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ARA-D 13% AIRFOIL (arad13-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: ARA-D 13% AIRFOIL (arad13-il)
Reynolds number: 100,000
Max Cl/Cd: 44.54 at α=6.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-arad13-il-100000-n5.txt
Download as CSV file: xf-arad13-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: ARA-D 13% 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
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.4538   0.09191   0.08675  -0.0189   1.0000   0.0411
  -9.000  -0.4643   0.08564   0.08053  -0.0227   1.0000   0.0410
  -8.750  -0.4839   0.07827   0.07323  -0.0280   1.0000   0.0409
  -8.500  -0.5108   0.06609   0.06094  -0.0379   1.0000   0.0407
  -8.250  -0.5538   0.04634   0.04027  -0.0475   1.0000   0.0416
  -8.000  -0.5535   0.03785   0.03075  -0.0493   1.0000   0.0439
  -7.750  -0.5311   0.03702   0.02993  -0.0490   1.0000   0.0452
  -7.500  -0.5122   0.03434   0.02688  -0.0490   1.0000   0.0472
  -7.250  -0.4929   0.03146   0.02352  -0.0487   1.0000   0.0493
  -7.000  -0.4712   0.03071   0.02278  -0.0481   1.0000   0.0511
  -6.750  -0.4518   0.02893   0.02063  -0.0472   1.0000   0.0540
  -6.500  -0.4333   0.02813   0.01982  -0.0460   1.0000   0.0559
  -6.250  -0.4000   0.02698   0.01848  -0.0477   0.9934   0.0594
  -6.000  -0.3616   0.02588   0.01724  -0.0502   0.9836   0.0630
  -5.750  -0.3238   0.02467   0.01571  -0.0523   0.9724   0.0678
  -5.500  -0.2867   0.02401   0.01511  -0.0544   0.9601   0.0715
  -5.250  -0.2500   0.02308   0.01399  -0.0561   0.9473   0.0766
  -5.000  -0.2144   0.02248   0.01336  -0.0576   0.9337   0.0814
  -4.750  -0.1803   0.02181   0.01260  -0.0587   0.9192   0.0867
  -4.500  -0.1488   0.02129   0.01198  -0.0591   0.9028   0.0925
  -4.250  -0.1190   0.02081   0.01148  -0.0592   0.8863   0.0980
  -4.000  -0.0900   0.02037   0.01091  -0.0589   0.8699   0.1049
  -3.750  -0.0621   0.02000   0.01057  -0.0586   0.8538   0.1111
  -3.500  -0.0343   0.01962   0.01009  -0.0581   0.8382   0.1188
  -3.250  -0.0070   0.01932   0.00977  -0.0575   0.8231   0.1267
  -3.000   0.0203   0.01900   0.00942  -0.0570   0.8074   0.1354
  -2.750   0.0480   0.01875   0.00910  -0.0566   0.7916   0.1457
  -2.500   0.0753   0.01847   0.00884  -0.0561   0.7761   0.1561
  -2.250   0.1026   0.01822   0.00856  -0.0556   0.7607   0.1680
  -2.000   0.1301   0.01802   0.00830  -0.0551   0.7450   0.1816
  -1.750   0.1575   0.01780   0.00806  -0.0546   0.7288   0.1966
  -1.500   0.1851   0.01757   0.00785  -0.0542   0.7120   0.2138
  -1.250   0.2129   0.01736   0.00765  -0.0538   0.6957   0.2347
  -1.000   0.2406   0.01711   0.00747  -0.0535   0.6799   0.2625
  -0.750   0.2680   0.01681   0.00731  -0.0532   0.6644   0.3109
  -0.500   0.2936   0.01605   0.00720  -0.0527   0.6495   0.4866
  -0.250   0.3111   0.01491   0.00720  -0.0487   0.6348   0.8664
   0.000   0.3536   0.01475   0.00692  -0.0511   0.6166   1.0000
   0.250   0.3812   0.01487   0.00684  -0.0508   0.6002   1.0000
   0.500   0.4088   0.01501   0.00679  -0.0505   0.5837   1.0000
   0.750   0.4364   0.01516   0.00675  -0.0502   0.5670   1.0000
   1.000   0.4641   0.01533   0.00674  -0.0499   0.5500   1.0000
   1.250   0.4918   0.01551   0.00675  -0.0497   0.5327   1.0000
   1.500   0.5194   0.01570   0.00678  -0.0495   0.5150   1.0000
   1.750   0.5471   0.01591   0.00683  -0.0493   0.4973   1.0000
   2.000   0.5747   0.01613   0.00691  -0.0491   0.4792   1.0000
   2.250   0.6022   0.01637   0.00701  -0.0490   0.4607   1.0000
