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GOE 389 AIRFOIL (goe389-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 389 AIRFOIL (goe389-il)
Reynolds number: 200,000
Max Cl/Cd: 73.41 at α=6.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe389-il-200000-n5.txt
Download as CSV file: xf-goe389-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 389 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
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.3718   0.08916   0.08568  -0.0369   1.0000   0.0232
  -8.750  -0.3782   0.08472   0.08130  -0.0385   1.0000   0.0235
  -8.500  -0.3882   0.08079   0.07745  -0.0391   1.0000   0.0237
  -8.250  -0.4043   0.07748   0.07426  -0.0386   1.0000   0.0238
  -8.000  -0.4170   0.07285   0.06970  -0.0407   0.9991   0.0239
  -7.750  -0.4003   0.06294   0.05973  -0.0549   0.9895   0.0248
  -7.500  -0.3740   0.06117   0.05791  -0.0587   0.9844   0.0259
  -7.250  -0.3489   0.05590   0.05252  -0.0663   0.9763   0.0273
  -7.000  -0.3270   0.04520   0.04148  -0.0774   0.9659   0.0284
  -6.750  -0.3068   0.03526   0.03081  -0.0843   0.9556   0.0305
  -6.500  -0.2799   0.02976   0.02451  -0.0876   0.9478   0.0324
  -6.250  -0.2523   0.02610   0.02026  -0.0895   0.9388   0.0335
  -6.000  -0.2226   0.02428   0.01824  -0.0910   0.9299   0.0350
  -5.750  -0.1903   0.02284   0.01653  -0.0925   0.9221   0.0363
  -5.500  -0.1609   0.02129   0.01466  -0.0931   0.9123   0.0371
  -5.250  -0.1303   0.01992   0.01299  -0.0939   0.9033   0.0379
  -5.000  -0.1010   0.01892   0.01174  -0.0942   0.8928   0.0393
  -4.750  -0.0730   0.01801   0.01061  -0.0942   0.8811   0.0405
  -4.500  -0.0454   0.01709   0.00946  -0.0941   0.8690   0.0412
  -4.250  -0.0179   0.01630   0.00849  -0.0938   0.8575   0.0418
  -4.000   0.0096   0.01561   0.00766  -0.0936   0.8468   0.0424
  -3.750   0.0364   0.01503   0.00696  -0.0933   0.8352   0.0430
  -3.500   0.0634   0.01453   0.00635  -0.0930   0.8237   0.0435
  -3.250   0.0900   0.01390   0.00568  -0.0927   0.8121   0.0446
  -3.000   0.1169   0.01347   0.00520  -0.0924   0.8005   0.0462
  -2.500   0.1713   0.01291   0.00450  -0.0919   0.7776   0.0505
  -2.250   0.1985   0.01266   0.00415  -0.0917   0.7661   0.0524
  -2.000   0.2259   0.01246   0.00383  -0.0914   0.7550   0.0547
  -1.500   0.2804   0.01206   0.00334  -0.0909   0.7328   0.0706
  -1.250   0.3075   0.01186   0.00313  -0.0907   0.7214   0.0916
  -1.000   0.3341   0.01155   0.00303  -0.0905   0.7098   0.1591
  -0.750   0.3605   0.01129   0.00299  -0.0903   0.6979   0.2450
  -0.500   0.3868   0.01105   0.00297  -0.0901   0.6848   0.3278
  -0.250   0.4111   0.01053   0.00300  -0.0896   0.6706   0.4929
   0.000   0.4379   0.00942   0.00307  -0.0883   0.6549   0.9398
   0.250   0.4733   0.00946   0.00297  -0.0899   0.6352   1.0000
   0.500   0.4992   0.00957   0.00292  -0.0894   0.6122   1.0000
   0.750   0.5246   0.00971   0.00288  -0.0888   0.5864   1.0000
   1.000   0.5497   0.00990   0.00286  -0.0881   0.5618   1.0000
   1.250   0.5747   0.01011   0.00288  -0.0875   0.5398   1.0000
   1.750   0.6251   0.01060   0.00302  -0.0864   0.5045   1.0000
   2.250   0.6764   0.01106   0.00326  -0.0856   0.4777   1.0000
   2.500   0.7023   0.01129   0.00340  -0.0852   0.4662   1.0000
   2.750   0.7281   0.01152   0.00355  -0.0848   0.4560   1.0000
   3.000   0.7540   0.01175   0.00371  -0.0845   0.4464   1.0000
   3.250   0.7802   0.01196   0.00388  -0.0842   0.4381   1.0000
   3.500   0.8062   0.01219   0.00408  -0.0839   0.4310   1.0000
   3.750   0.8325   0.01240   0.00428  -0.0837   0.4244   1.0000
   4.000   0.8586   0.01262   0.00449  -0.0834   0.4175   1.0000
   4.250   0.8846   0.01286   0.00472  -0.0831   0.4113   1.0000
   4.500   0.9108   0.01307   0.00496  -0.0828   0.4049   1.0000
   4.750   0.9363   0.01333   0.00520  -0.0824   0.3975   1.0000
