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DAE-21 AIRFOIL (dae21-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: DAE-21 AIRFOIL (dae21-il)
Reynolds number: 200,000
Max Cl/Cd: 88.71 at α=6.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-dae21-il-200000-n5.txt
Download as CSV file: xf-dae21-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: DAE-21 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
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.0411   0.09218   0.08760  -0.0757   0.7611   0.0285
  -8.250  -0.0419   0.08958   0.08504  -0.0788   0.7579   0.0291
  -8.000  -0.0408   0.08671   0.08221  -0.0814   0.7547   0.0292
  -7.750  -0.0244   0.08394   0.07942  -0.0804   0.7524   0.0296
  -7.500  -0.0147   0.08149   0.07696  -0.0809   0.7499   0.0300
  -7.250  -0.0067   0.07908   0.07452  -0.0818   0.7476   0.0304
  -7.000   0.0004   0.07665   0.07214  -0.0828   0.7446   0.0309
  -6.750   0.0058   0.07428   0.06981  -0.0839   0.7413   0.0313
  -6.500   0.0103   0.07196   0.06751  -0.0852   0.7380   0.0318
  -6.250   0.0184   0.06912   0.06468  -0.0879   0.7351   0.0326
  -6.000   0.0285   0.06526   0.06079  -0.0942   0.7323   0.0337
  -5.750   0.0441   0.06104   0.05650  -0.1006   0.7300   0.0339
  -5.500   0.0581   0.05463   0.05005  -0.1057   0.7267   0.0249
  -5.250   0.0754   0.05270   0.04812  -0.1068   0.7236   0.0243
  -5.000   0.0967   0.04880   0.04414  -0.1112   0.7205   0.0234
  -4.750   0.1228   0.04305   0.03820  -0.1178   0.7178   0.0224
  -4.500   0.1502   0.03857   0.03347  -0.1223   0.7156   0.0233
  -4.250   0.1792   0.03319   0.02767  -0.1265   0.7136   0.0236
  -4.000   0.2080   0.02843   0.02244  -0.1294   0.7105   0.0230
  -3.750   0.2368   0.02472   0.01815  -0.1311   0.7074   0.0230
  -3.500   0.2653   0.02233   0.01528  -0.1319   0.7045   0.0233
  -3.250   0.2939   0.02058   0.01308  -0.1322   0.7018   0.0239
  -3.000   0.3227   0.01925   0.01128  -0.1324   0.6994   0.0251
  -2.750   0.3505   0.01869   0.01066  -0.1325   0.6973   0.0263
  -2.500   0.3784   0.01800   0.00984  -0.1326   0.6941   0.0275
  -2.250   0.4064   0.01728   0.00897  -0.1326   0.6906   0.0284
  -2.000   0.4344   0.01666   0.00823  -0.1326   0.6874   0.0293
  -1.750   0.4623   0.01618   0.00774  -0.1326   0.6847   0.0307
  -1.500   0.4906   0.01582   0.00730  -0.1326   0.6822   0.0333
  -1.250   0.5186   0.01544   0.00690  -0.1326   0.6797   0.0355
  -1.000   0.5462   0.01519   0.00668  -0.1327   0.6757   0.0379
  -0.750   0.5741   0.01494   0.00642  -0.1327   0.6721   0.0414
  -0.500   0.6023   0.01472   0.00617  -0.1327   0.6689   0.0478
  -0.250   0.6308   0.01447   0.00591  -0.1328   0.6663   0.0578
   0.000   0.6590   0.01422   0.00573  -0.1329   0.6635   0.0860
   0.250   0.6860   0.01393   0.00579  -0.1330   0.6591   0.1803
   0.500   0.7127   0.01351   0.00587  -0.1332   0.6553   0.3493
   0.750   0.7382   0.01298   0.00592  -0.1328   0.6520   0.5623
   1.000   0.7676   0.01211   0.00577  -0.1325   0.6493   1.0000
   1.250   0.7950   0.01225   0.00583  -0.1325   0.6449   1.0000
   1.500   0.8225   0.01237   0.00587  -0.1324   0.6404   1.0000
   1.750   0.8504   0.01244   0.00584  -0.1324   0.6366   1.0000
   2.000   0.8789   0.01247   0.00576  -0.1324   0.6335   1.0000
   2.250   0.9056   0.01264   0.00590  -0.1323   0.6285   1.0000
   2.500   0.9328   0.01276   0.00598  -0.1322   0.6237   1.0000
   2.750   0.9606   0.01281   0.00596  -0.1321   0.6196   1.0000
   3.000   0.9881   0.01291   0.00600  -0.1321   0.6153   1.0000
   3.250   1.0143   0.01308   0.00617  -0.1319   0.6095   1.0000
   3.500   1.0416   0.01316   0.00620  -0.1318   0.6046   1.0000
   3.750   1.0688   0.01325   0.00625  -0.1317   0.5997   1.0000
