Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

GOE 324 (HANSA-BRANDENBURG) AIRFOIL (goe324-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 324 (HANSA-BRANDENBURG) AIRFOIL (goe324-il)
Reynolds number: 500,000
Max Cl/Cd: 108.8 at α=8°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe324-il-500000.txt
Download as CSV file: xf-goe324-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.500  -0.2455   0.08733   0.08382  -0.0116   0.6241   0.0266
  -7.250  -0.2379   0.08424   0.08070  -0.0140   0.6204   0.0270
  -7.000  -0.2310   0.08105   0.07754  -0.0171   0.6171   0.0274
  -6.750  -0.2186   0.07728   0.07377  -0.0219   0.6133   0.0280
  -6.500  -0.1949   0.06985   0.06621  -0.0378   0.6104   0.0288
  -6.250  -0.1765   0.06493   0.06118  -0.0428   0.6069   0.0289
  -6.000  -0.1627   0.06224   0.05845  -0.0430   0.6029   0.0291
  -5.750  -0.1461   0.05976   0.05596  -0.0437   0.5991   0.0292
  -5.500  -0.1275   0.05724   0.05342  -0.0450   0.5948   0.0295
  -5.250  -0.1070   0.05458   0.05071  -0.0468   0.5906   0.0298
  -5.000  -0.0847   0.05177   0.04780  -0.0489   0.5866   0.0303
  -4.750  -0.0607   0.04880   0.04471  -0.0512   0.5825   0.0310
  -4.500  -0.0211   0.04234   0.03770  -0.0567   0.5790   0.0331
  -4.250  -0.0011   0.03978   0.03516  -0.0573   0.5742   0.0333
  -4.000   0.0212   0.03789   0.03321  -0.0578   0.5696   0.0336
  -3.750   0.0451   0.03615   0.03138  -0.0584   0.5651   0.0339
  -3.500   0.0706   0.03432   0.02948  -0.0590   0.5603   0.0345
  -3.250   0.0972   0.03239   0.02742  -0.0596   0.5555   0.0354
  -3.000   0.1296   0.02893   0.02338  -0.0599   0.5515   0.0381
  -2.750   0.1547   0.02742   0.02186  -0.0603   0.5467   0.0384
  -2.500   0.1811   0.02614   0.02054  -0.0606   0.5414   0.0390
  -2.250   0.2083   0.02489   0.01916  -0.0608   0.5362   0.0399
  -2.000   0.2392   0.02314   0.01685  -0.0604   0.5316   0.0435
  -1.750   0.2661   0.02174   0.01550  -0.0608   0.5265   0.0442
  -1.500   0.2937   0.02080   0.01450  -0.0610   0.5214   0.0452
  -1.250   0.3240   0.02011   0.01335  -0.0607   0.5168   0.0498
  -1.000   0.3513   0.01882   0.01211  -0.0610   0.5121   0.0508
  -0.750   0.3797   0.01809   0.01135  -0.0612   0.5070   0.0527
  -0.500   0.4091   0.01743   0.01042  -0.0611   0.5021   0.0579
  -0.250   0.4371   0.01673   0.00969  -0.0612   0.4975   0.0599
   0.750   0.3356   0.02462   0.02047  -0.1038   0.4925   0.0509
   1.000   0.5852   0.01326   0.00544  -0.0602   0.4759   0.0433
   1.250   0.6138   0.01286   0.00504  -0.0602   0.4708   0.0430
   1.500   0.6421   0.01265   0.00473  -0.0601   0.4653   0.0431
   1.750   0.6703   0.01212   0.00430  -0.0601   0.4603   0.0442
   2.000   0.6988   0.01191   0.00410  -0.0602   0.4557   0.0448
   2.250   0.7272   0.01178   0.00396  -0.0602   0.4516   0.0454
   2.500   0.7556   0.01173   0.00388  -0.0602   0.4476   0.0465
   2.750   0.7845   0.01163   0.00383  -0.0604   0.4438   0.0480
   3.000   0.8132   0.01159   0.00380  -0.0605   0.4400   0.0495
   3.250   0.8417   0.01156   0.00377  -0.0606   0.4363   0.0536
   3.500   0.8699   0.01164   0.00379  -0.0607   0.4322   0.0592
   3.750   0.8974   0.00969   0.00400  -0.0609   0.4288   1.0000
   4.000   0.9257   0.00980   0.00405  -0.0610   0.4247   1.0000
   4.250   0.9538   0.00994   0.00412  -0.0610   0.4202   1.0000
   4.500   0.9813   0.01016   0.00424  -0.0610   0.4154   1.0000
