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GOE 380 AIRFOIL (goe380-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 380 AIRFOIL (goe380-il)
Reynolds number: 100,000
Max Cl/Cd: 59.98 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe380-il-100000-n5.txt
Download as CSV file: xf-goe380-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 380 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  -0.2764   0.10731   0.10282  -0.0277   1.0000   0.0264
  -7.750  -0.2823   0.10610   0.10171  -0.0267   1.0000   0.0264
  -7.500  -0.2880   0.10479   0.10050  -0.0257   1.0000   0.0265
  -7.250  -0.2914   0.10331   0.09911  -0.0256   1.0000   0.0265
  -7.000  -0.2938   0.10175   0.09761  -0.0255   1.0000   0.0265
  -6.750  -0.2916   0.09611   0.09206  -0.0213   1.0000   0.0271
  -6.500  -0.2929   0.09325   0.08926  -0.0190   0.9999   0.0276
  -6.250  -0.2708   0.08887   0.08487  -0.0232   0.9940   0.0287
  -6.000  -0.2457   0.08481   0.08079  -0.0289   0.9872   0.0300
  -5.750  -0.2197   0.08090   0.07684  -0.0349   0.9793   0.0316
  -5.500  -0.1908   0.07713   0.07303  -0.0417   0.9707   0.0336
  -5.250  -0.1490   0.07416   0.06994  -0.0526   0.9611   0.0352
  -5.000  -0.1021   0.07083   0.06643  -0.0633   0.9539   0.0356
  -4.750  -0.0894   0.06569   0.06137  -0.0633   0.9454   0.0362
  -4.500  -0.0650   0.06128   0.05695  -0.0657   0.9402   0.0377
  -4.250  -0.0378   0.05792   0.05352  -0.0690   0.9306   0.0397
  -4.000  -0.0017   0.05451   0.04996  -0.0742   0.9230   0.0422
  -3.750   0.0519   0.05271   0.04779  -0.0818   0.9141   0.0452
  -3.500   0.0819   0.04905   0.04397  -0.0845   0.9041   0.0459
  -3.250   0.1010   0.04451   0.03952  -0.0854   0.8968   0.0485
  -3.000   0.1304   0.04171   0.03658  -0.0873   0.8863   0.0508
  -2.750   0.1703   0.03799   0.03246  -0.0897   0.8760   0.0345
  -2.250   0.2389   0.03129   0.02510  -0.0925   0.8550   0.0256
  -2.000   0.2705   0.02869   0.02218  -0.0931   0.8409   0.0249
  -1.750   0.3021   0.02614   0.01923  -0.0932   0.8255   0.0247
  -1.500   0.3338   0.02364   0.01623  -0.0929   0.8098   0.0259
  -1.250   0.3640   0.02149   0.01362  -0.0926   0.7943   0.0275
  -1.000   0.3934   0.01982   0.01153  -0.0922   0.7792   0.0287
  -0.750   0.4227   0.01834   0.00966  -0.0917   0.7639   0.0311
  -0.500   0.4511   0.01735   0.00839  -0.0912   0.7478   0.0380
  -0.250   0.4791   0.01638   0.00716  -0.0905   0.7314   0.0458
   0.000   0.5067   0.01620   0.00684  -0.0900   0.7144   0.0698
   0.250   0.5334   0.01610   0.00654  -0.0896   0.6971   0.1032
   0.500   0.5603   0.01565   0.00592  -0.0891   0.6802   0.1160
   0.750   0.5873   0.01542   0.00547  -0.0887   0.6637   0.1269
   1.000   0.6139   0.01527   0.00515  -0.0882   0.6476   0.1350
   1.250   0.6401   0.01520   0.00493  -0.0878   0.6322   0.1477
   1.750   0.6890   0.01437   0.00485  -0.0866   0.6042   0.5465
   2.250   0.7651   0.01410   0.00480  -0.0906   0.5746   1.0000
   2.500   0.7897   0.01435   0.00488  -0.0898   0.5619   1.0000
   2.750   0.8141   0.01461   0.00499  -0.0891   0.5498   1.0000
   3.000   0.8385   0.01489   0.00515  -0.0884   0.5379   1.0000
   3.250   0.8626   0.01517   0.00533  -0.0876   0.5254   1.0000
   3.500   0.8866   0.01545   0.00555  -0.0869   0.5131   1.0000
   3.750   0.9104   0.01574   0.00579  -0.0862   0.5008   1.0000
