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GOE 122 (MVA H.2) AIRFOIL (goe122-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 122 (MVA H.2) AIRFOIL (goe122-il)
Reynolds number: 100,000
Max Cl/Cd: 56.65 at α=6.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe122-il-100000-n5.txt
Download as CSV file: xf-goe122-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 122 (MVA H.2) AIRFOIL                       
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.3873   0.09815   0.09346  -0.0097   1.0000   0.0362
  -7.750  -0.3817   0.09500   0.09035  -0.0114   1.0000   0.0372
  -7.500  -0.3767   0.09189   0.08730  -0.0135   1.0000   0.0382
  -7.250  -0.3698   0.08862   0.08408  -0.0166   1.0000   0.0394
  -7.000  -0.3588   0.08521   0.08071  -0.0228   1.0000   0.0411
  -6.750  -0.3411   0.08161   0.07709  -0.0324   1.0000   0.0420
  -6.500  -0.3236   0.07774   0.07314  -0.0383   1.0000   0.0423
  -6.250  -0.3181   0.07298   0.06847  -0.0375   1.0000   0.0430
  -6.000  -0.3143   0.07023   0.06581  -0.0337   1.0000   0.0451
  -5.750  -0.3045   0.06754   0.06314  -0.0343   1.0000   0.0485
  -5.500  -0.2759   0.06457   0.05984  -0.0442   1.0000   0.0540
  -5.250  -0.2737   0.06036   0.05576  -0.0425   1.0000   0.0550
  -5.000  -0.2603   0.05717   0.05262  -0.0421   0.9964   0.0571
  -4.750  -0.2001   0.05360   0.04833  -0.0541   0.9864   0.0670
  -4.500  -0.1781   0.04793   0.04292  -0.0559   0.9779   0.0698
  -4.250  -0.1347   0.04407   0.03870  -0.0622   0.9671   0.0828
  -4.000  -0.0922   0.03724   0.03143  -0.0661   0.9565   0.0487
  -3.750  -0.0523   0.03294   0.02662  -0.0696   0.9453   0.0465
  -3.500  -0.0149   0.02988   0.02312  -0.0721   0.9352   0.0478
  -3.250   0.0199   0.02688   0.01955  -0.0735   0.9236   0.0463
  -3.000   0.0522   0.02495   0.01722  -0.0743   0.9115   0.0480
  -2.750   0.0837   0.02331   0.01517  -0.0747   0.8989   0.0500
  -2.500   0.1140   0.02177   0.01324  -0.0747   0.8859   0.0499
  -2.250   0.1429   0.02052   0.01164  -0.0744   0.8720   0.0502
  -2.000   0.1709   0.01959   0.01043  -0.0739   0.8575   0.0519
  -1.750   0.1984   0.01890   0.00948  -0.0733   0.8422   0.0538
  -1.500   0.2252   0.01809   0.00851  -0.0726   0.8265   0.0540
  -1.250   0.2517   0.01731   0.00764  -0.0719   0.8106   0.0544
  -1.000   0.2779   0.01658   0.00687  -0.0712   0.7941   0.0551
  -0.750   0.3039   0.01602   0.00626  -0.0705   0.7773   0.0562
  -0.500   0.3300   0.01559   0.00576  -0.0697   0.7600   0.0577
  -0.250   0.3563   0.01528   0.00537  -0.0691   0.7418   0.0604
   0.000   0.3828   0.01508   0.00505  -0.0685   0.7235   0.0655
   0.250   0.4092   0.01487   0.00471  -0.0678   0.7053   0.0695
   0.500   0.4359   0.01474   0.00444  -0.0671   0.6873   0.0749
   0.750   0.4630   0.01462   0.00424  -0.0666   0.6689   0.0877
   1.250   0.5176   0.01257   0.00409  -0.0660   0.6334   1.0000
   1.500   0.5440   0.01277   0.00408  -0.0655   0.6159   1.0000
   1.750   0.5704   0.01298   0.00410  -0.0650   0.5983   1.0000
   2.000   0.5968   0.01319   0.00415  -0.0645   0.5801   1.0000
   2.250   0.6231   0.01341   0.00424  -0.0642   0.5615   1.0000
   2.500   0.6494   0.01364   0.00434  -0.0638   0.5435   1.0000
   2.750   0.6757   0.01388   0.00448  -0.0634   0.5267   1.0000
   3.000   0.7020   0.01413   0.00463  -0.0630   0.5113   1.0000
