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GOE 182 (MVA H.27) AIRFOIL (goe182-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 182 (MVA H.27) AIRFOIL (goe182-il)
Reynolds number: 200,000
Max Cl/Cd: 68.57 at α=10.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe182-il-200000.txt
Download as CSV file: xf-goe182-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 182 (MVA H.27) AIRFOIL                      
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.3028   0.09838   0.09498  -0.0196   1.0000   0.0489
  -8.000  -0.3117   0.09707   0.09377  -0.0248   1.0000   0.0497
  -7.750  -0.3107   0.09445   0.09121  -0.0303   1.0000   0.0499
  -7.500  -0.3057   0.08960   0.08640  -0.0274   1.0000   0.0505
  -7.250  -0.2956   0.08662   0.08344  -0.0241   1.0000   0.0514
  -7.000  -0.2886   0.08432   0.08118  -0.0226   1.0000   0.0526
  -6.750  -0.2853   0.08217   0.07910  -0.0222   1.0000   0.0540
  -6.500  -0.2844   0.08002   0.07700  -0.0224   1.0000   0.0557
  -6.250  -0.2853   0.07787   0.07491  -0.0234   1.0000   0.0576
  -6.000  -0.2510   0.07177   0.06872  -0.0455   0.9956   0.0602
  -5.750  -0.2327   0.06741   0.06441  -0.0435   0.9908   0.0614
  -5.500  -0.1982   0.06403   0.06102  -0.0464   0.9844   0.0633
  -5.250  -0.1508   0.05953   0.05643  -0.0563   0.9750   0.0690
  -5.000  -0.0912   0.05156   0.04824  -0.0736   0.9651   0.0737
  -4.750  -0.0571   0.04887   0.04553  -0.0762   0.9549   0.0760
  -4.500  -0.0025   0.04229   0.03853  -0.0895   0.9371   0.0862
  -4.250   0.0199   0.04048   0.03679  -0.0888   0.9158   0.0881
  -4.000   0.0481   0.03838   0.03460  -0.0900   0.8935   0.0921
  -3.750   0.0832   0.03449   0.03036  -0.0944   0.8680   0.1016
  -3.500   0.1105   0.01617   0.01179  -0.0901   0.7940   0.1143
  -3.250   0.1300   0.01509   0.01070  -0.0889   0.7737   0.1173
  -3.000   0.1837   0.02089   0.01453  -0.1001   0.8004   0.0727
  -2.750   0.2106   0.01936   0.01267  -0.0996   0.7777   0.0709
  -2.500   0.2379   0.01802   0.01093  -0.0992   0.7566   0.0708
  -2.250   0.2653   0.01738   0.00987  -0.0986   0.7368   0.0722
  -2.000   0.2924   0.01608   0.00826  -0.0982   0.7182   0.0729
  -1.750   0.3195   0.01516   0.00716  -0.0978   0.6996   0.0743
  -1.500   0.3466   0.01456   0.00644  -0.0973   0.6809   0.0765
  -1.250   0.3738   0.01411   0.00587  -0.0968   0.6619   0.0798
  -1.000   0.4010   0.01381   0.00542  -0.0962   0.6426   0.0843
  -0.750   0.4278   0.01321   0.00477  -0.0957   0.6230   0.0897
  -0.500   0.4548   0.01291   0.00440  -0.0952   0.6014   0.0974
  -0.250   0.4816   0.01266   0.00411  -0.0947   0.5795   0.1112
   0.000   0.5084   0.01253   0.00398  -0.0943   0.5570   0.1374
   0.250   0.5349   0.01227   0.00387  -0.0939   0.5336   0.2076
   0.500   0.5607   0.01211   0.00390  -0.0935   0.5102   0.3086
   0.750   0.5854   0.01176   0.00401  -0.0929   0.4860   0.5006
   1.000   0.6144   0.01095   0.00393  -0.0927   0.4613   1.0000
   1.250   0.6409   0.01123   0.00396  -0.0922   0.4383   1.0000
   1.500   0.6672   0.01155   0.00402  -0.0918   0.4185   1.0000
   1.750   0.6937   0.01186   0.00412  -0.0914   0.4014   1.0000
   2.000   0.7200   0.01220   0.00426  -0.0910   0.3872   1.0000
   2.250   0.7467   0.01250   0.00442  -0.0906   0.3750   1.0000
   2.500   0.7733   0.01284   0.00462  -0.0903   0.3653   1.0000
   2.750   0.7997   0.01321   0.00484  -0.0899   0.3573   1.0000
   3.000   0.8266   0.01354   0.00509  -0.0896   0.3502   1.0000
   3.250   0.8532   0.01388   0.00534  -0.0893   0.3442   1.0000
   3.500   0.8798   0.01432   0.00565  -0.0890   0.3393   1.0000
   3.750   0.9067   0.01462   0.00596  -0.0888   0.3346   1.0000
   4.000   0.9335   0.01497   0.00626  -0.0885   0.3305   1.0000
   4.250   0.9603   0.01537   0.00659  -0.0883   0.3271   1.0000
