02362  -0.0995   0.4980   0.0497
  -0.250   0.5796   0.02725   0.01992  -0.1003   0.4799   0.0419
   0.000   0.6084   0.02597   0.01843  -0.1005   0.4717   0.0404
   0.250   0.6370   0.02502   0.01731  -0.1006   0.4631   0.0416
   0.500   0.6653   0.02404   0.01610  -0.1005   0.4557   0.0415
   0.750   0.6943   0.02298   0.01486  -0.1005   0.4481   0.0407
   1.000   0.7229   0.02203   0.01368  -0.1003   0.4412   0.0403
   1.250   0.7512   0.02120   0.01265  -0.1001   0.4347   0.0404
   1.500   0.7794   0.02045   0.01173  -0.0999   0.4274   0.0409
   1.750   0.8077   0.01960   0.01059  -0.0994   0.4208   0.0431
   2.000   0.8345   0.01937   0.01033  -0.0993   0.4138   0.0441
   2.250   0.8617   0.01891   0.00974  -0.0989   0.4069   0.0451
   2.500   0.8887   0.01838   0.00902  -0.0985   0.4011   0.0466
   2.750   0.9158   0.01813   0.00873  -0.0982   0.3948   0.0488
   3.000   0.9425   0.01788   0.00838  -0.0978   0.3886   0.0526
   3.250   0.9684   0.01782   0.00825  -0.0974   0.3830   0.0554
   3.500   0.9951   0.01770   0.00811  -0.0971   0.3769   0.0596
   3.750   1.0210   0.01772   0.00808  -0.0967   0.3706   0.0656
   4.000   1.0465   0.01777   0.00806  -0.0962   0.3649   0.0715
   4.250   1.0725   0.01781   0.00810  -0.0959   0.3585   0.0782
   4.500   1.0978   0.01786   0.00812  -0.0955   0.3526   0.0841
   4.750   1.1229   0.01798   0.00819  -0.0951   0.3475   0.0887
   5.000   1.1485   0.01800   0.00826  -0.0947   0.3420   0.0912
   5.250   1.1734   0.01809   0.00837  -0.0943   0.3365   0.0942
   5.500   1.1977   0.01827   0.00851  -0.0938   0.3315   0.0959
   5.750   1.2229   0.01840   0.00869  -0.0934   0.3256   0.0979
   6.000   1.2471   0.01855   0.00885  -0.0929   0.3195   0.0999
   6.250   1.2706   0.01878   0.00905  -0.0923   0.3139   0.1012
   6.500   1.2950   0.01898   0.00928  -0.0919   0.3077   0.1027
   6.750   1.3185   0.01925   0.00953  -0.0913   0.3023   0.1049
   7.000   1.3413   0.01960   0.00982  -0.0906   0.2982   0.1074
   7.250   1.3652   0.01986   0.01014  -0.0901   0.2937   0.1093
   7.500   1.3883   0.02017   0.01046  -0.0895   0.2888   0.1114
   7.750   1.4104   0.02054   0.01080  -0.0888   0.2841   0.1139
   8.000   1.4324   0.02093   0.01119  -0.0880   0.2799   0.1181
   8.250   1.4548   0.02127   0.01159  -0.0873   0.2748   0.1239
   8.750   1.4962   0.02136   0.01262  -0.0858   0.2663   0.7997
   9.250   1.5353   0.02201   0.01354  -0.0834   0.2584   1.0000
   9.500   1.5542   0.02251   0.01406  -0.0823   0.2545   1.0000
   9.750   1.5709   0.02306   0.01462  -0.0809   0.2510   1.0000
  10.000   1.5868   0.02366   0.01521  -0.0794   0.2477   1.0000
  10.250   1.6042   0.02419   0.01584  -0.0782   0.2442   1.0000
  10.500   1.6202   0.02480   0.01652  -0.0769   0.2404   1.0000
  10.750   1.6346   0.02549   0.01725  -0.0754   0.2367   1.0000
  11.000   1.6475   0.02628   0.01805  -0.0738   0.2333   1.0000
  11.250   1.6615   0.02705   0.01889  -0.0725   0.2299   1.0000
  11.500   1.6755   0.02784   0.01981  -0.0712   0.2261   1.0000
  11.750   1.6876   0.02875   0.02079  -0.0699   0.2222   1.0000
  12.000   1.6977   0.02981   0.02188  -0.0684   0.2184   1.0000
  12.250   1.7074   0.03094   0.02306  -0.0671   0.2145   1.0000
  12.500   1.7178   0.03207   0.02433  -0.0659   0.2094   1.0000
  12.750   1.7247   0.03347   0.02579  -0.0646   0.2041   1.0000
  13.000   1.7300   0.03505   0.02741  -0.0634   0.1993   1.0000
  13.250   1.7373   0.03658   0.02907  -0.0624   0.1934   1.0000
  13.500   1.7402   0.03850   0.03103  -0.0614   0.1879   1.0000
  13.750   1.7439   0.04044   0.03308  -0.0605   0.1826   1.0000
  14.000   1.7463   0.04258   0.03531  -0.0597   0.1766   1.0000
  14.250   1.7443   0.04519   0.03796  -0.0590   0.1713   1.0000
  14.500   1.7446   0.04769   0.04058  -0.0585   0.1649   1.0000
  14.750   1.7389   0.05090   0.04383  -0.0581   0.1594   1.0000
  15.000   1.7356   0.05397   0.04699  -0.0578   0.1540   1.0000
  15.250   1.7290   0.05756   0.05066  -0.0578   0.1490   1.0000
  15.500   1.7202   0.06154   0.05470  -0.0580   0.1449   1.0000
  15.750   1.7138   0.06536   0.05863  -0.0584   0.1407   1.0000
  16.000   1.7042   0.06968   0.06303  -0.0589   0.1370   1.0000
  16.250   1.6925   0.07437   0.06778  -0.0597   0.1339   1.0000
  16.500   1.6846   0.07860   0.07212  -0.0603   0.1311   1.0000
  16.750   1.6764   0.08293   0.07657  -0.0611   0.1283   1.0000
  17.000   1.6668   0.08752   0.08125  -0.0621   0.1257   1.0000
  17.250   1.6562   0.09227   0.08608  -0.0632   0.1233   1.0000
  17.500   1.6455   0.09704   0.09090  -0.0643   0.1210   1.0000
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