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GOE 324 (HANSA-BRANDENBURG) AIRFOIL (goe324-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 324 (HANSA-BRANDENBURG) AIRFOIL (goe324-il)
Reynolds number: 1,000,000
Max Cl/Cd: 136.44 at α=7.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe324-il-1000000.txt
Download as CSV file: xf-goe324-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 324 (HANSA-BRANDENBURG) AIRFOIL             
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.2692   0.09198   0.08902  -0.0061   0.5955   0.0210
  -7.750  -0.2674   0.08727   0.08432  -0.0118   0.5929   0.0217
  -7.500  -0.2648   0.08243   0.07948  -0.0187   0.5902   0.0218
  -7.250  -0.2523   0.07755   0.07457  -0.0253   0.5871   0.0218
  -7.000  -0.2397   0.07270   0.06967  -0.0303   0.5838   0.0219
  -6.750  -0.2273   0.06954   0.06651  -0.0318   0.5811   0.0220
  -6.500  -0.2116   0.06674   0.06370  -0.0337   0.5777   0.0221
  -6.250  -0.1943   0.06389   0.06082  -0.0360   0.5739   0.0222
  -6.000  -0.1755   0.06097   0.05784  -0.0386   0.5700   0.0223
  -5.750  -0.1553   0.05799   0.05479  -0.0414   0.5658   0.0225
  -5.500  -0.1336   0.05491   0.05168  -0.0442   0.5624   0.0227
  -5.250  -0.1107   0.05181   0.04850  -0.0470   0.5583   0.0230
  -5.000  -0.0867   0.04866   0.04526  -0.0496   0.5541   0.0235
  -4.750  -0.0498   0.04183   0.03807  -0.0548   0.5506   0.0251
  -4.500  -0.0272   0.03700   0.03304  -0.0566   0.5472   0.0253
  -4.250  -0.0044   0.03501   0.03100  -0.0573   0.5429   0.0255
  -4.000   0.0200   0.03334   0.02925  -0.0579   0.5381   0.0256
  -3.750   0.0452   0.03174   0.02755  -0.0584   0.5331   0.0258
  -3.500   0.0713   0.03009   0.02580  -0.0589   0.5286   0.0261
  -3.250   0.0982   0.02836   0.02395  -0.0593   0.5233   0.0265
  -3.000   0.1256   0.02654   0.02197  -0.0596   0.5178   0.0272
  -2.750   0.1567   0.02217   0.01696  -0.0592   0.5136   0.0291
  -2.500   0.1834   0.02085   0.01562  -0.0595   0.5085   0.0293
  -2.250   0.2108   0.01989   0.01459  -0.0597   0.5029   0.0296
  -2.000   0.2386   0.01905   0.01364  -0.0599   0.4974   0.0300
  -1.750   0.2669   0.01815   0.01265  -0.0600   0.4925   0.0306
  -1.500   0.2980   0.01786   0.01194  -0.0595   0.4870   0.0330
  -1.250   0.3250   0.01570   0.00967  -0.0598   0.4814   0.0338
  -1.000   0.3536   0.01507   0.00901  -0.0599   0.4768   0.0343
  -0.750   0.3824   0.01453   0.00840  -0.0601   0.4719   0.0350
  -0.500   0.4125   0.01484   0.00848  -0.0599   0.4667   0.0376
  -0.250   0.4408   0.01334   0.00689  -0.0600   0.4626   0.0386
   0.000   0.4697   0.01284   0.00639  -0.0602   0.4581   0.0394
   0.250   0.4986   0.01252   0.00601  -0.0603   0.4529   0.0408
   0.500   0.5277   0.01217   0.00553  -0.0603   0.4474   0.0444
   0.750   0.5567   0.01177   0.00515  -0.0605   0.4427   0.0457
   1.000   0.5858   0.01159   0.00490  -0.0605   0.4376   0.0479
   1.250   0.6150   0.01025   0.00335  -0.0598   0.4327   0.0325
   1.500   0.6440   0.01007   0.00318  -0.0599   0.4293   0.0327
   1.750   0.6730   0.00995   0.00305  -0.0600   0.4257   0.0330
   2.000   0.7017   0.00969   0.00279  -0.0601   0.4222   0.0337
   2.250   0.7305   0.00962   0.00273  -0.0603   0.4184   0.0348
   2.500   0.7593   0.00959   0.00269  -0.0604   0.4146   0.0356
   2.750   0.7885   0.00952   0.00264  -0.0606   0.4117   0.0367
   3.000   0.8176   0.00951   0.00263  -0.0608   0.4079   0.0376
   3.250   0.8464   0.00949   0.00259  -0.0609   0.4032   0.0393
   3.500   0.8750   0.00954   0.00263  -0.0611   0.3982   0.0415
   3.750   0.9042   0.00952   0.00264  -0.0613   0.3948   0.0456
   4.000   0.9330   0.00940   0.00272  -0.0615   0.3910   0.1504
   4.250   0.9587   0.00777   0.00294  -0.0616   0.3870   1.0000