   4.500   0.9871   0.01587   0.00702  -0.0880   0.3241   1.0000
   4.750   1.0138   0.01620   0.00741  -0.0878   0.3212   1.0000
   5.000   1.0405   0.01657   0.00780  -0.0876   0.3182   1.0000
   5.250   1.0672   0.01696   0.00821  -0.0873   0.3155   1.0000
   5.500   1.0939   0.01739   0.00864  -0.0871   0.3133   1.0000
   5.750   1.1207   0.01787   0.00909  -0.0869   0.3111   1.0000
   6.000   1.1474   0.01849   0.00968  -0.0868   0.3089   1.0000
   6.250   1.1735   0.01887   0.01019  -0.0865   0.3070   1.0000
   6.500   1.1996   0.01930   0.01073  -0.0862   0.3050   1.0000
   6.750   1.2256   0.01977   0.01129  -0.0860   0.3030   1.0000
   7.000   1.2515   0.02018   0.01178  -0.0857   0.3003   1.0000
   7.250   1.2774   0.02057   0.01218  -0.0854   0.2971   1.0000
   7.500   1.3035   0.02120   0.01275  -0.0852   0.2935   1.0000
   7.750   1.3274   0.02147   0.01324  -0.0846   0.2902   1.0000
   8.000   1.3520   0.02184   0.01376  -0.0842   0.2869   1.0000
   8.250   1.3768   0.02209   0.01406  -0.0837   0.2826   1.0000
   8.500   1.4013   0.02244   0.01437  -0.0833   0.2771   1.0000
   8.750   1.4231   0.02244   0.01460  -0.0823   0.2703   1.0000
   9.000   1.4470   0.02258   0.01467  -0.0818   0.2640   1.0000
   9.250   1.4681   0.02271   0.01504  -0.0808   0.2574   1.0000
   9.500   1.4899   0.02269   0.01504  -0.0799   0.2493   1.0000
   9.750   1.5099   0.02275   0.01532  -0.0787   0.2405   1.0000
  10.000   1.5290   0.02269   0.01540  -0.0774   0.2283   1.0000
  10.250   1.5462   0.02255   0.01536  -0.0758   0.2028   1.0000
  10.500   1.5389   0.02522   0.01732  -0.0722   0.0882   1.0000
  10.750   1.5308   0.02810   0.01998  -0.0684   0.0599   1.0000
  11.000   1.5257   0.03017   0.02220  -0.0647   0.0533   1.0000
  11.250   1.5155   0.03274   0.02489  -0.0614   0.0496   1.0000
  11.500   1.5051   0.03567   0.02797  -0.0591   0.0471   1.0000
  11.750   1.4993   0.03864   0.03112  -0.0580   0.0448   1.0000
  12.000   1.4904   0.04238   0.03501  -0.0578   0.0430   1.0000
  12.250   1.4791   0.04679   0.03956  -0.0583   0.0418   1.0000
  12.500   1.4655   0.05176   0.04466  -0.0593   0.0409   1.0000
  12.750   1.4498   0.05711   0.05012  -0.0604   0.0401   1.0000
  13.000   1.4334   0.06247   0.05555  -0.0612   0.0393   1.0000
  13.250   1.4259   0.06675   0.05994  -0.0618   0.0384   1.0000
  13.500   1.4200   0.07085   0.06416  -0.0624   0.0375   1.0000
  13.750   1.4144   0.07484   0.06825  -0.0629   0.0365   1.0000
  14.000   1.4097   0.07868   0.07217  -0.0633   0.0353   1.0000
  14.250   1.4060   0.08237   0.07591  -0.0637   0.0342   1.0000
  14.500   1.4037   0.08577   0.07933  -0.0638   0.0331   1.0000
  14.750   1.4111   0.08642   0.07984  -0.0608   0.0316   1.0000
  15.000   1.4128   0.08951   0.08307  -0.0610   0.0310   1.0000
  15.250   1.4159   0.09226   0.08594  -0.0608   0.0303   1.0000
  15.500   1.4194   0.09493   0.08871  -0.0605   0.0296   1.0000
  15.750   1.4224   0.09773   0.09162  -0.0603   0.0288   1.0000
  16.000   1.4248   0.10067   0.09466  -0.0605   0.0281   1.0000
  16.250   1.4261   0.10382   0.09789  -0.0609   0.0273   1.0000
  16.500   1.4291   0.10657   0.10068  -0.0610   0.0266   1.0000
  17.000   1.4400   0.11102   0.10527  -0.0587   0.0253   1.0000
  17.250   1.4345   0.11571   0.11016  -0.0605   0.0251   1.0000
  17.500   1.4280   0.12066   0.11531  -0.0626   0.0250   1.0000
  17.750   1.4203   0.12594   0.12079  -0.0650   0.0249   1.0000
  18.000   1.4115   0.13158   0.12664  -0.0679   0.0248   1.0000
  18.250   1.4012   0.13767   0.13293  -0.0712   0.0247   1.0000
  18.500   1.3898   0.14416   0.13962  -0.0750   0.0248   1.0000
  18.750   1.3773   0.15111   0.14676  -0.0793   0.0248   1.0000
  19.000   1.3637   0.15851   0.15434  -0.0841   0.0249   1.0000
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