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ARA-D 6% AIRFOIL (arad6-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: ARA-D 6% AIRFOIL (arad6-il)
Reynolds number: 1,000,000
Max Cl/Cd: 105.97 at α=2.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-arad6-il-1000000-n5.txt
Download as CSV file: xf-arad6-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: ARA-D 6% AIRFOIL                                
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.3660   0.11505   0.11332  -0.0267   1.0000   0.0053
  -9.750  -0.3638   0.11136   0.10965  -0.0275   1.0000   0.0056
  -9.500  -0.3656   0.10727   0.10557  -0.0282   1.0000   0.0061
  -9.250  -0.3603   0.10417   0.10249  -0.0294   0.9993   0.0061
  -9.000  -0.3480   0.10107   0.09939  -0.0320   0.9975   0.0062
  -8.750  -0.3352   0.09784   0.09616  -0.0349   0.9957   0.0063
  -8.500  -0.3224   0.09454   0.09286  -0.0380   0.9936   0.0064
  -8.250  -0.3107   0.09119   0.08952  -0.0409   0.9896   0.0066
  -8.000  -0.2979   0.08766   0.08599  -0.0443   0.9857   0.0068
  -7.750  -0.2875   0.08427   0.08260  -0.0472   0.9791   0.0070
  -7.500  -0.2717   0.08034   0.07867  -0.0519   0.9740   0.0072
  -7.250  -0.2567   0.07643   0.07474  -0.0564   0.9670   0.0073
  -7.000  -0.2392   0.07225   0.07054  -0.0616   0.9606   0.0074
  -6.750  -0.2203   0.06785   0.06611  -0.0672   0.9535   0.0077
  -6.500  -0.1979   0.06268   0.06089  -0.0741   0.9466   0.0080
  -6.000  -0.0776   0.01519   0.01145  -0.1298   0.9358   0.0088
  -5.750  -0.0476   0.01349   0.00942  -0.1310   0.9314   0.0091
  -5.500  -0.0183   0.01264   0.00841  -0.1316   0.9264   0.0093
  -5.250   0.0109   0.01188   0.00747  -0.1321   0.9210   0.0095
  -5.000   0.0399   0.01122   0.00666  -0.1324   0.9161   0.0097
  -4.750   0.0692   0.01064   0.00595  -0.1328   0.9105   0.0098
  -4.500   0.0982   0.01017   0.00536  -0.1330   0.9046   0.0101
  -4.250   0.1272   0.00975   0.00483  -0.1333   0.8989   0.0105
  -4.000   0.1563   0.00938   0.00437  -0.1335   0.8923   0.0108
  -3.750   0.1852   0.00907   0.00397  -0.1336   0.8861   0.0112
  -3.500   0.2142   0.00879   0.00362  -0.1338   0.8789   0.0115
  -3.250   0.2429   0.00856   0.00331  -0.1339   0.8719   0.0117
  -3.000   0.2718   0.00836   0.00306  -0.1341   0.8640   0.0120
  -2.750   0.3006   0.00818   0.00281  -0.1342   0.8562   0.0121
  -2.500   0.3296   0.00794   0.00250  -0.1343   0.8476   0.0127
  -2.250   0.3585   0.00777   0.00228  -0.1345   0.8392   0.0137
  -2.000   0.3872   0.00766   0.00212  -0.1345   0.8301   0.0148
  -1.750   0.4160   0.00756   0.00198  -0.1346   0.8204   0.0159
  -1.500   0.4448   0.00747   0.00186  -0.1347   0.8109   0.0196
  -1.250   0.4734   0.00736   0.00177  -0.1348   0.7993   0.0351
  -1.000   0.5012   0.00737   0.00171  -0.1347   0.7747   0.0459
  -0.750   0.5287   0.00744   0.00167  -0.1346   0.7440   0.0574
  -0.500   0.5567   0.00747   0.00166  -0.1346   0.7196   0.0724
  -0.250   0.5845   0.00753   0.00166  -0.1345   0.6944   0.0902
   0.000   0.6123   0.00761   0.00169  -0.1345   0.6675   0.1105
   0.250   0.6400   0.00772   0.00172  -0.1345   0.6407   0.1260
   0.500   0.6680   0.00781   0.00175  -0.1345   0.6189   0.1378
   0.750   0.6957   0.00793   0.00180  -0.1345   0.5937   0.1505
   1.000   0.7234   0.00807   0.00186  -0.1345   0.5668   0.1660
   1.250   0.7509   0.00821   0.00195  -0.1345   0.5358   0.1938
   1.500   0.7780   0.00843   0.00207  -0.1344   0.4970   0.2239
   1.750   0.8050   0.00864   0.00221  -0.1344   0.4561   0.2669
   2.000   0.8317   0.00887   0.00241  -0.1344   0.4030   0.3686
   2.250   0.8520   0.00804   0.00264  -0.1332   0.3478   1.0000
   2.500   0.8778   0.00853   0.00285  -0.1330   0.2933   1.0000
   2.750   0.9045   0.00886   0.00303  -0.1328   0.2620   1.0000
   3.000   0.9313   0.00916   0.00320  -0.1327   0.2366   1.0000
   3.250   0.9580   0.00944   0.00336  -0.1326   0.2141   1.0000
