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GOE 321 (HANSA-BRANDENBURG III.1) AIRFOIL (goe321-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: GOE 321 (HANSA-BRANDENBURG III.1) AIRFOIL (goe321-il)
Reynolds number: 1,000,000
Max Cl/Cd: 104.55 at α=8.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe321-il-1000000-n5.txt
Download as CSV file: xf-goe321-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 321 (HANSA-BRANDENBURG III.1) 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.3664   0.10359   0.10083  -0.0101   0.6771   0.0137
  -9.500  -0.3623   0.09986   0.09711  -0.0120   0.6731   0.0141
  -9.250  -0.3733   0.09228   0.08952  -0.0163   0.6701   0.0152
  -9.000  -0.3652   0.08969   0.08692  -0.0179   0.6649   0.0153
  -8.750  -0.3568   0.08713   0.08435  -0.0196   0.6601   0.0154
  -8.500  -0.3484   0.08452   0.08174  -0.0214   0.6547   0.0155
  -8.250  -0.3409   0.08171   0.07892  -0.0236   0.6489   0.0157
  -8.000  -0.3349   0.07852   0.07572  -0.0267   0.6437   0.0159
  -7.750  -0.3242   0.07452   0.07170  -0.0316   0.6376   0.0162
  -7.500  -0.3118   0.07009   0.06723  -0.0371   0.6310   0.0165
  -7.250  -0.3063   0.05735   0.05433  -0.0511   0.6277   0.0181
  -7.000  -0.2870   0.05399   0.05089  -0.0542   0.6194   0.0183
  -6.750  -0.2663   0.05091   0.04770  -0.0568   0.6111   0.0184
  -6.500  -0.2777   0.01890   0.01390  -0.0681   0.6135   0.0216
  -6.250  -0.2511   0.01797   0.01282  -0.0681   0.6033   0.0218
  -6.000  -0.2237   0.01742   0.01215  -0.0682   0.5931   0.0220
  -5.500  -0.1689   0.01602   0.01045  -0.0683   0.5741   0.0224
  -5.000  -0.1136   0.01456   0.00867  -0.0683   0.5592   0.0228
  -4.750  -0.0857   0.01392   0.00787  -0.0684   0.5523   0.0231
  -4.500  -0.0576   0.01333   0.00714  -0.0684   0.5469   0.0233
  -4.250  -0.0292   0.01279   0.00649  -0.0684   0.5421   0.0236
  -4.000  -0.0008   0.01233   0.00592  -0.0685   0.5377   0.0238
  -3.500   0.0562   0.01155   0.00496  -0.0686   0.5279   0.0243
  -3.250   0.0848   0.01124   0.00456  -0.0686   0.5215   0.0245
  -2.750   0.1422   0.01071   0.00391  -0.0687   0.5125   0.0249
  -2.500   0.1711   0.01051   0.00366  -0.0688   0.5080   0.0251
  -2.250   0.1998   0.01030   0.00340  -0.0688   0.5031   0.0254
  -2.000   0.2284   0.01002   0.00307  -0.0689   0.4985   0.0259
  -1.750   0.2573   0.00983   0.00287  -0.0690   0.4947   0.0263
  -1.500   0.2862   0.00968   0.00271  -0.0691   0.4897   0.0266
  -1.250   0.3151   0.00957   0.00257  -0.0692   0.4850   0.0270
  -1.000   0.3441   0.00947   0.00245  -0.0694   0.4810   0.0274
  -0.750   0.3731   0.00935   0.00233  -0.0695   0.4774   0.0278
  -0.500   0.4022   0.00925   0.00222  -0.0696   0.4730   0.0283
  -0.250   0.4311   0.00918   0.00213  -0.0697   0.4678   0.0287
   0.000   0.4601   0.00912   0.00205  -0.0699   0.4631   0.0292
   0.250   0.4892   0.00906   0.00198  -0.0700   0.4585   0.0296
   0.500   0.5182   0.00899   0.00190  -0.0702   0.4523   0.0303
   0.750   0.5472   0.00895   0.00185  -0.0704   0.4459   0.0315
   1.000   0.5761   0.00894   0.00183  -0.0705   0.4370   0.0328
   1.250   0.6049   0.00896   0.00181  -0.0707   0.4243   0.0340
   1.500   0.6333   0.00906   0.00182  -0.0708   0.4023   0.0350
   1.750   0.6609   0.00927   0.00189  -0.0708   0.3669   0.0378
   2.250   0.7163   0.00968   0.00212  -0.0710   0.3186   0.0498
   2.500   0.7443   0.00982   0.00224  -0.0711   0.3043   0.0646
   2.750   0.7722   0.00995   0.00236  -0.0712   0.2916   0.0845
   3.000   0.8001   0.01000   0.00249  -0.0714   0.2791   0.1500
   3.250   0.8234   0.00834   0.00276  -0.0709   0.2679   1.0000
   3.500   0.8510   0.00857   0.00289  -0.0710   0.2544   1.0000
   3.750   0.8783   0.00882   0.00304  -0.0710   0.2389   1.0000
   4.000   0.9053   0.00911   0.00321  -0.0710   0.2211   1.0000
   4.250   0.9320   0.00943   0.00341  -0.0710   0.2036   1.0000
   4.500   0.9589   0.00971   0.00361  -0.0709   0.1910   1.0000
