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GOE 319 (HANSA-BRANDENBURG II) AIRFOIL (goe319-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: GOE 319 (HANSA-BRANDENBURG II) AIRFOIL (goe319-il)
Reynolds number: 50,000
Max Cl/Cd: 26.13 at α=5.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe319-il-50000.txt
Download as CSV file: xf-goe319-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 319 (HANSA-BRANDENBURG II) AIRFOIL          
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.2587   0.12150   0.11448  -0.0252   1.0000   0.1253
  -9.500  -0.2597   0.12039   0.11345  -0.0270   1.0000   0.1285
  -9.250  -0.2705   0.12117   0.11437  -0.0295   1.0000   0.1299
  -9.000  -0.2566   0.11567   0.10893  -0.0290   1.0000   0.1320
  -8.750  -0.2404   0.11107   0.10436  -0.0279   1.0000   0.1366
  -8.500  -0.2378   0.10894   0.10233  -0.0280   1.0000   0.1411
  -8.250  -0.2461   0.10835   0.10188  -0.0281   1.0000   0.1445
  -8.000  -0.2675   0.10917   0.10292  -0.0266   1.0000   0.1458
  -7.750  -0.2936   0.11015   0.10409  -0.0237   1.0000   0.1462
  -7.500  -0.3186   0.11110   0.10520  -0.0219   1.0000   0.1466
  -7.250  -0.3026   0.10495   0.09911  -0.0178   1.0000   0.1495
  -7.000  -0.3083   0.10312   0.09737  -0.0145   1.0000   0.1520
  -6.750  -0.3207   0.10216   0.09651  -0.0118   1.0000   0.1543
  -6.500  -0.3338   0.10130   0.09575  -0.0099   1.0000   0.1567
  -6.250  -0.3471   0.10056   0.09510  -0.0089   1.0000   0.1596
  -6.000  -0.3621   0.10066   0.09526  -0.0109   1.0000   0.1625
  -5.750  -0.3702   0.09994   0.09456  -0.0139   1.0000   0.1642
  -5.500  -0.3680   0.09571   0.09044  -0.0087   1.0000   0.1667
  -5.250  -0.3682   0.09344   0.08821  -0.0067   1.0000   0.1707
  -5.000  -0.3686   0.09179   0.08658  -0.0077   1.0000   0.1765
  -4.750  -0.3649   0.09047   0.08521  -0.0131   1.0000   0.1816
  -4.500  -0.3538   0.08663   0.08145  -0.0109   0.9970   0.1866
  -4.000  -0.2869   0.08048   0.07509  -0.0266   0.9790   0.2149
  -3.500  -0.2351   0.07427   0.06882  -0.0336   0.9620   0.2486
  -3.250  -0.2073   0.07102   0.06559  -0.0360   0.9545   0.2686
  -3.000  -0.1853   0.06903   0.06352  -0.0394   0.9453   0.2989
  -2.750  -0.1615   0.06610   0.06064  -0.0403   0.9378   0.3348
  -2.500  -0.1520   0.06378   0.05842  -0.0380   0.9296   0.3721
  -2.250  -0.1329   0.06148   0.05620  -0.0364   0.9225   0.4407
  -2.000  -0.1310   0.05949   0.05433  -0.0316   0.9141   0.4789
  -1.750  -0.1137   0.05733   0.05226  -0.0287   0.9067   0.5326
  -1.500  -0.1074   0.05562   0.05064  -0.0247   0.8984   0.5705
  -1.250  -0.0872   0.05367   0.04874  -0.0227   0.8903   0.6153
  -1.000  -0.0709   0.05195   0.04705  -0.0217   0.8815   0.6434
  -0.750  -0.0221   0.04987   0.04491  -0.0281   0.8717   0.6618
  -0.500   0.0657   0.04841   0.04302  -0.0484   0.8579   0.6169
  -0.250   0.2423   0.04942   0.04175  -0.0865   0.8393   0.3008
   0.000   0.2890   0.04914   0.04088  -0.0892   0.8256   0.2388
   0.250   0.3361   0.04841   0.03966  -0.0914   0.8117   0.2079
   0.500   0.3882   0.04720   0.03802  -0.0938   0.7980   0.1876
   0.750   0.4381   0.04611   0.03652  -0.0957   0.7841   0.1763
   1.000   0.4687   0.04560   0.03582  -0.0955   0.7690   0.1722
   1.250   0.5005   0.04519   0.03523  -0.0953   0.7541   0.1733
   1.500   0.5387   0.04472   0.03450  -0.0956   0.7396   0.1772
   1.750   0.5914   0.04342   0.03296  -0.0968   0.7276   0.1819
   2.000   0.6311   0.04242   0.03193  -0.0966   0.7144   0.1944
   2.250   0.6569   0.04219   0.03171  -0.0953   0.6985   0.2120
   2.500   0.6850   0.04169   0.03132  -0.0942   0.6829   0.2443
   2.750   0.7203   0.03942   0.03036  -0.0930   0.6689   1.0000
   3.000   0.7540   0.03912   0.02961  -0.0917   0.6544   1.0000
   3.250   0.7966   0.03802   0.02822  -0.0908   0.6423   1.0000
   3.500   0.8224   0.03808   0.02813  -0.0892   0.6256   1.0000
   3.750   0.8482   0.03815   0.02806  -0.0876   0.6090   1.0000
   4.000   0.8742   0.03819   0.02799  -0.0860   0.5926   1.0000
   4.250   0.8995   0.03831   0.02801  -0.0845   0.5763   1.0000
   4.500   0.9230   0.03867   0.02828  -0.0830   0.5605   1.0000
   4.750   0.9437   0.03941   0.02896  -0.0815   0.5453   1.0000
   5.000   0.9649   0.04018   0.02968  -0.0802   0.5313   1.0000
   5.250   1.0107   0.03868   0.02796  -0.0798   0.5225   1.0000
   5.500   1.0214   0.04047   0.02978  -0.0782   0.5079   1.0000
   5.750   1.0268   0.04292   0.03229  -0.0766   0.4946   1.0000
   6.000   1.0580   0.04297   0.03227  -0.0759   0.4857   1.0000
   6.250   1.0690   0.04489   0.03424  -0.0745   0.4745   1.0000
   6.500   1.0590   0.04898   0.03844  -0.0727   0.4633   1.0000
   6.750   1.1053   0.04752   0.03687  -0.0724   0.4562   1.0000
   7.000   1.0212   0.05947   0.04907  -0.0700   0.4440   1.0000
   7.250   1.1258   0.05173   0.04118  -0.0698   0.4388   1.0000
   7.500   0.9235   0.07952   0.06923  -0.0731   0.4278   1.0000
   7.750   1.0312   0.06910   0.05876  -0.0680   0.4217   1.0000
   8.000   0.9132   0.08876   0.07850  -0.0737   0.4170   1.0000
   8.250   0.8906   0.09555   0.08533  -0.0751   0.4143   1.0000
   8.500   0.8791   0.10111   0.09093  -0.0762   0.4124   1.0000
   8.750   0.8710   0.10633   0.09618  -0.0772   0.4114   1.0000
   9.000   0.8593   0.11244   0.10234  -0.0789   0.4159   1.0000
   9.250   0.8705   0.11707   0.10701  -0.0800   0.4201   1.0000
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