   2.500   0.6297   0.01664   0.00713  -0.0488   0.4422   1.0000
   2.750   0.6570   0.01692   0.00727  -0.0486   0.4236   1.0000
   3.000   0.6842   0.01723   0.00744  -0.0485   0.4052   1.0000
   3.250   0.7113   0.01756   0.00764  -0.0483   0.3875   1.0000
   3.500   0.7383   0.01791   0.00787  -0.0482   0.3704   1.0000
   3.750   0.7650   0.01829   0.00812  -0.0480   0.3543   1.0000
   4.000   0.7915   0.01869   0.00839  -0.0478   0.3395   1.0000
   4.250   0.8180   0.01911   0.00870  -0.0477   0.3256   1.0000
   4.500   0.8445   0.01953   0.00905  -0.0475   0.3128   1.0000
   4.750   0.8706   0.01999   0.00942  -0.0473   0.3016   1.0000
   5.000   0.8965   0.02046   0.00980  -0.0471   0.2911   1.0000
   5.250   0.9226   0.02093   0.01023  -0.0469   0.2813   1.0000
   5.500   0.9479   0.02145   0.01065  -0.0466   0.2728   1.0000
   5.750   0.9738   0.02193   0.01113  -0.0464   0.2642   1.0000
   6.000   0.9988   0.02248   0.01160  -0.0461   0.2568   1.0000
   6.250   1.0242   0.02300   0.01212  -0.0459   0.2495   1.0000
   6.500   1.0490   0.02355   0.01266  -0.0456   0.2426   1.0000
   6.750   1.0734   0.02415   0.01319  -0.0452   0.2368   1.0000
   7.000   1.0982   0.02471   0.01381  -0.0449   0.2303   1.0000
   7.250   1.1221   0.02531   0.01438  -0.0445   0.2248   1.0000
   7.500   1.1459   0.02595   0.01501  -0.0441   0.2197   1.0000
   7.750   1.1696   0.02657   0.01571  -0.0437   0.2141   1.0000
   8.000   1.1926   0.02721   0.01634  -0.0432   0.2093   1.0000
   8.250   1.2154   0.02792   0.01702  -0.0426   0.2050   1.0000
   8.500   1.2379   0.02861   0.01784  -0.0421   0.2000   1.0000
   8.750   1.2597   0.02931   0.01857  -0.0415   0.1956   1.0000
   9.000   1.2812   0.03005   0.01927  -0.0408   0.1919   1.0000
   9.250   1.3021   0.03086   0.02019  -0.0401   0.1878   1.0000
   9.500   1.3222   0.03166   0.02110  -0.0393   0.1836   1.0000
   9.750   1.3419   0.03245   0.02193  -0.0385   0.1799   1.0000
  10.000   1.3614   0.03328   0.02273  -0.0377   0.1768   1.0000
  10.250   1.3791   0.03424   0.02385  -0.0367   0.1733   1.0000
  10.500   1.3956   0.03521   0.02495  -0.0355   0.1696   1.0000
  10.750   1.4116   0.03614   0.02595  -0.0343   0.1664   1.0000
  11.000   1.4276   0.03706   0.02689  -0.0331   0.1636   1.0000
  11.250   1.4421   0.03814   0.02803  -0.0318   0.1610   1.0000
  11.500   1.4516   0.03940   0.02950  -0.0300   0.1579   1.0000
  11.750   1.4595   0.04062   0.03087  -0.0279   0.1550   1.0000
  12.000   1.4674   0.04184   0.03217  -0.0259   0.1525   1.0000
  12.250   1.4770   0.04304   0.03341  -0.0243   0.1503   1.0000
  12.500   1.4873   0.04437   0.03474  -0.0230   0.1482   1.0000
  12.750   1.4865   0.04642   0.03707  -0.0210   0.1458   1.0000
  13.000   1.4871   0.04850   0.03937  -0.0196   0.1433   1.0000
  13.250   1.4891   0.05056   0.04157  -0.0184   0.1410   1.0000
  13.500   1.4931   0.05250   0.04360  -0.0176   0.1389   1.0000
  13.750   1.5001   0.05425   0.04538  -0.0168   0.1371   1.0000
  14.000   1.5043   0.05636   0.04757  -0.0162   0.1353   1.0000
  14.250   1.4908   0.06034   0.05186  -0.0160   0.1334   1.0000
  14.500   1.4775   0.06455   0.05633  -0.0162   0.1314   1.0000
  14.750   1.4648   0.06890   0.06089  -0.0168   0.1296   1.0000
  15.000   1.4548   0.07307   0.06523  -0.0176   0.1278   1.0000
  15.250   1.4506   0.07659   0.06883  -0.0183   0.1261   1.0000
  15.500   1.4567   0.07875   0.07100  -0.0184   0.1246   1.0000
  15.750   1.4365   0.08471   0.07715  -0.0204   0.1231   1.0000
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