   3.250   0.7283   0.01439   0.00481  -0.0627   0.4975   1.0000
   3.500   0.7545   0.01466   0.00503  -0.0624   0.4839   1.0000
   3.750   0.7806   0.01495   0.00526  -0.0620   0.4710   1.0000
   4.000   0.8067   0.01525   0.00552  -0.0617   0.4585   1.0000
   4.250   0.8325   0.01557   0.00581  -0.0613   0.4463   1.0000
   4.500   0.8585   0.01590   0.00614  -0.0610   0.4352   1.0000
   4.750   0.8847   0.01622   0.00651  -0.0608   0.4253   1.0000
   5.000   0.9105   0.01658   0.00691  -0.0604   0.4158   1.0000
   5.250   0.9358   0.01693   0.00728  -0.0600   0.4025   1.0000
   5.500   0.9607   0.01726   0.00765  -0.0596   0.3845   1.0000
   5.750   0.9853   0.01760   0.00802  -0.0591   0.3646   1.0000
   6.000   1.0097   0.01795   0.00844  -0.0587   0.3463   1.0000
   6.250   1.0342   0.01832   0.00888  -0.0582   0.3293   1.0000
   6.500   1.0586   0.01869   0.00935  -0.0578   0.3094   1.0000
   6.750   1.0826   0.01911   0.00985  -0.0573   0.2881   1.0000
   7.000   1.1064   0.01957   0.01044  -0.0567   0.2668   1.0000
   7.250   1.1288   0.02016   0.01102  -0.0561   0.2355   1.0000
   7.500   1.1495   0.02097   0.01173  -0.0553   0.2008   1.0000
   7.750   1.1666   0.02227   0.01277  -0.0543   0.1597   1.0000
   8.000   1.1816   0.02391   0.01409  -0.0532   0.0844   1.0000
   8.250   1.1943   0.02576   0.01573  -0.0517   0.0624   1.0000
   8.500   1.2080   0.02738   0.01739  -0.0503   0.0543   1.0000
   8.750   1.2220   0.02883   0.01904  -0.0488   0.0491   1.0000
   9.000   1.2298   0.03080   0.02112  -0.0469   0.0446   1.0000
   9.250   1.2402   0.03235   0.02290  -0.0451   0.0416   1.0000
   9.500   1.2476   0.03407   0.02479  -0.0432   0.0383   1.0000
   9.750   1.2501   0.03601   0.02688  -0.0408   0.0357   1.0000
  10.000   1.2474   0.03834   0.02928  -0.0381   0.0339   1.0000
  10.250   1.2497   0.04057   0.03161  -0.0361   0.0323   1.0000
  10.500   1.2560   0.04249   0.03373  -0.0346   0.0303   1.0000
  10.750   1.2610   0.04464   0.03604  -0.0332   0.0282   1.0000
  11.000   1.2664   0.04694   0.03847  -0.0318   0.0268   1.0000
  11.250   1.2720   0.04937   0.04099  -0.0305   0.0255   1.0000
  11.500   1.2779   0.05200   0.04365  -0.0293   0.0242   1.0000
  11.750   1.2838   0.05499   0.04676  -0.0281   0.0229   1.0000
  12.000   1.2841   0.05779   0.04987  -0.0275   0.0220   1.0000
  12.250   1.2837   0.06096   0.05336  -0.0270   0.0211   1.0000
  12.500   1.2821   0.06452   0.05718  -0.0267   0.0206   1.0000
  12.750   1.2778   0.06842   0.06135  -0.0267   0.0201   1.0000
  13.000   1.2708   0.07271   0.06589  -0.0272   0.0198   1.0000
  13.250   1.2615   0.07740   0.07083  -0.0283   0.0195   1.0000
  13.500   1.2500   0.08253   0.07621  -0.0299   0.0193   1.0000
  13.750   1.2365   0.08812   0.08203  -0.0321   0.0192   1.0000
  14.000   1.2213   0.09419   0.08833  -0.0349   0.0191   1.0000
  14.250   1.2047   0.10082   0.09518  -0.0383   0.0191   1.0000
  14.500   1.1868   0.10809   0.10265  -0.0424   0.0192   1.0000
  14.750   1.1678   0.11612   0.11088  -0.0472   0.0193   1.0000
  15.000   1.1478   0.12499   0.11993  -0.0528   0.0195   1.0000
  15.250   1.1270   0.13474   0.12985  -0.0591   0.0199   1.0000
  15.500   1.1054   0.14560   0.14080  -0.0662   0.0202   1.0000
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