   3.500   0.9849   0.00969   0.00353  -0.1325   0.1972   1.0000
   3.750   1.0116   0.00996   0.00371  -0.1323   0.1808   1.0000
   4.000   1.0385   0.01019   0.00388  -0.1322   0.1686   1.0000
   4.250   1.0652   0.01043   0.00407  -0.1320   0.1562   1.0000
   4.500   1.0918   0.01067   0.00426  -0.1319   0.1470   1.0000
   4.750   1.1184   0.01090   0.00446  -0.1317   0.1383   1.0000
   5.000   1.1449   0.01114   0.00466  -0.1315   0.1286   1.0000
   5.250   1.1708   0.01144   0.00489  -0.1312   0.1157   1.0000
   5.500   1.1968   0.01172   0.00514  -0.1310   0.1066   1.0000
   5.750   1.2226   0.01201   0.00539  -0.1307   0.0982   1.0000
   6.000   1.2483   0.01229   0.00565  -0.1304   0.0899   1.0000
   6.250   1.2736   0.01262   0.00593  -0.1300   0.0811   1.0000
   6.500   1.2989   0.01293   0.00624  -0.1297   0.0743   1.0000
   6.750   1.3237   0.01329   0.00655  -0.1292   0.0656   1.0000
   7.000   1.3480   0.01370   0.00691  -0.1287   0.0562   1.0000
   7.250   1.3721   0.01411   0.00729  -0.1282   0.0489   1.0000
   7.500   1.3965   0.01447   0.00764  -0.1276   0.0439   1.0000
   7.750   1.4200   0.01491   0.00806  -0.1270   0.0377   1.0000
   8.000   1.4437   0.01530   0.00845  -0.1264   0.0335   1.0000
   8.250   1.4665   0.01579   0.00891  -0.1256   0.0279   1.0000
   8.500   1.4895   0.01623   0.00936  -0.1249   0.0244   1.0000
   8.750   1.5117   0.01673   0.00986  -0.1241   0.0207   1.0000
   9.000   1.5340   0.01720   0.01035  -0.1232   0.0178   1.0000
   9.250   1.5550   0.01778   0.01092  -0.1222   0.0136   1.0000
   9.500   1.5742   0.01854   0.01165  -0.1208   0.0083   1.0000
   9.750   1.5937   0.01921   0.01234  -0.1195   0.0062   1.0000
  10.000   1.6132   0.01984   0.01302  -0.1182   0.0052   1.0000
  10.250   1.6324   0.02046   0.01370  -0.1169   0.0047   1.0000
  10.500   1.6504   0.02114   0.01444  -0.1153   0.0042   1.0000
  10.750   1.6673   0.02188   0.01525  -0.1136   0.0038   1.0000
  11.000   1.6832   0.02265   0.01609  -0.1117   0.0035   1.0000
  11.250   1.6993   0.02333   0.01685  -0.1099   0.0034   1.0000
  11.500   1.7141   0.02407   0.01767  -0.1078   0.0033   1.0000
  11.750   1.7273   0.02487   0.01855  -0.1056   0.0032   1.0000
  12.000   1.7370   0.02572   0.01950  -0.1026   0.0031   1.0000
  12.250   1.7460   0.02665   0.02053  -0.0997   0.0029   1.0000
  12.500   1.7548   0.02766   0.02163  -0.0969   0.0028   1.0000
  12.750   1.7631   0.02875   0.02282  -0.0942   0.0027   1.0000
  13.000   1.7705   0.02995   0.02411  -0.0915   0.0027   1.0000
  13.250   1.7770   0.03126   0.02552  -0.0888   0.0026   1.0000
  13.500   1.7823   0.03270   0.02707  -0.0862   0.0025   1.0000
  13.750   1.7862   0.03430   0.02878  -0.0836   0.0024   1.0000
  14.000   1.7887   0.03610   0.03070  -0.0810   0.0023   1.0000
  14.250   1.7891   0.03813   0.03286  -0.0785   0.0023   1.0000
  14.500   1.7868   0.04052   0.03538  -0.0760   0.0022   1.0000
  14.750   1.7824   0.04323   0.03826  -0.0737   0.0021   1.0000
  15.000   1.7751   0.04638   0.04157  -0.0716   0.0021   1.0000
  15.250   1.7710   0.04934   0.04466  -0.0701   0.0021   1.0000
  15.500   1.7667   0.05247   0.04793  -0.0690   0.0021   1.0000
  15.750   1.7604   0.05600   0.05160  -0.0682   0.0020   1.0000
  16.000   1.7518   0.06002   0.05576  -0.0678   0.0020   1.0000
  16.250   1.7422   0.06445   0.06033  -0.0679   0.0020   1.0000
  16.500   1.7304   0.06950   0.06553  -0.0685   0.0020   1.0000
  16.750   1.7159   0.07522   0.07142  -0.0697   0.0020   1.0000
  17.000   1.6973   0.08200   0.07836  -0.0718   0.0020   1.0000
  17.250   1.6761   0.08966   0.08620  -0.0747   0.0020   1.0000
  17.500   1.6509   0.09853   0.09524  -0.0785   0.0020   1.0000
  17.750   1.6189   0.10920   0.10610  -0.0836   0.0020   1.0000
  18.000   1.5827   0.12141   0.11850  -0.0898   0.0020   1.0000
  18.250   1.5405   0.13526   0.13256  -0.0971   0.0020   1.0000
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