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

GOE 321 (HANSA-BRANDENBURG III.1) AIRFOIL (goe321-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 321 (HANSA-BRANDENBURG III.1) AIRFOIL (goe321-il)
Reynolds number: 1,000,000
Max Cl/Cd: 120.94 at α=3.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe321-il-1000000.txt
Download as CSV file: xf-goe321-il-1000000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.2359   0.09658   0.09412  -0.0194   0.7114   0.0201
  -9.250  -0.2315   0.09331   0.09084  -0.0204   0.7073   0.0207
  -9.000  -0.3343   0.09980   0.09729  -0.0116   0.7207   0.0198
  -8.750  -0.3272   0.09686   0.09433  -0.0131   0.7154   0.0203
  -8.500  -0.3205   0.09377   0.09121  -0.0149   0.7104   0.0210
  -8.250  -0.3247   0.08779   0.08524  -0.0223   0.7066   0.0222
  -8.000  -0.3225   0.08339   0.08085  -0.0268   0.7020   0.0222
  -7.750  -0.3125   0.07857   0.07600  -0.0327   0.6972   0.0223
  -7.500  -0.3063   0.07386   0.07124  -0.0358   0.6924   0.0225
  -7.250  -0.2923   0.07120   0.06859  -0.0374   0.6876   0.0227
  -7.000  -0.2769   0.06844   0.06579  -0.0397   0.6820   0.0228
  -6.750  -0.2603   0.06564   0.06293  -0.0424   0.6763   0.0231
  -6.500  -0.2421   0.06262   0.05988  -0.0454   0.6708   0.0235
  -6.250  -0.2226   0.05924   0.05644  -0.0488   0.6645   0.0242
  -5.750  -0.1530   0.03098   0.02796  -0.0597   0.6395   0.0265
  -5.500  -0.1341   0.02863   0.02553  -0.0604   0.6303   0.0267
  -5.250  -0.1136   0.02671   0.02354  -0.0610   0.6215   0.0270
  -5.000  -0.0922   0.02459   0.02132  -0.0618   0.6119   0.0274
  -4.750  -0.0698   0.02229   0.01891  -0.0627   0.6033   0.0280
  -4.500  -0.0463   0.01961   0.01605  -0.0637   0.5953   0.0291
  -4.250  -0.0225   0.01306   0.00893  -0.0650   0.5911   0.0311
  -4.000   0.0017   0.01194   0.00771  -0.0653   0.5835   0.0314
  -3.750   0.0265   0.01102   0.00669  -0.0654   0.5761   0.0317
  -3.500   0.0519   0.01016   0.00572  -0.0656   0.5684   0.0323
  -3.250   0.0779   0.00930   0.00471  -0.0657   0.5615   0.0335
  -2.750   0.1339   0.01410   0.00807  -0.0671   0.5571   0.0302
  -2.500   0.1624   0.01328   0.00707  -0.0671   0.5513   0.0304
  -2.250   0.1907   0.01231   0.00587  -0.0671   0.5457   0.0309
  -2.000   0.2192   0.01143   0.00490  -0.0671   0.5407   0.0312
  -1.750   0.2476   0.01095   0.00436  -0.0672   0.5347   0.0316
  -1.500   0.2762   0.01066   0.00401  -0.0672   0.5295   0.0320
  -1.250   0.3051   0.01035   0.00369  -0.0673   0.5260   0.0324
  -1.000   0.3339   0.01008   0.00341  -0.0673   0.5221   0.0329
  -0.750   0.3627   0.00986   0.00316  -0.0674   0.5182   0.0334
  -0.500   0.3913   0.00968   0.00294  -0.0675   0.5141   0.0340
  -0.250   0.4203   0.00951   0.00276  -0.0676   0.5107   0.0348
   0.000   0.4494   0.00940   0.00265  -0.0677   0.5069   0.0356
   0.250   0.4782   0.00916   0.00238  -0.0678   0.5031   0.0365
   0.500   0.5070   0.00903   0.00224  -0.0679   0.4987   0.0377
   0.750   0.5360   0.00895   0.00216  -0.0681   0.4944   0.0390
   1.000   0.5652   0.00887   0.00209  -0.0682   0.4897   0.0404
   1.250   0.5942   0.00884   0.00204  -0.0684   0.4841   0.0418
   1.500   0.6231   0.00877   0.00196  -0.0685   0.4792   0.0455
   1.750   0.6523   0.00871   0.00193  -0.0687   0.4748   0.0503
   2.000   0.6813   0.00865   0.00192  -0.0689   0.4693   0.0636
   2.250   0.7101   0.00861   0.00194  -0.0691   0.4634   0.0975
   2.500   0.7351   0.00659   0.00211  -0.0690   0.4578   1.0000
   2.750   0.7637   0.00668   0.00213  -0.0691   0.4498   1.0000
   3.000   0.7923   0.00676   0.00216  -0.0692   0.4411   1.0000
   3.250   0.8208   0.00687   0.00220  -0.0693   0.4294   1.0000
   3.500   0.8490   0.00702   0.00226  -0.0694   0.4123   1.0000
   3.750   0.8765   0.00727   0.00236  -0.0694   0.3847   1.0000
   4.000   0.9033   0.00762   0.00254  -0.0694   0.3528   1.0000