   4.750   1.0096   0.01024   0.00434  -0.0611   0.4110   1.0000
   5.000   1.0376   0.01036   0.00445  -0.0612   0.4063   1.0000
   5.250   1.0652   0.01054   0.00458  -0.0613   0.4017   1.0000
   5.500   1.0929   0.01072   0.00474  -0.0613   0.3974   1.0000
   5.750   1.1209   0.01084   0.00488  -0.0615   0.3929   1.0000
   6.000   1.1485   0.01099   0.00503  -0.0615   0.3884   1.0000
   6.250   1.1755   0.01122   0.00520  -0.0616   0.3838   1.0000
   6.500   1.2032   0.01137   0.00539  -0.0617   0.3793   1.0000
   6.750   1.2307   0.01152   0.00556  -0.0618   0.3741   1.0000
   7.000   1.2575   0.01173   0.00575  -0.0618   0.3689   1.0000
   7.250   1.2846   0.01192   0.00595  -0.0619   0.3632   1.0000
   7.500   1.3114   0.01210   0.00615  -0.0620   0.3562   1.0000
   7.750   1.3376   0.01236   0.00638  -0.0620   0.3499   1.0000
   8.000   1.3643   0.01254   0.00661  -0.0620   0.3428   1.0000
   8.250   1.3897   0.01285   0.00689  -0.0620   0.3356   1.0000
   8.500   1.4160   0.01307   0.00715  -0.0620   0.3279   1.0000
   8.750   1.4406   0.01343   0.00747  -0.0619   0.3196   1.0000
   9.000   1.4658   0.01373   0.00780  -0.0618   0.3103   1.0000
   9.250   1.4897   0.01412   0.00818  -0.0616   0.3011   1.0000
   9.500   1.5127   0.01458   0.00861  -0.0614   0.2916   1.0000
   9.750   1.5359   0.01501   0.00905  -0.0611   0.2830   1.0000
  10.000   1.5569   0.01558   0.00959  -0.0607   0.2748   1.0000
  10.250   1.5788   0.01606   0.01010  -0.0603   0.2670   1.0000
  10.500   1.5979   0.01672   0.01073  -0.0597   0.2599   1.0000
  10.750   1.6180   0.01727   0.01132  -0.0592   0.2527   1.0000
  11.000   1.6336   0.01808   0.01211  -0.0583   0.2456   1.0000
  11.250   1.6513   0.01872   0.01279  -0.0575   0.2390   1.0000
  11.500   1.6605   0.01973   0.01381  -0.0560   0.2330   1.0000
  11.750   1.6730   0.02072   0.01485  -0.0552   0.2278   1.0000
  12.000   1.6841   0.02198   0.01616  -0.0547   0.2225   1.0000
  12.250   1.6908   0.02376   0.01795  -0.0543   0.2172   1.0000
  12.500   1.7037   0.02506   0.01933  -0.0542   0.2125   1.0000
  12.750   1.7122   0.02678   0.02110  -0.0540   0.2075   1.0000
  13.250   1.7255   0.03054   0.02496  -0.0535   0.1978   1.0000
  13.500   1.7299   0.03263   0.02710  -0.0531   0.1928   1.0000
  13.750   1.7294   0.03517   0.02966  -0.0527   0.1881   1.0000
  14.000   1.7358   0.03707   0.03165  -0.0524   0.1829   1.0000
  14.250   1.7336   0.03980   0.03441  -0.0520   0.1770   1.0000
  14.500   1.7329   0.04239   0.03706  -0.0516   0.1714   1.0000
  14.750   1.7282   0.04542   0.04013  -0.0513   0.1642   1.0000
  15.000   1.7222   0.04862   0.04336  -0.0510   0.1565   1.0000
  15.250   1.7114   0.05251   0.04725  -0.0509   0.1479   1.0000
  15.500   1.7017   0.05642   0.05117  -0.0509   0.1381   1.0000
  15.750   1.6895   0.06070   0.05547  -0.0511   0.1283   1.0000
  16.000   1.6752   0.06533   0.06010  -0.0514   0.1191   1.0000
  16.250   1.6605   0.07012   0.06489  -0.0518   0.1118   1.0000
  16.500   1.6476   0.07473   0.06953  -0.0522   0.1060   1.0000
  16.750   1.6357   0.07930   0.07413  -0.0528   0.1017   1.0000
  17.000   1.6263   0.08359   0.07846  -0.0533   0.0982   1.0000
  17.250   1.6143   0.08826   0.08318  -0.0541   0.0950   1.0000
<< Back to GOE 324 (HANSA-BRANDENBURG) AIRFOIL (goe324-il)

Polar data table (+)

Polar graphs


<< Back to GOE 324 (HANSA-BRANDENBURG) AIRFOIL (goe324-il)