   4.000   0.9338   0.01603   0.00606  -0.0853   0.4872   1.0000
   4.250   0.9568   0.01632   0.00631  -0.0844   0.4723   1.0000
   4.500   0.9795   0.01660   0.00656  -0.0835   0.4572   1.0000
   4.750   1.0023   0.01690   0.00689  -0.0826   0.4430   1.0000
   5.000   1.0252   0.01721   0.00721  -0.0818   0.4305   1.0000
   5.250   1.0481   0.01753   0.00755  -0.0809   0.4188   1.0000
   5.500   1.0707   0.01787   0.00790  -0.0800   0.4076   1.0000
   5.750   1.0933   0.01823   0.00836  -0.0792   0.3958   1.0000
   6.000   1.1156   0.01860   0.00881  -0.0783   0.3843   1.0000
   6.250   1.1377   0.01900   0.00927  -0.0773   0.3737   1.0000
   6.500   1.1596   0.01944   0.00976  -0.0764   0.3638   1.0000
   6.750   1.1812   0.01988   0.01038  -0.0754   0.3529   1.0000
   7.000   1.2026   0.02036   0.01098  -0.0744   0.3421   1.0000
   7.250   1.2236   0.02087   0.01161  -0.0733   0.3317   1.0000
   7.500   1.2428   0.02138   0.01225  -0.0719   0.3171   1.0000
   7.750   1.2538   0.02191   0.01270  -0.0694   0.2781   1.0000
   8.000   1.2678   0.02255   0.01341  -0.0673   0.2401   1.0000
   8.250   1.2732   0.02388   0.01429  -0.0643   0.1747   1.0000
   8.500   1.2693   0.02629   0.01596  -0.0605   0.0795   1.0000
   8.750   1.2604   0.02906   0.01826  -0.0559   0.0258   1.0000
   9.000   1.2621   0.03074   0.02009  -0.0523   0.0210   1.0000
   9.250   1.2661   0.03226   0.02184  -0.0493   0.0192   1.0000
   9.500   1.2690   0.03386   0.02369  -0.0464   0.0174   1.0000
   9.750   1.2692   0.03574   0.02579  -0.0436   0.0157   1.0000
  10.000   1.2664   0.03791   0.02819  -0.0410   0.0146   1.0000
  10.250   1.2607   0.04047   0.03098  -0.0388   0.0140   1.0000
  10.500   1.2536   0.04334   0.03407  -0.0370   0.0137   1.0000
  10.750   1.2435   0.04675   0.03770  -0.0357   0.0133   1.0000
  11.000   1.2331   0.05050   0.04165  -0.0351   0.0131   1.0000
  11.250   1.2231   0.05449   0.04582  -0.0350   0.0129   1.0000
  11.500   1.2133   0.05867   0.05016  -0.0351   0.0127   1.0000
  11.750   1.2047   0.06279   0.05441  -0.0352   0.0126   1.0000
  12.000   1.2024   0.06621   0.05793  -0.0352   0.0123   1.0000
  12.250   1.2027   0.06928   0.06112  -0.0350   0.0121   1.0000
  12.500   1.2044   0.07226   0.06425  -0.0347   0.0114   1.0000
  12.750   1.2070   0.07516   0.06727  -0.0344   0.0107   1.0000
  13.000   1.2126   0.07765   0.06987  -0.0336   0.0104   1.0000
  13.250   1.2202   0.08001   0.07247  -0.0325   0.0101   1.0000
  13.500   1.2272   0.08275   0.07538  -0.0315   0.0100   1.0000
  13.750   1.2301   0.08622   0.07905  -0.0313   0.0098   1.0000
  14.000   1.2298   0.09018   0.08322  -0.0317   0.0098   1.0000
  14.250   1.2262   0.09470   0.08797  -0.0327   0.0098   1.0000
  14.500   1.2202   0.09962   0.09312  -0.0343   0.0098   1.0000
  14.750   1.2123   0.10503   0.09876  -0.0363   0.0098   1.0000
  15.000   1.2031   0.11076   0.10471  -0.0389   0.0098   1.0000
  15.250   1.1931   0.11679   0.11095  -0.0419   0.0099   1.0000
  15.500   1.1820   0.12329   0.11766  -0.0454   0.0099   1.0000
  15.750   1.1711   0.13001   0.12457  -0.0493   0.0100   1.0000
  16.000   1.1600   0.13707   0.13181  -0.0536   0.0101   1.0000
  16.250   1.1484   0.14458   0.13949  -0.0583   0.0102   1.0000
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