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GOE 322 (HANSA-BRANDENBURG IV.1) AIRFOIL (goe322-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 322 (HANSA-BRANDENBURG IV.1) AIRFOIL (goe322-il)
Reynolds number: 1,000,000
Max Cl/Cd: 123.22 at α=5.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe322-il-1000000.txt
Download as CSV file: xf-goe322-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 322 (HANSA-BRANDENBURG IV.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.2227   0.08755   0.08484  -0.0396   0.6862   0.0219
  -8.250  -0.2190   0.08340   0.08070  -0.0428   0.6831   0.0220
  -8.000  -0.2170   0.07933   0.07663  -0.0462   0.6800   0.0220
  -7.750  -0.2139   0.07466   0.07194  -0.0497   0.6768   0.0223
  -7.500  -0.2011   0.07194   0.06920  -0.0522   0.6735   0.0225
  -7.250  -0.1866   0.06923   0.06649  -0.0547   0.6702   0.0227
  -7.000  -0.1709   0.06646   0.06370  -0.0576   0.6665   0.0229
  -6.750  -0.1541   0.06345   0.06065  -0.0609   0.6627   0.0234
  -6.500  -0.1360   0.05997   0.05711  -0.0649   0.6588   0.0240
  -6.000  -0.0942   0.04304   0.03980  -0.0804   0.6532   0.0265
  -5.750  -0.0726   0.04114   0.03783  -0.0813   0.6491   0.0267
  -5.500  -0.0498   0.03951   0.03612  -0.0822   0.6446   0.0270
  -5.250  -0.0259   0.03773   0.03425  -0.0831   0.6398   0.0275
  -5.000  -0.0011   0.03540   0.03182  -0.0842   0.6344   0.0282
  -4.750   0.0223   0.02498   0.02066  -0.0865   0.6309   0.0316
  -4.500   0.0484   0.02405   0.01965  -0.0867   0.6251   0.0319
  -4.250   0.0751   0.02304   0.01857  -0.0871   0.6189   0.0323
  -4.000   0.1020   0.02193   0.01732  -0.0873   0.6125   0.0329
  -3.750   0.1277   0.01574   0.01007  -0.0869   0.6081   0.0314
  -3.500   0.1559   0.01451   0.00876  -0.0870   0.6025   0.0300
  -3.250   0.1842   0.01344   0.00749  -0.0871   0.5970   0.0297
  -3.000   0.2130   0.01265   0.00655  -0.0872   0.5916   0.0296
  -2.750   0.2419   0.01202   0.00581  -0.0873   0.5855   0.0296
  -2.500   0.2708   0.01163   0.00531  -0.0874   0.5795   0.0300
  -2.250   0.2999   0.01129   0.00491  -0.0875   0.5743   0.0304
  -2.000   0.3290   0.01096   0.00451  -0.0877   0.5686   0.0306
  -1.500   0.3869   0.01030   0.00374  -0.0879   0.5573   0.0311
  -1.250   0.4155   0.00989   0.00329  -0.0881   0.5514   0.0315
  -1.000   0.4442   0.00965   0.00301  -0.0882   0.5460   0.0320
  -0.750   0.4734   0.00944   0.00281  -0.0884   0.5409   0.0325
  -0.500   0.5024   0.00932   0.00265  -0.0886   0.5343   0.0330
  -0.250   0.5314   0.00921   0.00252  -0.0888   0.5274   0.0337
   0.000   0.5605   0.00913   0.00241  -0.0890   0.5202   0.0347
   0.250   0.5895   0.00909   0.00234  -0.0892   0.5140   0.0357
   0.500   0.6188   0.00903   0.00227  -0.0894   0.5085   0.0365
   0.750   0.6478   0.00896   0.00217  -0.0897   0.5024   0.0384
   1.000   0.6768   0.00894   0.00213  -0.0899   0.4963   0.0408
   1.250   0.7059   0.00891   0.00211  -0.0901   0.4890   0.0468
   1.500   0.7347   0.00887   0.00215  -0.0904   0.4816   0.0836
   1.750   0.7636   0.00880   0.00221  -0.0906   0.4733   0.1335
   2.000   0.7922   0.00880   0.00226  -0.0909   0.4647   0.1731
   2.250   0.8186   0.00704   0.00245  -0.0912   0.4555   1.0000
   2.500   0.8469   0.00717   0.00250  -0.0913   0.4460   1.0000
   2.750   0.8750   0.00732   0.00257  -0.0914   0.4354   1.0000
   3.000   0.9033   0.00745   0.00264  -0.0916   0.4242   1.0000
   3.250   0.9313   0.00762   0.00273  -0.0917   0.4123   1.0000
   3.500   0.9590   0.00781   0.00283  -0.0918   0.3994   1.0000
   3.750   0.9865   0.00802   0.00296  -0.0919   0.3861   1.0000
