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ARA-D 6% AIRFOIL (arad6-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: ARA-D 6% AIRFOIL (arad6-il)
Reynolds number: 100,000
Max Cl/Cd: 68.88 at α=5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-arad6-il-100000.txt
Download as CSV file: xf-arad6-il-100000.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 =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -6.750  -0.3627   0.09585   0.09126  -0.0201   1.0000   0.0664
  -6.500  -0.3623   0.09362   0.08908  -0.0197   1.0000   0.0680
  -6.250  -0.3608   0.09135   0.08686  -0.0201   1.0000   0.0699
  -6.000  -0.3562   0.08912   0.08466  -0.0221   1.0000   0.0723
  -5.750  -0.3276   0.08823   0.08368  -0.0379   1.0000   0.0748
  -5.500  -0.3239   0.08358   0.07910  -0.0365   1.0000   0.0755
  -5.250  -0.3253   0.07994   0.07553  -0.0314   1.0000   0.0767
  -5.000  -0.3203   0.07715   0.07278  -0.0291   1.0000   0.0790
  -4.750  -0.3070   0.07444   0.07007  -0.0306   1.0000   0.0834
  -4.500  -0.2625   0.07059   0.06604  -0.0446   1.0000   0.0897
  -4.250  -0.2597   0.06743   0.06295  -0.0410   1.0000   0.0915
  -4.000  -0.2453   0.06470   0.06021  -0.0412   1.0000   0.0950
  -3.750  -0.1929   0.06096   0.05620  -0.0540   1.0000   0.1040
  -3.500  -0.1845   0.05792   0.05324  -0.0519   1.0000   0.1062
  -3.250  -0.1630   0.05538   0.05067  -0.0534   1.0000   0.1117
  -3.000  -0.1233   0.05198   0.04707  -0.0602   1.0000   0.1202
  -2.750  -0.0998   0.04966   0.04470  -0.0615   1.0000   0.1270
  -2.500  -0.0646   0.04679   0.04167  -0.0661   1.0000   0.1368
  -2.250  -0.0328   0.04453   0.03929  -0.0693   1.0000   0.1511
  -2.000  -0.0010   0.04239   0.03702  -0.0722   1.0000   0.1657
  -1.750   0.0916   0.03367   0.02684  -0.0854   1.0000   0.0902
  -1.500   0.1305   0.03093   0.02372  -0.0882   1.0000   0.0829
  -1.250   0.1795   0.02850   0.02063  -0.0924   0.9983   0.0848
  -1.000   0.2294   0.02673   0.01833  -0.0966   0.9957   0.0927
  -0.750   0.2750   0.02592   0.01731  -0.1002   0.9917   0.1125
  -0.500   0.3198   0.02549   0.01667  -0.1038   0.9868   0.1468
  -0.250   0.3663   0.02502   0.01626  -0.1078   0.9832   0.1807
   0.000   0.4056   0.02462   0.01589  -0.1105   0.9761   0.2121
   0.250   0.4518   0.02424   0.01564  -0.1144   0.9718   0.2581
   0.500   0.4904   0.02392   0.01551  -0.1169   0.9646   0.3202
   0.750   0.5284   0.02228   0.01529  -0.1188   0.9592   1.0000
   1.000   0.5651   0.02258   0.01531  -0.1208   0.9499   1.0000
   1.250   0.6099   0.02275   0.01532  -0.1243   0.9432   1.0000
   1.500   0.6438   0.02295   0.01544  -0.1257   0.9321   1.0000
   1.750   0.6883   0.02264   0.01507  -0.1285   0.9191   1.0000
   2.000   0.7407   0.02169   0.01407  -0.1319   0.9041   1.0000
   2.250   0.7885   0.02087   0.01327  -0.1346   0.8913   1.0000
   2.500   0.8309   0.02028   0.01270  -0.1365   0.8812   1.0000
   2.750   0.8727   0.01958   0.01204  -0.1380   0.8715   1.0000
   3.000   0.9059   0.01912   0.01165  -0.1380   0.8581   1.0000
   3.250   0.9386   0.01860   0.01120  -0.1377   0.8441   1.0000
