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GOE 182 (MVA H.27) AIRFOIL (goe182-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 182 (MVA H.27) AIRFOIL (goe182-il)
Reynolds number: 200,000
Max Cl/Cd: 69.42 at α=9.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe182-il-200000-n5.txt
Download as CSV file: xf-goe182-il-200000-n5.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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.2930   0.09108   0.08772  -0.0227   1.0000   0.0293
  -7.750  -0.2913   0.08806   0.08475  -0.0235   1.0000   0.0290
  -7.500  -0.2931   0.08538   0.08214  -0.0237   1.0000   0.0288
  -7.250  -0.2954   0.08283   0.07965  -0.0239   1.0000   0.0293
  -7.000  -0.2861   0.07850   0.07534  -0.0293   0.9955   0.0305
  -6.750  -0.2578   0.07203   0.06884  -0.0401   0.9853   0.0309
  -6.500  -0.2263   0.06464   0.06138  -0.0522   0.9737   0.0312
  -6.250  -0.1998   0.06223   0.05896  -0.0557   0.9623   0.0327
  -6.000  -0.1706   0.05954   0.05621  -0.0601   0.9481   0.0343
  -5.750  -0.1384   0.05404   0.05061  -0.0685   0.9272   0.0348
  -5.500  -0.1037   0.04787   0.04425  -0.0773   0.8999   0.0351
  -5.250  -0.0640   0.03993   0.03596  -0.0877   0.8676   0.0369
  -5.000  -0.0241   0.02791   0.02298  -0.0985   0.8393   0.0375
  -4.750   0.0055   0.02305   0.01713  -0.1010   0.8061   0.0389
  -4.500   0.0311   0.02148   0.01517  -0.1011   0.7751   0.0397
  -4.250   0.0573   0.02020   0.01349  -0.1009   0.7488   0.0402
  -4.000   0.0839   0.01916   0.01207  -0.1008   0.7271   0.0409
  -3.750   0.1109   0.01822   0.01081  -0.1006   0.7084   0.0416
  -3.500   0.1383   0.01739   0.00968  -0.1004   0.6916   0.0424
  -3.250   0.1658   0.01676   0.00880  -0.1002   0.6752   0.0438
  -3.000   0.1933   0.01618   0.00797  -0.1000   0.6582   0.0453
  -2.750   0.2209   0.01559   0.00714  -0.0997   0.6400   0.0462
  -2.500   0.2483   0.01509   0.00643  -0.0994   0.6204   0.0470
  -2.250   0.2754   0.01456   0.00576  -0.0990   0.6003   0.0481
  -2.000   0.3025   0.01422   0.00532  -0.0987   0.5800   0.0495
  -1.750   0.3296   0.01398   0.00496  -0.0984   0.5606   0.0511
  -1.500   0.3568   0.01380   0.00465  -0.0981   0.5420   0.0535
  -1.250   0.3840   0.01369   0.00438  -0.0977   0.5242   0.0566
  -1.000   0.4111   0.01349   0.00411  -0.0975   0.5070   0.0598
  -0.750   0.4383   0.01338   0.00391  -0.0972   0.4901   0.0639
  -0.500   0.4656   0.01330   0.00371  -0.0969   0.4727   0.0690
  -0.250   0.4929   0.01319   0.00353  -0.0967   0.4545   0.0765
   0.000   0.5200   0.01312   0.00340  -0.0965   0.4355   0.0881
   0.250   0.5469   0.01307   0.00339  -0.0962   0.4160   0.1137
   0.500   0.5737   0.01309   0.00342  -0.0960   0.3972   0.1633
   0.750   0.6004   0.01311   0.00348  -0.0958   0.3801   0.2082
   1.000   0.6270   0.01314   0.00357  -0.0955   0.3651   0.2607
   1.250   0.6536   0.01312   0.00367  -0.0953   0.3524   0.3309
   1.500   0.6795   0.01301   0.00383  -0.0950   0.3418   0.4620
   2.000   0.7343   0.01238   0.00398  -0.0944   0.3240   1.0000
   2.500   0.7878   0.01287   0.00424  -0.0938   0.3107   1.0000
   2.750   0.8143   0.01313   0.00440  -0.0935   0.3050   1.0000
