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ARA-D 6% AIRFOIL (arad6-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: ARA-D 6% AIRFOIL (arad6-il)
Reynolds number: 100,000
Max Cl/Cd: 66.55 at α=4.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-arad6-il-100000-n5.txt
Download as CSV file: xf-arad6-il-100000-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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.3468   0.10250   0.09759  -0.0249   1.0000   0.0435
  -7.500  -0.3525   0.10076   0.09592  -0.0231   1.0000   0.0441
  -7.250  -0.3579   0.09898   0.09422  -0.0215   1.0000   0.0448
  -7.000  -0.3604   0.09690   0.09221  -0.0207   1.0000   0.0456
  -6.750  -0.3618   0.09474   0.09011  -0.0205   1.0000   0.0465
  -6.500  -0.3616   0.09250   0.08792  -0.0209   1.0000   0.0475
  -6.250  -0.3586   0.09020   0.08567  -0.0227   1.0000   0.0489
  -6.000  -0.3461   0.08798   0.08345  -0.0298   1.0000   0.0503
  -5.750  -0.2995   0.08315   0.07847  -0.0449   0.9957   0.0509
  -5.500  -0.2972   0.07808   0.07351  -0.0402   0.9933   0.0524
  -5.250  -0.2757   0.07438   0.06979  -0.0422   0.9895   0.0542
  -5.000  -0.2430   0.07012   0.06547  -0.0487   0.9859   0.0556
  -4.500  -0.1510   0.05737   0.05231  -0.0699   0.9780   0.0375
  -4.250  -0.1116   0.05276   0.04757  -0.0766   0.9750   0.0354
  -4.000  -0.0613   0.04708   0.04164  -0.0859   0.9729   0.0334
  -3.750  -0.0155   0.04194   0.03621  -0.0933   0.9688   0.0330
  -3.500   0.0313   0.03747   0.03139  -0.0999   0.9657   0.0349
  -3.250   0.0818   0.03208   0.02545  -0.1067   0.9637   0.0350
  -3.000   0.1305   0.02737   0.01995  -0.1122   0.9623   0.0351
  -2.750   0.1746   0.02430   0.01614  -0.1160   0.9608   0.0362
  -2.500   0.2161   0.02231   0.01358  -0.1188   0.9592   0.0381
  -2.250   0.2477   0.02135   0.01246  -0.1198   0.9534   0.0422
  -2.000   0.2842   0.02053   0.01143  -0.1216   0.9496   0.0488
  -1.750   0.3229   0.01962   0.01043  -0.1238   0.9469   0.0575
  -1.500   0.3581   0.01916   0.00991  -0.1254   0.9426   0.0777
  -1.250   0.3905   0.01894   0.00974  -0.1264   0.9365   0.1019
  -1.000   0.4282   0.01856   0.00936  -0.1285   0.9329   0.1248
  -0.750   0.4620   0.01824   0.00904  -0.1297   0.9277   0.1454
  -0.500   0.4942   0.01800   0.00882  -0.1305   0.9213   0.1703
  -0.250   0.5312   0.01768   0.00854  -0.1323   0.9174   0.2004
   0.000   0.5603   0.01751   0.00844  -0.1325   0.9093   0.2342
   0.250   0.5958   0.01713   0.00825  -0.1340   0.9043   0.2922
   0.500   0.6174   0.01560   0.00817  -0.1325   0.8959   1.0000
   0.750   0.6512   0.01555   0.00795  -0.1334   0.8897   1.0000
   1.000   0.6800   0.01562   0.00792  -0.1334   0.8806   1.0000
   1.250   0.7140   0.01552   0.00773  -0.1342   0.8742   1.0000
   1.500   0.7432   0.01540   0.00755  -0.1339   0.8612   1.0000
   1.750   0.7741   0.01509   0.00715  -0.1336   0.8448   1.0000
   2.000   0.8005   0.01491   0.00692  -0.1324   0.8226   1.0000
   2.250   0.8297   0.01476   0.00671  -0.1319   0.8037   1.0000
   2.500   0.8582   0.01472   0.00663  -0.1315   0.7871   1.0000
   2.750   0.8853   0.01477   0.00669  -0.1309   0.7685   1.0000
   3.000   0.9127   0.01481   0.00670  -0.1304   0.7486   1.0000
   3.250   0.9399   0.01488   0.00673  -0.1297   0.7264   1.0000
   3.500   0.9667   0.01497   0.00677  -0.1290   0.7009   1.0000