   5.000   0.9619   0.01354   0.00544  -0.0821   0.3878   1.0000
   5.250   0.9873   0.01378   0.00571  -0.0817   0.3790   1.0000
   5.500   1.0126   0.01402   0.00597  -0.0813   0.3707   1.0000
   5.750   1.0379   0.01425   0.00625  -0.0809   0.3612   1.0000
   6.000   1.0623   0.01451   0.00653  -0.0804   0.3476   1.0000
   6.250   1.0857   0.01479   0.00678  -0.0797   0.3278   1.0000
   6.500   1.1085   0.01513   0.00707  -0.0790   0.3039   1.0000
   6.750   1.1307   0.01554   0.00741  -0.0782   0.2791   1.0000
   7.000   1.1510   0.01612   0.00785  -0.0771   0.2427   1.0000
   7.250   1.1660   0.01717   0.00854  -0.0755   0.1796   1.0000
   7.500   1.1782   0.01854   0.00952  -0.0735   0.1254   1.0000
   7.750   1.1960   0.01938   0.01029  -0.0722   0.1070   1.0000
   8.000   1.2110   0.02041   0.01115  -0.0705   0.0660   1.0000
   8.250   1.2202   0.02185   0.01233  -0.0681   0.0257   1.0000
   8.500   1.2321   0.02298   0.01342  -0.0660   0.0196   1.0000
   8.750   1.2471   0.02381   0.01436  -0.0642   0.0180   1.0000
   9.000   1.2591   0.02470   0.01537  -0.0620   0.0169   1.0000
   9.250   1.2690   0.02575   0.01654  -0.0596   0.0158   1.0000
   9.500   1.2763   0.02700   0.01793  -0.0570   0.0147   1.0000
   9.750   1.2819   0.02843   0.01950  -0.0545   0.0139   1.0000
  10.000   1.2901   0.02971   0.02092  -0.0525   0.0135   1.0000
  10.250   1.2964   0.03119   0.02255  -0.0506   0.0132   1.0000
  10.500   1.3011   0.03286   0.02440  -0.0487   0.0128   1.0000
  10.750   1.3042   0.03477   0.02645  -0.0470   0.0125   1.0000
  11.000   1.3058   0.03692   0.02874  -0.0456   0.0123   1.0000
  11.250   1.3061   0.03931   0.03127  -0.0443   0.0120   1.0000
  11.500   1.3054   0.04195   0.03404  -0.0434   0.0118   1.0000
  11.750   1.3039   0.04479   0.03700  -0.0427   0.0115   1.0000
  12.000   1.3015   0.04783   0.04016  -0.0422   0.0112   1.0000
  12.250   1.2981   0.05106   0.04350  -0.0418   0.0109   1.0000
  12.500   1.2940   0.05446   0.04699  -0.0416   0.0106   1.0000
  12.750   1.2887   0.05806   0.05067  -0.0415   0.0104   1.0000
  13.000   1.2834   0.06165   0.05434  -0.0413   0.0101   1.0000
  13.250   1.2782   0.06514   0.05786  -0.0408   0.0099   1.0000
  13.500   1.2790   0.06815   0.06096  -0.0407   0.0098   1.0000
  13.750   1.2801   0.07118   0.06414  -0.0407   0.0097   1.0000
  14.000   1.2812   0.07425   0.06733  -0.0408   0.0095   1.0000
  14.250   1.2823   0.07736   0.07057  -0.0409   0.0094   1.0000
  14.500   1.2831   0.08055   0.07388  -0.0410   0.0093   1.0000
  14.750   1.2835   0.08383   0.07729  -0.0412   0.0092   1.0000
  15.000   1.2835   0.08724   0.08084  -0.0416   0.0091   1.0000
  15.250   1.2830   0.09079   0.08452  -0.0421   0.0090   1.0000
  15.500   1.2817   0.09451   0.08839  -0.0428   0.0089   1.0000
  15.750   1.2793   0.09847   0.09251  -0.0437   0.0088   1.0000
  16.000   1.2761   0.10266   0.09685  -0.0448   0.0087   1.0000
  16.250   1.2719   0.10713   0.10149  -0.0463   0.0087   1.0000
  16.500   1.2665   0.11192   0.10644  -0.0481   0.0086   1.0000
  16.750   1.2602   0.11697   0.11167  -0.0502   0.0085   1.0000
  17.000   1.2531   0.12230   0.11717  -0.0527   0.0085   1.0000
  17.250   1.2453   0.12790   0.12294  -0.0555   0.0084   1.0000
  17.500   1.2370   0.13379   0.12900  -0.0587   0.0083   1.0000
  17.750   1.2279   0.14006   0.13544  -0.0622   0.0083   1.0000
  18.000   1.2186   0.14660   0.14215  -0.0662   0.0082   1.0000
  18.250   1.2084   0.15359   0.14931  -0.0705   0.0082   1.0000
  18.500   1.1974   0.16106   0.15695  -0.0753   0.0082   1.0000
  18.750   1.1855   0.16920   0.16526  -0.0807   0.0083   1.0000
  19.000   1.1725   0.17813   0.17436  -0.0866   0.0083   1.0000
  19.250   1.1573   0.18846   0.18485  -0.0935   0.0084   1.0000
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