   4.750   0.9861   0.00995   0.00378  -0.0709   0.1833   1.0000
   5.000   1.0132   0.01017   0.00397  -0.0709   0.1778   1.0000
   5.250   1.0402   0.01040   0.00416  -0.0709   0.1727   1.0000
   5.500   1.0675   0.01058   0.00433  -0.0710   0.1703   1.0000
   5.750   1.0947   0.01078   0.00451  -0.0710   0.1681   1.0000
   6.000   1.1216   0.01098   0.00470  -0.0710   0.1660   1.0000
   6.250   1.1484   0.01119   0.00490  -0.0709   0.1640   1.0000
   6.500   1.1750   0.01142   0.00512  -0.0709   0.1620   1.0000
   6.750   1.2015   0.01165   0.00535  -0.0708   0.1600   1.0000
   7.000   1.2277   0.01189   0.00559  -0.0708   0.1581   1.0000
   7.250   1.2539   0.01212   0.00583  -0.0707   0.1569   1.0000
   7.500   1.2803   0.01233   0.00606  -0.0706   0.1564   1.0000
   7.750   1.3065   0.01253   0.00629  -0.0706   0.1557   1.0000
   8.000   1.3325   0.01275   0.00653  -0.0705   0.1542   1.0000
   8.250   1.3581   0.01299   0.00678  -0.0703   0.1525   1.0000
   8.500   1.3833   0.01326   0.00706  -0.0701   0.1502   1.0000
   8.750   1.4080   0.01355   0.00736  -0.0699   0.1480   1.0000
   9.000   1.4324   0.01386   0.00767  -0.0696   0.1461   1.0000
   9.250   1.4563   0.01419   0.00802  -0.0693   0.1438   1.0000
   9.500   1.4802   0.01450   0.00836  -0.0689   0.1421   1.0000
   9.750   1.5049   0.01473   0.00864  -0.0687   0.1410   1.0000
  10.000   1.5291   0.01499   0.00892  -0.0684   0.1387   1.0000
  10.250   1.5521   0.01531   0.00925  -0.0680   0.1349   1.0000
  10.500   1.5735   0.01574   0.00967  -0.0673   0.1302   1.0000
  10.750   1.5957   0.01609   0.01004  -0.0668   0.1266   1.0000
  11.000   1.6148   0.01661   0.01050  -0.0659   0.1169   1.0000
  11.250   1.6185   0.01803   0.01166  -0.0630   0.0832   1.0000
  11.500   1.6131   0.01967   0.01320  -0.0587   0.0624   1.0000
  11.750   1.6073   0.02168   0.01511  -0.0554   0.0428   1.0000
  12.000   1.5974   0.02440   0.01772  -0.0526   0.0223   1.0000
  12.250   1.6028   0.02618   0.01951  -0.0515   0.0176   1.0000
  12.500   1.6110   0.02783   0.02121  -0.0508   0.0157   1.0000
  12.750   1.6191   0.02955   0.02298  -0.0503   0.0145   1.0000
  13.000   1.6263   0.03140   0.02488  -0.0498   0.0135   1.0000
  13.250   1.6342   0.03318   0.02673  -0.0493   0.0129   1.0000
  13.500   1.6406   0.03512   0.02873  -0.0489   0.0123   1.0000
  13.750   1.6453   0.03724   0.03091  -0.0484   0.0117   1.0000
  14.000   1.6482   0.03955   0.03328  -0.0480   0.0112   1.0000
  14.250   1.6499   0.04201   0.03580  -0.0476   0.0107   1.0000
  14.500   1.6530   0.04435   0.03822  -0.0472   0.0104   1.0000
  14.750   1.6546   0.04686   0.04081  -0.0470   0.0101   1.0000
  15.000   1.6550   0.04956   0.04359  -0.0467   0.0098   1.0000
  15.250   1.6544   0.05244   0.04654  -0.0467   0.0095   1.0000
  15.500   1.6529   0.05550   0.04968  -0.0467   0.0093   1.0000
  15.750   1.6506   0.05877   0.05303  -0.0468   0.0090   1.0000
  16.000   1.6472   0.06226   0.05659  -0.0471   0.0088   1.0000
  16.250   1.6422   0.06599   0.06042  -0.0475   0.0086   1.0000
  16.500   1.6359   0.06995   0.06446  -0.0480   0.0083   1.0000
  16.750   1.6318   0.07368   0.06828  -0.0485   0.0082   1.0000
  17.000   1.6263   0.07764   0.07234  -0.0492   0.0081   1.0000
  17.250   1.6190   0.08188   0.07667  -0.0499   0.0080   1.0000
  17.500   1.6107   0.08635   0.08124  -0.0508   0.0079   1.0000
  17.750   1.6014   0.09106   0.08605  -0.0519   0.0078   1.0000
  18.000   1.5910   0.09599   0.09109  -0.0531   0.0077   1.0000
  18.250   1.5795   0.10115   0.09636  -0.0545   0.0075   1.0000
  18.500   1.5670   0.10659   0.10191  -0.0561   0.0074   1.0000
  18.750   1.5538   0.11225   0.10767  -0.0579   0.0073   1.0000
  19.000   1.5390   0.11822   0.11375  -0.0600   0.0073   1.0000
  19.250   1.5235   0.12441   0.12006  -0.0623   0.0072   1.0000
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