   3.750   0.9927   0.01513   0.00689  -0.1281   0.6704   1.0000
   4.000   1.0179   0.01535   0.00702  -0.1271   0.6340   1.0000
   4.250   1.0422   0.01566   0.00718  -0.1260   0.5891   1.0000
   4.500   1.0650   0.01611   0.00740  -0.1246   0.5327   1.0000
   4.750   1.0855   0.01679   0.00776  -0.1229   0.4615   1.0000
   5.000   1.1040   0.01771   0.00825  -0.1211   0.3850   1.0000
   5.250   1.1224   0.01871   0.00887  -0.1195   0.3242   1.0000
   5.500   1.1420   0.01963   0.00955  -0.1182   0.2831   1.0000
   5.750   1.1624   0.02047   0.01026  -0.1170   0.2544   1.0000
   6.000   1.1830   0.02128   0.01101  -0.1159   0.2316   1.0000
   6.250   1.2038   0.02205   0.01175  -0.1148   0.2126   1.0000
   6.500   1.2244   0.02282   0.01251  -0.1136   0.1960   1.0000
   6.750   1.2449   0.02360   0.01329  -0.1124   0.1811   1.0000
   7.000   1.2651   0.02438   0.01413  -0.1113   0.1673   1.0000
   7.250   1.2852   0.02518   0.01497  -0.1100   0.1547   1.0000
   7.500   1.3048   0.02601   0.01586  -0.1088   0.1431   1.0000
   7.750   1.3237   0.02688   0.01676  -0.1074   0.1319   1.0000
   8.000   1.3417   0.02780   0.01770  -0.1060   0.1216   1.0000
   8.250   1.3605   0.02868   0.01875  -0.1046   0.1116   1.0000
   8.500   1.3781   0.02965   0.01982  -0.1030   0.1025   1.0000
   8.750   1.3936   0.03075   0.02092  -0.1013   0.0951   1.0000
   9.000   1.4107   0.03182   0.02220  -0.0996   0.0878   1.0000
   9.250   1.4243   0.03307   0.02347  -0.0976   0.0819   1.0000
   9.500   1.4396   0.03421   0.02483  -0.0958   0.0752   1.0000
   9.750   1.4505   0.03561   0.02629  -0.0935   0.0706   1.0000
  10.000   1.4644   0.03698   0.02793  -0.0914   0.0654   1.0000
  10.250   1.4732   0.03828   0.02935  -0.0888   0.0607   1.0000
  10.500   1.4807   0.03982   0.03105  -0.0861   0.0561   1.0000
  10.750   1.4874   0.04109   0.03250  -0.0835   0.0506   1.0000
  11.000   1.4920   0.04266   0.03421  -0.0809   0.0456   1.0000
  11.250   1.4975   0.04425   0.03601  -0.0785   0.0408   1.0000
  11.500   1.4970   0.04640   0.03820  -0.0758   0.0377   1.0000
  11.750   1.5005   0.04865   0.04085  -0.0734   0.0342   1.0000
  12.000   1.5002   0.05101   0.04341  -0.0711   0.0312   1.0000
  12.250   1.4955   0.05378   0.04628  -0.0690   0.0290   1.0000
  12.500   1.4915   0.05693   0.04970  -0.0670   0.0268   1.0000
  12.750   1.4864   0.06024   0.05330  -0.0654   0.0249   1.0000
  13.000   1.4791   0.06386   0.05713  -0.0642   0.0235   1.0000
  13.250   1.4700   0.06784   0.06131  -0.0634   0.0226   1.0000
  13.500   1.4590   0.07226   0.06592  -0.0632   0.0219   1.0000
  13.750   1.4458   0.07722   0.07106  -0.0635   0.0214   1.0000
  14.000   1.4312   0.08270   0.07672  -0.0644   0.0210   1.0000
  14.250   1.4156   0.08879   0.08304  -0.0659   0.0207   1.0000
  14.500   1.3988   0.09550   0.09002  -0.0684   0.0205   1.0000
  14.750   1.3807   0.10299   0.09776  -0.0717   0.0204   1.0000
  15.000   1.3619   0.11120   0.10620  -0.0761   0.0204   1.0000
  15.250   1.3423   0.12015   0.11535  -0.0812   0.0204   1.0000
  15.500   1.3223   0.12983   0.12521  -0.0872   0.0205   1.0000
  15.750   1.3022   0.14015   0.13569  -0.0936   0.0207   1.0000
  16.000   1.2824   0.15093   0.14659  -0.1004   0.0209   1.0000
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