   4.000   1.0138   0.00825   0.00311  -0.0920   0.3731   1.0000
   4.250   1.0412   0.00847   0.00325  -0.0921   0.3614   1.0000
   4.500   1.0685   0.00868   0.00340  -0.0921   0.3514   1.0000
   4.750   1.0954   0.00892   0.00358  -0.0922   0.3418   1.0000
   5.000   1.1227   0.00912   0.00374  -0.0923   0.3337   1.0000
   5.250   1.1495   0.00936   0.00393  -0.0923   0.3259   1.0000
   5.500   1.1767   0.00955   0.00410  -0.0924   0.3189   1.0000
   5.750   1.2030   0.00981   0.00431  -0.0923   0.3113   1.0000
   6.000   1.2299   0.01000   0.00448  -0.0924   0.3043   1.0000
   6.250   1.2557   0.01030   0.00472  -0.0923   0.2946   1.0000
   6.500   1.2821   0.01051   0.00491  -0.0923   0.2871   1.0000
   6.750   1.3077   0.01079   0.00515  -0.0922   0.2788   1.0000
   7.000   1.3334   0.01105   0.00537  -0.0921   0.2700   1.0000
   7.250   1.3586   0.01134   0.00563  -0.0919   0.2605   1.0000
   7.500   1.3827   0.01170   0.00592  -0.0916   0.2495   1.0000
   7.750   1.4064   0.01208   0.00623  -0.0913   0.2365   1.0000
   8.000   1.4291   0.01251   0.00659  -0.0908   0.2226   1.0000
   8.250   1.4508   0.01299   0.00699  -0.0902   0.2084   1.0000
   8.500   1.4715   0.01351   0.00743  -0.0894   0.1951   1.0000
   8.750   1.4918   0.01402   0.00789  -0.0885   0.1839   1.0000
   9.000   1.5107   0.01459   0.00839  -0.0875   0.1730   1.0000
   9.250   1.5287   0.01517   0.00892  -0.0863   0.1637   1.0000
   9.500   1.5453   0.01578   0.00948  -0.0850   0.1545   1.0000
   9.750   1.5599   0.01642   0.01008  -0.0833   0.1437   1.0000
  10.000   1.5652   0.01737   0.01092  -0.0801   0.1280   1.0000
  10.250   1.5483   0.01981   0.01308  -0.0749   0.0841   1.0000
  10.500   1.5216   0.02377   0.01683  -0.0706   0.0388   1.0000
  10.750   1.5163   0.02658   0.01959  -0.0689   0.0178   1.0000
  11.000   1.5250   0.02822   0.02127  -0.0681   0.0158   1.0000
  11.250   1.5345   0.02981   0.02292  -0.0675   0.0150   1.0000
  11.500   1.5420   0.03157   0.02475  -0.0667   0.0144   1.0000
  11.750   1.5473   0.03355   0.02679  -0.0659   0.0137   1.0000
  12.000   1.5503   0.03577   0.02909  -0.0651   0.0131   1.0000
  12.250   1.5560   0.03771   0.03110  -0.0644   0.0128   1.0000
  12.500   1.5607   0.03978   0.03323  -0.0637   0.0126   1.0000
  12.750   1.5640   0.04201   0.03553  -0.0630   0.0122   1.0000
  13.000   1.5658   0.04440   0.03799  -0.0623   0.0119   1.0000
  13.250   1.5663   0.04697   0.04064  -0.0617   0.0116   1.0000
  13.500   1.5658   0.04975   0.04350  -0.0612   0.0113   1.0000
  13.750   1.5635   0.05285   0.04668  -0.0608   0.0111   1.0000
  14.000   1.5577   0.05643   0.05036  -0.0605   0.0108   1.0000
  14.250   1.5478   0.06067   0.05471  -0.0604   0.0105   1.0000
  14.500   1.5455   0.06405   0.05817  -0.0604   0.0104   1.0000
  14.750   1.5430   0.06748   0.06170  -0.0605   0.0103   1.0000
  15.000   1.5393   0.07114   0.06544  -0.0607   0.0102   1.0000
  15.250   1.5341   0.07506   0.06945  -0.0609   0.0100   1.0000
  15.500   1.5279   0.07917   0.07366  -0.0613   0.0099   1.0000
  15.750   1.5201   0.08353   0.07811  -0.0618   0.0098   1.0000
  16.000   1.5114   0.08810   0.08278  -0.0625   0.0096   1.0000
  16.250   1.5022   0.09283   0.08761  -0.0632   0.0095   1.0000
  16.500   1.4916   0.09780   0.09267  -0.0641   0.0094   1.0000
  16.750   1.4805   0.10292   0.09790  -0.0652   0.0093   1.0000
  17.000   1.4690   0.10821   0.10329  -0.0664   0.0092   1.0000
  17.250   1.4573   0.11359   0.10877  -0.0677   0.0091   1.0000
  17.500   1.4455   0.11903   0.11431  -0.0692   0.0091   1.0000
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