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GOE 318 (HANSA-BRANDENBURG VI.5) AIRFOIL (goe318-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 318 (HANSA-BRANDENBURG VI.5) AIRFOIL (goe318-il)
Reynolds number: 200,000
Max Cl/Cd: 69.03 at α=5.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe318-il-200000.txt
Download as CSV file: xf-goe318-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 318 (HANSA-BRANDENBURG VI.5) 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.4396   0.10791   0.10493   0.0092   1.0000   0.0375
  -8.500  -0.4383   0.10498   0.10208   0.0021   1.0000   0.0381
  -8.250  -0.4328   0.10131   0.09849  -0.0053   1.0000   0.0383
  -8.000  -0.4225   0.09517   0.09238  -0.0100   0.9450   0.0387
  -7.750  -0.4129   0.09177   0.08888  -0.0037   0.9046   0.0397
  -7.500  -0.4072   0.08914   0.08615  -0.0027   0.8789   0.0406
  -7.250  -0.3998   0.08608   0.08301  -0.0043   0.8608   0.0417
  -7.000  -0.3904   0.08266   0.07952  -0.0073   0.8468   0.0429
  -6.750  -0.3787   0.07897   0.07573  -0.0113   0.8350   0.0445
  -6.500  -0.3504   0.07417   0.07071  -0.0251   0.8235   0.0477
  -6.250  -0.3243   0.07006   0.06627  -0.0329   0.8144   0.0483
  -6.000  -0.3212   0.06418   0.06050  -0.0312   0.8065   0.0495
  -5.750  -0.3078   0.06168   0.05799  -0.0302   0.7978   0.0509
  -5.500  -0.2898   0.05889   0.05509  -0.0313   0.7904   0.0532
  -5.250  -0.2655   0.05536   0.05141  -0.0347   0.7824   0.0566
  -5.000  -0.2311   0.04999   0.04549  -0.0412   0.7763   0.0613
  -4.750  -0.2136   0.04710   0.04266  -0.0412   0.7691   0.0627
  -4.500  -0.1927   0.04495   0.04044  -0.0415   0.7622   0.0655
  -4.250  -0.1591   0.04172   0.03662  -0.0445   0.7563   0.0748
  -4.000  -0.1385   0.03905   0.03402  -0.0448   0.7493   0.0768
  -3.750  -0.1149   0.03721   0.03205  -0.0449   0.7439   0.0809
  -3.500  -0.0844   0.03463   0.02911  -0.0464   0.7369   0.0902
  -3.250  -0.0605   0.03290   0.02733  -0.0465   0.7310   0.0945
  -3.000  -0.0323   0.03105   0.02520  -0.0472   0.7249   0.1061
  -2.750  -0.0035   0.02987   0.02369  -0.0476   0.7181   0.1195
  -2.500   0.0210   0.02795   0.02179  -0.0476   0.7122   0.1246
  -2.250   0.0490   0.02648   0.02016  -0.0481   0.7043   0.1384
  -2.000   0.0755   0.02520   0.01868  -0.0480   0.6980   0.1536
  -1.750   0.1177   0.02155   0.01393  -0.0471   0.6906   0.0859
  -1.500   0.1481   0.01948   0.01138  -0.0463   0.6840   0.0723
  -1.250   0.1770   0.01809   0.00982  -0.0462   0.6761   0.0699
  -1.000   0.2054   0.01711   0.00864  -0.0458   0.6688   0.0686
  -0.750   0.2340   0.01635   0.00777  -0.0456   0.6604   0.0684
  -0.500   0.2619   0.01583   0.00712  -0.0451   0.6528   0.0706
  -0.250   0.2903   0.01530   0.00656  -0.0450   0.6444   0.0718
   0.000   0.3182   0.01483   0.00602  -0.0447   0.6379   0.0727
   0.250   0.3466   0.01441   0.00562  -0.0446   0.6305   0.0741
   0.500   0.3745   0.01395   0.00517  -0.0444   0.6234   0.0780
   0.750   0.4029   0.01373   0.00496  -0.0444   0.6157   0.0841
   1.000   0.4312   0.01349   0.00473  -0.0443   0.6080   0.0985
   1.250   0.4580   0.01096   0.00456  -0.0439   0.6002   1.0000
   1.500   0.4861   0.01102   0.00439  -0.0436   0.5921   1.0000
   1.750   0.5144   0.01108   0.00436  -0.0435   0.5831   1.0000
   2.000   0.5423   0.01115   0.00427  -0.0433   0.5753   1.0000
   2.250   0.5707   0.01121   0.00429  -0.0434   0.5653   1.0000
   2.500   0.5987   0.01127   0.00426  -0.0432   0.5564   1.0000
   2.750   0.6267   0.01132   0.00425  -0.0432   0.5463   1.0000
   3.000   0.6549   0.01138   0.00428  -0.0431   0.5350   1.0000
   3.250   0.6829   0.01145   0.00429  -0.0431   0.5235   1.0000
   3.500   0.7108   0.01152   0.00430  -0.0430   0.5112   1.0000
   3.750   0.7386   0.01161   0.00434  -0.0429   0.4975   1.0000