   4.500   0.9869   0.00793   0.00304  -0.0617   0.3825   1.0000
   4.750   1.0157   0.00801   0.00312  -0.0619   0.3796   1.0000
   5.000   1.0443   0.00811   0.00320  -0.0620   0.3757   1.0000
   5.250   1.0726   0.00824   0.00331  -0.0622   0.3714   1.0000
   5.500   1.1005   0.00842   0.00344  -0.0623   0.3667   1.0000
   5.750   1.1291   0.00851   0.00354  -0.0625   0.3631   1.0000
   6.000   1.1574   0.00863   0.00366  -0.0627   0.3583   1.0000
   6.250   1.1852   0.00882   0.00380  -0.0629   0.3526   1.0000
   6.500   1.2133   0.00895   0.00394  -0.0631   0.3476   1.0000
   6.750   1.2412   0.00911   0.00408  -0.0632   0.3408   1.0000
   7.000   1.2686   0.00932   0.00426  -0.0634   0.3337   1.0000
   7.250   1.2962   0.00950   0.00442  -0.0635   0.3261   1.0000
   7.500   1.3232   0.00974   0.00463  -0.0636   0.3177   1.0000
   7.750   1.3501   0.00999   0.00484  -0.0637   0.3077   1.0000
   8.000   1.3767   0.01026   0.00508  -0.0638   0.2978   1.0000
   8.250   1.4026   0.01058   0.00536  -0.0639   0.2872   1.0000
   8.750   1.4537   0.01129   0.00598  -0.0639   0.2664   1.0000
   9.000   1.4787   0.01167   0.00633  -0.0638   0.2573   1.0000
   9.250   1.5032   0.01208   0.00670  -0.0637   0.2483   1.0000
   9.500   1.5280   0.01244   0.00705  -0.0636   0.2411   1.0000
   9.750   1.5518   0.01287   0.00746  -0.0635   0.2339   1.0000
  10.000   1.5758   0.01326   0.00785  -0.0633   0.2274   1.0000
  10.250   1.5983   0.01377   0.00832  -0.0631   0.2192   1.0000
  10.500   1.6213   0.01420   0.00875  -0.0628   0.2124   1.0000
  10.750   1.6429   0.01471   0.00924  -0.0625   0.2058   1.0000
  11.000   1.6647   0.01519   0.00972  -0.0621   0.2005   1.0000
  11.250   1.6863   0.01564   0.01020  -0.0618   0.1953   1.0000
  11.500   1.7048   0.01630   0.01084  -0.0611   0.1891   1.0000
  11.750   1.7249   0.01680   0.01137  -0.0606   0.1842   1.0000
  12.000   1.7390   0.01759   0.01215  -0.0595   0.1767   1.0000
  12.250   1.7505   0.01848   0.01305  -0.0582   0.1695   1.0000
  12.500   1.7575   0.01993   0.01449  -0.0573   0.1612   1.0000
  12.750   1.7654   0.02163   0.01619  -0.0570   0.1516   1.0000
  13.000   1.7685   0.02392   0.01846  -0.0569   0.1398   1.0000
  13.250   1.7629   0.02709   0.02157  -0.0565   0.1249   1.0000
  13.750   1.7403   0.03442   0.02883  -0.0554   0.0998   1.0000
  14.000   1.7320   0.03776   0.03219  -0.0548   0.0942   1.0000
  14.250   1.7273   0.04077   0.03524  -0.0543   0.0908   1.0000
  14.500   1.7226   0.04379   0.03832  -0.0539   0.0886   1.0000
  14.750   1.7160   0.04704   0.04162  -0.0535   0.0864   1.0000
  15.000   1.7095   0.05040   0.04503  -0.0532   0.0840   1.0000
  15.250   1.7068   0.05346   0.04816  -0.0531   0.0823   1.0000
  15.500   1.7073   0.05623   0.05100  -0.0531   0.0813   1.0000
  15.750   1.7056   0.05930   0.05415  -0.0531   0.0801   1.0000
  16.000   1.7026   0.06251   0.05743  -0.0532   0.0787   1.0000
  16.250   1.6982   0.06597   0.06094  -0.0534   0.0772   1.0000
  16.500   1.6912   0.06980   0.06484  -0.0536   0.0755   1.0000
  16.750   1.6828   0.07383   0.06894  -0.0540   0.0736   1.0000
  17.000   1.6834   0.07673   0.07191  -0.0542   0.0721   1.0000
  17.250   1.6824   0.07991   0.07516  -0.0546   0.0703   1.0000
  17.500   1.6785   0.08346   0.07876  -0.0551   0.0679   1.0000
  17.750   1.6694   0.08770   0.08304  -0.0557   0.0652   1.0000
  18.000   1.6656   0.09129   0.08670  -0.0562   0.0624   1.0000
  18.500   1.6404   0.10098   0.09637  -0.0581   0.0469   1.0000
  18.750   1.6163   0.10756   0.10291  -0.0596   0.0384   1.0000
  19.000   1.5974   0.11354   0.10893  -0.0611   0.0341   1.0000
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