   3.000   0.8408   0.01340   0.00459  -0.0932   0.3004   1.0000
   3.250   0.8675   0.01363   0.00478  -0.0929   0.2959   1.0000
   3.500   0.8940   0.01389   0.00498  -0.0926   0.2919   1.0000
   3.750   0.9201   0.01419   0.00521  -0.0922   0.2884   1.0000
   4.000   0.9463   0.01449   0.00546  -0.0919   0.2855   1.0000
   4.250   0.9728   0.01474   0.00571  -0.0916   0.2826   1.0000
   4.500   0.9991   0.01501   0.00599  -0.0912   0.2799   1.0000
   4.750   1.0253   0.01530   0.00627  -0.0909   0.2774   1.0000
   5.000   1.0512   0.01561   0.00656  -0.0906   0.2748   1.0000
   5.250   1.0768   0.01596   0.00688  -0.0902   0.2722   1.0000
   5.500   1.1024   0.01631   0.00721  -0.0898   0.2697   1.0000
   5.750   1.1284   0.01659   0.00754  -0.0895   0.2672   1.0000
   6.000   1.1543   0.01689   0.00790  -0.0891   0.2650   1.0000
   6.250   1.1800   0.01722   0.00828  -0.0888   0.2631   1.0000
   6.500   1.2055   0.01756   0.00867  -0.0884   0.2616   1.0000
   6.750   1.2309   0.01792   0.00909  -0.0880   0.2601   1.0000
   7.000   1.2560   0.01827   0.00947  -0.0876   0.2578   1.0000
   7.250   1.2804   0.01869   0.00986  -0.0871   0.2545   1.0000
   7.500   1.3053   0.01899   0.01027  -0.0867   0.2515   1.0000
   7.750   1.3302   0.01931   0.01072  -0.0863   0.2490   1.0000
   8.000   1.3547   0.01964   0.01116  -0.0858   0.2462   1.0000
   8.250   1.3789   0.01998   0.01158  -0.0853   0.2431   1.0000
   8.500   1.4026   0.02036   0.01201  -0.0847   0.2402   1.0000
   8.750   1.4257   0.02073   0.01247  -0.0841   0.2360   1.0000
   9.000   1.4488   0.02092   0.01284  -0.0834   0.2288   1.0000
   9.250   1.4700   0.02124   0.01317  -0.0826   0.2202   1.0000
   9.500   1.4925   0.02150   0.01358  -0.0819   0.2103   1.0000
   9.750   1.5141   0.02186   0.01406  -0.0811   0.1999   1.0000
  10.000   1.5350   0.02226   0.01453  -0.0802   0.1805   1.0000
  10.250   1.5379   0.02419   0.01592  -0.0776   0.1080   1.0000
  10.500   1.5390   0.02641   0.01797  -0.0748   0.0647   1.0000
  10.750   1.5406   0.02822   0.01974  -0.0719   0.0518   1.0000
  11.000   1.5427   0.02980   0.02141  -0.0691   0.0452   1.0000
  11.250   1.5454   0.03139   0.02315  -0.0667   0.0399   1.0000
  11.500   1.5448   0.03335   0.02522  -0.0645   0.0360   1.0000
  11.750   1.5449   0.03543   0.02743  -0.0628   0.0324   1.0000
  12.000   1.5401   0.03821   0.03033  -0.0616   0.0299   1.0000
  12.250   1.5374   0.04111   0.03338  -0.0610   0.0277   1.0000
  12.500   1.5320   0.04462   0.03704  -0.0611   0.0259   1.0000
  12.750   1.5231   0.04883   0.04138  -0.0617   0.0247   1.0000
  13.000   1.5104   0.05379   0.04649  -0.0628   0.0238   1.0000
  13.250   1.4979   0.05898   0.05184  -0.0642   0.0232   1.0000
  13.500   1.4833   0.06463   0.05767  -0.0658   0.0226   1.0000
  13.750   1.4667   0.07071   0.06392  -0.0676   0.0222   1.0000
  14.000   1.4488   0.07701   0.07038  -0.0695   0.0219   1.0000
  14.250   1.4310   0.08340   0.07691  -0.0714   0.0216   1.0000
  14.500   1.4142   0.08972   0.08337  -0.0733   0.0213   1.0000
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