   3.500   0.9709   0.01802   0.01068  -0.1371   0.8289   1.0000
   3.750   0.9997   0.01757   0.01030  -0.1359   0.8106   1.0000
   4.000   1.0272   0.01716   0.00999  -0.1345   0.7890   1.0000
   4.250   1.0543   0.01679   0.00966  -0.1329   0.7639   1.0000
   4.500   1.0802   0.01650   0.00939  -0.1312   0.7328   1.0000
   4.750   1.1049   0.01634   0.00923  -0.1292   0.6924   1.0000
   5.000   1.1275   0.01637   0.00912  -0.1269   0.6362   1.0000
   5.250   1.1463   0.01680   0.00915  -0.1239   0.5463   1.0000
   5.500   1.1593   0.01802   0.00959  -0.1205   0.4282   1.0000
   5.750   1.1736   0.01951   0.01043  -0.1180   0.3530   1.0000
   6.000   1.1913   0.02083   0.01141  -0.1162   0.3100   1.0000
   6.250   1.2109   0.02207   0.01241  -0.1148   0.2797   1.0000
   6.500   1.2317   0.02326   0.01345  -0.1136   0.2549   1.0000
   6.750   1.2530   0.02448   0.01451  -0.1126   0.2341   1.0000
   7.000   1.2746   0.02565   0.01565  -0.1115   0.2147   1.0000
   7.250   1.2963   0.02683   0.01687  -0.1105   0.1972   1.0000
   7.500   1.3177   0.02803   0.01807  -0.1095   0.1810   1.0000
   7.750   1.3390   0.02929   0.01936  -0.1084   0.1663   1.0000
   8.000   1.3603   0.03063   0.02076  -0.1074   0.1529   1.0000
   8.250   1.3809   0.03199   0.02223  -0.1063   0.1405   1.0000
   8.500   1.4031   0.03362   0.02389  -0.1054   0.1301   1.0000
   8.750   1.4248   0.03521   0.02542  -0.1046   0.1200   1.0000
   9.000   1.4419   0.03662   0.02722  -0.1027   0.1107   1.0000
   9.250   1.4621   0.03871   0.02946  -0.1015   0.1029   1.0000
   9.500   1.4797   0.04016   0.03097  -0.1001   0.0946   1.0000
   9.750   1.4927   0.04229   0.03353  -0.0978   0.0870   1.0000
  10.000   1.5063   0.04402   0.03526  -0.0960   0.0791   1.0000
  10.250   1.5139   0.04533   0.03688  -0.0930   0.0717   1.0000
  10.500   1.5212   0.04791   0.03971  -0.0904   0.0653   1.0000
  10.750   1.5272   0.04967   0.04166  -0.0874   0.0594   1.0000
  11.000   1.5305   0.05345   0.04570  -0.0845   0.0554   1.0000
  11.250   1.5229   0.05655   0.04934  -0.0799   0.0525   1.0000
  11.500   1.5199   0.05873   0.05171  -0.0762   0.0493   1.0000
  11.750   1.5232   0.06175   0.05469  -0.0742   0.0463   1.0000
  12.000   1.5050   0.06569   0.05899  -0.0694   0.0456   1.0000
  12.250   1.4841   0.06941   0.06310  -0.0651   0.0453   1.0000
  12.500   1.4621   0.07368   0.06772  -0.0619   0.0451   1.0000
  12.750   1.4388   0.07846   0.07282  -0.0597   0.0450   1.0000
  13.000   1.4144   0.08380   0.07844  -0.0586   0.0450   1.0000
  13.250   1.3895   0.08970   0.08460  -0.0587   0.0452   1.0000
  13.500   1.3643   0.09626   0.09135  -0.0601   0.0454   1.0000
  13.750   1.3392   0.10348   0.09876  -0.0627   0.0456   1.0000
  14.000   1.3154   0.11135   0.10678  -0.0662   0.0459   1.0000
  14.250   1.2177   0.14179   0.13768  -0.0890   0.0574   1.0000
  14.500   1.1640   0.17119   0.16688  -0.1068   0.0691   1.0000
  14.750   1.1621   0.17820   0.17388  -0.1096   0.0688   1.0000
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