   4.000   0.7664   0.01172   0.00440  -0.0429   0.4820   1.0000
   4.250   0.7940   0.01187   0.00450  -0.0428   0.4645   1.0000
   4.500   0.8214   0.01208   0.00464  -0.0428   0.4458   1.0000
   4.750   0.8484   0.01236   0.00480  -0.0427   0.4266   1.0000
   5.000   0.8753   0.01269   0.00505  -0.0427   0.4071   1.0000
   5.250   0.9022   0.01307   0.00536  -0.0426   0.3897   1.0000
   5.500   0.9289   0.01347   0.00569  -0.0426   0.3757   1.0000
   5.750   0.9555   0.01392   0.00604  -0.0426   0.3648   1.0000
   6.000   0.9825   0.01431   0.00645  -0.0426   0.3552   1.0000
   6.250   1.0091   0.01476   0.00689  -0.0426   0.3480   1.0000
   6.500   1.0360   0.01517   0.00734  -0.0426   0.3414   1.0000
   7.000   1.0893   0.01608   0.00832  -0.0425   0.3310   1.0000
   7.250   1.1157   0.01648   0.00876  -0.0425   0.3249   1.0000
   7.500   1.1417   0.01689   0.00922  -0.0424   0.3176   1.0000
   7.750   1.1670   0.01725   0.00955  -0.0423   0.3075   1.0000
   8.000   1.1920   0.01749   0.00990  -0.0422   0.2949   1.0000
   8.250   1.2168   0.01781   0.01032  -0.0420   0.2833   1.0000
   8.500   1.2412   0.01820   0.01077  -0.0419   0.2729   1.0000
   8.750   1.2651   0.01862   0.01125  -0.0416   0.2616   1.0000
   9.000   1.2884   0.01903   0.01174  -0.0414   0.2475   1.0000
   9.250   1.3114   0.01939   0.01227  -0.0412   0.2262   1.0000
   9.500   1.3225   0.02117   0.01346  -0.0406   0.1101   1.0000
   9.750   1.3183   0.02489   0.01670  -0.0386   0.0540   1.0000
  10.000   1.3247   0.02694   0.01885  -0.0373   0.0457   1.0000
  10.250   1.3277   0.02899   0.02105  -0.0358   0.0416   1.0000
  10.500   1.3284   0.03112   0.02329  -0.0346   0.0389   1.0000
  10.750   1.3270   0.03386   0.02613  -0.0343   0.0371   1.0000
  11.000   1.3210   0.03724   0.02959  -0.0342   0.0357   1.0000
  11.250   1.3158   0.04061   0.03303  -0.0339   0.0347   1.0000
  11.500   1.3177   0.04324   0.03578  -0.0336   0.0337   1.0000
  11.750   1.3192   0.04592   0.03857  -0.0333   0.0325   1.0000
  12.000   1.3204   0.04862   0.04135  -0.0329   0.0313   1.0000
  12.250   1.3216   0.05133   0.04412  -0.0327   0.0302   1.0000
  12.500   1.3222   0.05405   0.04689  -0.0323   0.0292   1.0000
  12.750   1.3241   0.05647   0.04929  -0.0310   0.0282   1.0000
  13.000   1.3321   0.05823   0.05107  -0.0287   0.0274   1.0000
  13.250   1.3385   0.06047   0.05345  -0.0279   0.0270   1.0000
  13.500   1.3453   0.06273   0.05585  -0.0270   0.0265   1.0000
  13.750   1.3515   0.06513   0.05840  -0.0260   0.0261   1.0000
  14.000   1.3556   0.06784   0.06128  -0.0254   0.0256   1.0000
  14.250   1.3573   0.07086   0.06447  -0.0252   0.0251   1.0000
  14.500   1.3574   0.07409   0.06785  -0.0252   0.0245   1.0000
  14.750   1.3565   0.07742   0.07133  -0.0255   0.0240   1.0000
  15.000   1.3552   0.08087   0.07491  -0.0258   0.0235   1.0000
  15.250   1.3511   0.08482   0.07903  -0.0264   0.0233   1.0000
  15.500   1.3451   0.08920   0.08360  -0.0272   0.0232   1.0000
  15.750   1.3366   0.09409   0.08869  -0.0285   0.0232   1.0000
  16.000   1.3242   0.09976   0.09460  -0.0306   0.0233   1.0000
  16.250   1.3066   0.10653   0.10163  -0.0337   0.0234   1.0000
  16.500   1.2859   0.11425   0.10961  -0.0378   0.0237   1.0000
  16.750   1.2632   0.12285   0.11848  -0.0427   0.0240   1.0000
  17.000   1.2395   0.13215   0.12802  -0.0484   0.0244   1.0000
  17.250   1.2152   0.14222   0.13832  -0.0549   0.0248   1.0000
  17.500   1.1898   0.15330   0.14959  -0.0623   0.0253   1.0000
  17.750   1.1629   0.16561   0.16205  -0.0705   0.0259   1.0000
  18.000   1.1369   0.17867   0.17522  -0.0791   0.0267   1.0000
  18.250   1.1243   0.18784   0.18439  -0.0841   0.0275   1.0000
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