   4.250   0.9301   0.00797   0.00274  -0.0694   0.3280   1.0000
   4.500   0.9570   0.00830   0.00295  -0.0694   0.3090   1.0000
   4.750   0.9840   0.00858   0.00314  -0.0694   0.2926   1.0000
   5.000   1.0110   0.00887   0.00334  -0.0694   0.2760   1.0000
   5.250   1.0377   0.00918   0.00356  -0.0694   0.2574   1.0000
   5.500   1.0638   0.00956   0.00380  -0.0693   0.2352   1.0000
   5.750   1.0895   0.00996   0.00409  -0.0692   0.2144   1.0000
   6.000   1.1154   0.01032   0.00435  -0.0690   0.2002   1.0000
   6.250   1.1416   0.01062   0.00460  -0.0690   0.1922   1.0000
   6.500   1.1678   0.01092   0.00487  -0.0689   0.1860   1.0000
   6.750   1.1944   0.01116   0.00510  -0.0688   0.1827   1.0000
   7.000   1.2205   0.01143   0.00535  -0.0687   0.1797   1.0000
   7.250   1.2463   0.01172   0.00564  -0.0686   0.1767   1.0000
   7.500   1.2716   0.01205   0.00596  -0.0684   0.1736   1.0000
   7.750   1.2976   0.01230   0.00623  -0.0683   0.1717   1.0000
   8.000   1.3237   0.01251   0.00647  -0.0682   0.1700   1.0000
   8.250   1.3493   0.01276   0.00674  -0.0681   0.1683   1.0000
   8.500   1.3745   0.01304   0.00703  -0.0679   0.1661   1.0000
   8.750   1.3991   0.01335   0.00736  -0.0676   0.1641   1.0000
   9.000   1.4230   0.01372   0.00773  -0.0673   0.1618   1.0000
   9.250   1.4458   0.01415   0.00817  -0.0668   0.1591   1.0000
   9.500   1.4700   0.01444   0.00850  -0.0665   0.1577   1.0000
   9.750   1.4951   0.01465   0.00875  -0.0663   0.1563   1.0000
  10.000   1.5196   0.01489   0.00903  -0.0660   0.1543   1.0000
  10.250   1.5433   0.01517   0.00934  -0.0657   0.1517   1.0000
  10.500   1.5653   0.01557   0.00973  -0.0651   0.1480   1.0000
  10.750   1.5850   0.01609   0.01027  -0.0643   0.1441   1.0000
  11.000   1.6103   0.01621   0.01044  -0.0641   0.1416   1.0000
  11.250   1.6327   0.01651   0.01074  -0.0636   0.1365   1.0000
  11.500   1.6519   0.01700   0.01122  -0.0627   0.1303   1.0000
  11.750   1.6710   0.01745   0.01163  -0.0618   0.1206   1.0000
  12.000   1.6686   0.01892   0.01284  -0.0580   0.0875   1.0000
  12.250   1.6537   0.02141   0.01517  -0.0535   0.0603   1.0000
  12.500   1.6397   0.02442   0.01804  -0.0504   0.0371   1.0000
  12.750   1.6336   0.02725   0.02083  -0.0489   0.0244   1.0000
  13.000   1.6361   0.02950   0.02311  -0.0481   0.0205   1.0000
  13.250   1.6410   0.03158   0.02524  -0.0475   0.0188   1.0000
  13.500   1.6431   0.03395   0.02767  -0.0469   0.0174   1.0000
  13.750   1.6481   0.03605   0.02984  -0.0465   0.0167   1.0000
  14.000   1.6513   0.03833   0.03219  -0.0460   0.0160   1.0000
  14.250   1.6522   0.04086   0.03480  -0.0456   0.0154   1.0000
  14.500   1.6505   0.04371   0.03772  -0.0452   0.0148   1.0000
  14.750   1.6452   0.04700   0.04111  -0.0448   0.0143   1.0000
  15.000   1.6438   0.04993   0.04412  -0.0446   0.0140   1.0000
  15.250   1.6426   0.05292   0.04720  -0.0446   0.0137   1.0000
  15.500   1.6399   0.05615   0.05052  -0.0447   0.0134   1.0000
  15.750   1.6365   0.05959   0.05406  -0.0449   0.0132   1.0000
  16.000   1.6320   0.06326   0.05782  -0.0453   0.0129   1.0000
  16.250   1.6260   0.06717   0.06182  -0.0457   0.0127   1.0000
  16.500   1.6182   0.07138   0.06613  -0.0463   0.0124   1.0000
  16.750   1.6085   0.07594   0.07079  -0.0471   0.0122   1.0000
  17.000   1.5967   0.08087   0.07583  -0.0481   0.0120   1.0000
  17.250   1.5826   0.08622   0.08128  -0.0492   0.0119   1.0000
  17.500   1.5663   0.09205   0.08723  -0.0506   0.0117   1.0000
  17.750   1.5477   0.09838   0.09369  -0.0524   0.0116   1.0000
  18.000   1.5275   0.10509   0.10053  -0.0544   0.0115   1.0000
<< Back to GOE 321 (HANSA-BRANDENBURG III.1) AIRFOIL (goe321-il)

Polar data table (+)

Polar graphs


<< Back to GOE 321 (HANSA-BRANDENBURG III.1) AIRFOIL (goe321-il)