   4.000   1.0945   0.01343   0.00646  -0.1314   0.5932   1.0000
   4.250   1.1216   0.01351   0.00649  -0.1313   0.5878   1.0000
   4.500   1.1474   0.01368   0.00667  -0.1310   0.5814   1.0000
   4.750   1.1733   0.01383   0.00682  -0.1307   0.5747   1.0000
   5.000   1.1995   0.01395   0.00692  -0.1305   0.5684   1.0000
   5.250   1.2243   0.01415   0.00714  -0.1301   0.5604   1.0000
   5.500   1.2501   0.01428   0.00724  -0.1298   0.5536   1.0000
   5.750   1.2742   0.01451   0.00752  -0.1293   0.5450   1.0000
   6.000   1.2990   0.01469   0.00768  -0.1289   0.5373   1.0000
   6.250   1.3224   0.01494   0.00795  -0.1283   0.5281   1.0000
   6.500   1.3459   0.01518   0.00821  -0.1277   0.5191   1.0000
   6.750   1.3688   0.01543   0.00845  -0.1270   0.5093   1.0000
   7.000   1.3902   0.01575   0.00879  -0.1261   0.4984   1.0000
   7.250   1.4112   0.01607   0.00911  -0.1252   0.4874   1.0000
   7.500   1.4312   0.01643   0.00945  -0.1240   0.4758   1.0000
   7.750   1.4495   0.01685   0.00987  -0.1227   0.4632   1.0000
   8.000   1.4663   0.01731   0.01033  -0.1212   0.4501   1.0000
   8.250   1.4810   0.01784   0.01085  -0.1194   0.4365   1.0000
   8.500   1.4919   0.01842   0.01142  -0.1170   0.4228   1.0000
   8.750   1.5000   0.01913   0.01211  -0.1143   0.4088   1.0000
   9.000   1.5070   0.01998   0.01292  -0.1117   0.3944   1.0000
   9.250   1.5136   0.02094   0.01386  -0.1092   0.3798   1.0000
   9.500   1.5194   0.02203   0.01492  -0.1069   0.3646   1.0000
   9.750   1.5248   0.02323   0.01609  -0.1046   0.3495   1.0000
  10.000   1.5296   0.02453   0.01736  -0.1025   0.3342   1.0000
  10.250   1.5341   0.02592   0.01872  -0.1004   0.3194   1.0000
  10.500   1.5380   0.02741   0.02020  -0.0984   0.3044   1.0000
  11.000   1.5440   0.03071   0.02343  -0.0946   0.2745   1.0000
  11.250   1.5465   0.03248   0.02518  -0.0929   0.2598   1.0000
  11.500   1.5491   0.03431   0.02700  -0.0912   0.2455   1.0000
  11.750   1.5513   0.03623   0.02890  -0.0896   0.2316   1.0000
  12.000   1.5530   0.03824   0.03090  -0.0881   0.2179   1.0000
  12.250   1.5546   0.04034   0.03299  -0.0867   0.2047   1.0000
  12.500   1.5563   0.04251   0.03516  -0.0855   0.1922   1.0000
  12.750   1.5577   0.04479   0.03744  -0.0843   0.1801   1.0000
  13.000   1.5585   0.04721   0.03986  -0.0833   0.1684   1.0000
  13.250   1.5587   0.04977   0.04241  -0.0823   0.1569   1.0000
  13.500   1.5605   0.05225   0.04490  -0.0815   0.1459   1.0000
  13.750   1.5616   0.05486   0.04753  -0.0808   0.1356   1.0000
  14.000   1.5621   0.05759   0.05028  -0.0801   0.1263   1.0000
  14.250   1.5612   0.06057   0.05326  -0.0796   0.1175   1.0000
  14.500   1.5628   0.06332   0.05607  -0.0792   0.1090   1.0000
  14.750   1.5630   0.06630   0.05909  -0.0789   0.1018   1.0000
  15.000   1.5621   0.06948   0.06230  -0.0787   0.0948   1.0000
  15.250   1.5627   0.07253   0.06541  -0.0785   0.0884   1.0000
  15.750   1.5616   0.07912   0.07212  -0.0786   0.0774   1.0000
  16.000   1.5586   0.08285   0.07590  -0.0788   0.0728   1.0000
  16.250   1.5590   0.08615   0.07929  -0.0791   0.0683   1.0000
  16.500   1.5564   0.08992   0.08312  -0.0795   0.0643   1.0000
  16.750   1.5550   0.09359   0.08689  -0.0801   0.0608   1.0000
  17.000   1.5533   0.09735   0.09073  -0.0807   0.0574   1.0000
  17.500   1.5485   0.10521   0.09878  -0.0823   0.0517   1.0000
  17.750   1.5455   0.10930   0.10297  -0.0833   0.0490   1.0000
  18.250   1.5401   0.11752   0.11137  -0.0857   0.0447   1.0000
  18.500   1.5375   0.12166   0.11562  -0.0870   0.0427   1.0000
  18.750   1.5331   0.12612   0.12015  -0.0886   0.0410   1.0000
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