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GOE 180 (MVA H.26) AIRFOIL (goe180-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 180 (MVA H.26) AIRFOIL (goe180-il)
Reynolds number: 100,000
Max Cl/Cd: 55.26 at α=6.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe180-il-100000.txt
Download as CSV file: xf-goe180-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 180 (MVA H.26) 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3540   0.10745   0.10241  -0.0246   1.0000   0.0771
  -8.500  -0.3653   0.10699   0.10207  -0.0280   1.0000   0.0783
  -8.250  -0.3780   0.10625   0.10147  -0.0309   1.0000   0.0787
  -8.000  -0.3715   0.10070   0.09596  -0.0293   1.0000   0.0798
  -7.750  -0.3470   0.09524   0.09045  -0.0257   1.0000   0.0828
  -7.500  -0.3452   0.09267   0.08794  -0.0249   1.0000   0.0851
  -7.250  -0.3478   0.09040   0.08575  -0.0244   1.0000   0.0874
  -7.000  -0.3499   0.08805   0.08348  -0.0259   1.0000   0.0903
  -6.750  -0.3557   0.08683   0.08232  -0.0352   1.0000   0.0931
  -6.500  -0.3547   0.08297   0.07849  -0.0378   1.0000   0.0942
  -6.250  -0.3504   0.07918   0.07479  -0.0308   1.0000   0.0961
  -6.000  -0.3463   0.07672   0.07238  -0.0279   1.0000   0.0994
  -5.750  -0.3424   0.07421   0.06989  -0.0287   1.0000   0.1041
  -5.500  -0.3311   0.07070   0.06622  -0.0383   1.0000   0.1096
  -5.250  -0.3286   0.06762   0.06327  -0.0338   1.0000   0.1115
  -5.000  -0.3219   0.06515   0.06083  -0.0320   1.0000   0.1149
  -4.750  -0.2982   0.06176   0.05715  -0.0406   1.0000   0.1249
  -4.500  -0.2931   0.05869   0.05421  -0.0374   1.0000   0.1270
  -4.250  -0.2718   0.05683   0.05214  -0.0406   1.0000   0.1385
  -4.000  -0.2628   0.05327   0.04865  -0.0397   1.0000   0.1425
  -3.750  -0.2419   0.05101   0.04621  -0.0424   1.0000   0.1563
  -3.500  -0.1992   0.04742   0.04250  -0.0480   0.9942   0.1721
  -3.250  -0.1551   0.04394   0.03896  -0.0532   0.9863   0.1895
  -3.000  -0.1085   0.04106   0.03592  -0.0589   0.9774   0.2193
  -2.500   0.0261   0.02932   0.02199  -0.0748   0.9642   0.1072
  -2.250   0.0764   0.02630   0.01861  -0.0792   0.9560   0.1012
  -2.000   0.1276   0.02419   0.01603  -0.0834   0.9469   0.1007
  -1.750   0.1753   0.02237   0.01381  -0.0866   0.9355   0.0989
  -1.500   0.2240   0.02088   0.01211  -0.0900   0.9248   0.1005
  -1.250   0.2775   0.01952   0.01060  -0.0941   0.9170   0.1065
  -1.000   0.3210   0.01829   0.00946  -0.0965   0.9031   0.1163
  -0.750   0.3621   0.01718   0.00842  -0.0982   0.8879   0.1306
  -0.500   0.3996   0.01565   0.00744  -0.0993   0.8717   0.2431
  -0.250   0.4322   0.01347   0.00697  -0.0988   0.8518   1.0000
   0.000   0.4636   0.01343   0.00663  -0.0987   0.8301   1.0000
   0.250   0.4940   0.01343   0.00636  -0.0984   0.8103   1.0000
   0.500   0.5211   0.01354   0.00626  -0.0978   0.7888   1.0000
   0.750   0.5489   0.01364   0.00615  -0.0972   0.7702   1.0000
   1.000   0.5765   0.01376   0.00606  -0.0966   0.7526   1.0000
   1.250   0.6038   0.01393   0.00602  -0.0961   0.7360   1.0000
   1.500   0.6303   0.01416   0.00609  -0.0955   0.7197   1.0000
   1.750   0.6570   0.01440   0.00618  -0.0949   0.7046   1.0000
   2.000   0.6836   0.01465   0.00629  -0.0944   0.6901   1.0000
   2.250   0.7100   0.01492   0.00643  -0.0938   0.6760   1.0000
   2.500   0.7361   0.01522   0.00666  -0.0933   0.6625   1.0000
   2.750   0.7623   0.01557   0.00696  -0.0929   0.6508   1.0000
   3.000   0.7889   0.01592   0.00725  -0.0926   0.6401   1.0000
   3.250   0.8160   0.01626   0.00751  -0.0922   0.6299   1.0000
   3.500   0.8416   0.01662   0.00787  -0.0918   0.6181   1.0000
   3.750   0.8673   0.01698   0.00824  -0.0913   0.6063   1.0000
   4.000   0.8931   0.01734   0.00857  -0.0907   0.5946   1.0000
   4.250   0.9192   0.01769   0.00889  -0.0902   0.5825   1.0000
   4.500   0.9449   0.01800   0.00916  -0.0895   0.5691   1.0000
   4.750   0.9699   0.01831   0.00945  -0.0887   0.5545   1.0000
   5.000   0.9946   0.01862   0.00977  -0.0879   0.5393   1.0000
   5.250   1.0192   0.01894   0.01008  -0.0871   0.5239   1.0000
   5.500   1.0433   0.01926   0.01043  -0.0862   0.5077   1.0000
   5.750   1.0669   0.01959   0.01082  -0.0852   0.4907   1.0000
   6.000   1.0901   0.01992   0.01123  -0.0842   0.4724   1.0000
   6.250   1.1133   0.02025   0.01159  -0.0832   0.4535   1.0000
   6.500   1.1368   0.02059   0.01192  -0.0822   0.4349   1.0000
   6.750   1.1599   0.02099   0.01234  -0.0811   0.4163   1.0000
   7.000   1.1817   0.02143   0.01288  -0.0800   0.3964   1.0000
   7.250   1.2040   0.02188   0.01338  -0.0789   0.3782   1.0000
   7.500   1.2264   0.02236   0.01388  -0.0778   0.3611   1.0000
   7.750   1.2487   0.02290   0.01446  -0.0768   0.3449   1.0000
   8.000   1.2692   0.02337   0.01497  -0.0755   0.3266   1.0000
   8.250   1.2867   0.02369   0.01532  -0.0737   0.3044   1.0000
   8.500   1.3029   0.02416   0.01573  -0.0719   0.2819   1.0000
   8.750   1.3196   0.02486   0.01644  -0.0703   0.2624   1.0000
   9.000   1.3359   0.02566   0.01726  -0.0687   0.2446   1.0000
   9.250   1.3502   0.02647   0.01811  -0.0669   0.2261   1.0000
   9.500   1.3620   0.02717   0.01902  -0.0647   0.2043   1.0000
   9.750   1.3700   0.02792   0.01993  -0.0620   0.1712   1.0000
  10.000   1.3654   0.02994   0.02156  -0.0581   0.1157   1.0000
  10.250   1.3587   0.03230   0.02372  -0.0538   0.0869   1.0000
  10.500   1.3566   0.03438   0.02574  -0.0503   0.0746   1.0000
  10.750   1.3532   0.03662   0.02795  -0.0473   0.0685   1.0000
  11.000   1.3520   0.03888   0.03031  -0.0446   0.0640   1.0000
  11.250   1.3506   0.04127   0.03276  -0.0424   0.0603   1.0000
  11.500   1.3462   0.04411   0.03553  -0.0403   0.0574   1.0000
  11.750   1.3499   0.04643   0.03804  -0.0386   0.0547   1.0000
  12.000   1.3546   0.04881   0.04053  -0.0370   0.0525   1.0000
  12.250   1.3620   0.05113   0.04291  -0.0354   0.0506   1.0000
  12.500   1.3751   0.05342   0.04518  -0.0337   0.0488   1.0000
  12.750   1.3950   0.05638   0.04821  -0.0322   0.0469   1.0000
  13.000   1.3957   0.05929   0.05143  -0.0309   0.0459   1.0000
  13.250   1.3942   0.06253   0.05496  -0.0299   0.0449   1.0000
  13.500   1.3908   0.06611   0.05882  -0.0291   0.0442   1.0000
  13.750   1.3850   0.07010   0.06309  -0.0285   0.0438   1.0000
  14.000   1.3752   0.07456   0.06785  -0.0285   0.0437   1.0000
  14.250   1.3618   0.07949   0.07306  -0.0291   0.0437   1.0000
  14.500   1.3451   0.08499   0.07884  -0.0304   0.0438   1.0000
  14.750   1.3255   0.09107   0.08520  -0.0324   0.0440   1.0000
  15.000   1.3038   0.09778   0.09216  -0.0354   0.0443   1.0000
  15.250   1.2800   0.10517   0.09979  -0.0391   0.0446   1.0000
  15.500   1.2548   0.11339   0.10823  -0.0438   0.0450   1.0000
  15.750   1.2285   0.12251   0.11753  -0.0495   0.0456   1.0000
  16.000   1.2012   0.13261   0.12780  -0.0560   0.0461   1.0000
  16.250   1.1750   0.14346   0.13875  -0.0630   0.0468   1.0000
  16.500   1.0823   0.18205   0.17735  -0.0876   0.0570   1.0000
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