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ARA-D 10% AIRFOIL (arad10-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: ARA-D 10% AIRFOIL (arad10-il)
Reynolds number: 100,000
Max Cl/Cd: 49.47 at α=4°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-arad10-il-100000-n5.txt
Download as CSV file: xf-arad10-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: ARA-D 10% 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
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.3776   0.09330   0.08815  -0.0259   1.0000   0.0374
  -8.000  -0.3810   0.08992   0.08485  -0.0268   1.0000   0.0374
  -7.750  -0.3838   0.08640   0.08140  -0.0283   1.0000   0.0375
  -7.500  -0.3849   0.08260   0.07765  -0.0305   1.0000   0.0376
  -7.250  -0.3858   0.07852   0.07363  -0.0327   1.0000   0.0376
  -7.000  -0.3857   0.07392   0.06904  -0.0355   1.0000   0.0373
  -6.750  -0.3849   0.06779   0.06287  -0.0396   1.0000   0.0367
  -6.250  -0.3691   0.05059   0.04520  -0.0507   1.0000   0.0360
  -6.000  -0.3542   0.04540   0.03976  -0.0528   1.0000   0.0365
  -5.750  -0.3331   0.04052   0.03453  -0.0553   0.9991   0.0374
  -5.500  -0.2949   0.03201   0.02485  -0.0618   0.9953   0.0409
  -5.250  -0.2585   0.02956   0.02205  -0.0647   0.9908   0.0429
  -5.000  -0.2213   0.02729   0.01936  -0.0674   0.9861   0.0454
  -4.750  -0.1833   0.02547   0.01713  -0.0699   0.9817   0.0494
  -4.500  -0.1467   0.02423   0.01563  -0.0719   0.9758   0.0539
  -4.250  -0.1077   0.02331   0.01459  -0.0744   0.9713   0.0587
  -4.000  -0.0713   0.02226   0.01328  -0.0762   0.9649   0.0648
  -3.750  -0.0327   0.02162   0.01257  -0.0785   0.9593   0.0713
  -3.500   0.0053   0.02097   0.01187  -0.0805   0.9536   0.0782
  -3.250   0.0407   0.02030   0.01107  -0.0819   0.9455   0.0859
  -3.000   0.0787   0.01977   0.01051  -0.0839   0.9395   0.0942
  -2.750   0.1112   0.01929   0.01003  -0.0847   0.9293   0.1021
  -2.500   0.1465   0.01879   0.00946  -0.0859   0.9213   0.1121
  -2.250   0.1790   0.01840   0.00909  -0.0866   0.9109   0.1222
  -2.000   0.2109   0.01802   0.00874  -0.0872   0.9003   0.1332
  -1.750   0.2441   0.01763   0.00835  -0.0879   0.8909   0.1461
  -1.500   0.2735   0.01736   0.00808  -0.0878   0.8780   0.1599
  -1.250   0.3032   0.01709   0.00782  -0.0878   0.8655   0.1754
  -0.750   0.3612   0.01651   0.00733  -0.0873   0.8376   0.2118
  -0.500   0.3885   0.01622   0.00707  -0.0865   0.8180   0.2350
  -0.250   0.4159   0.01593   0.00682  -0.0858   0.7971   0.2683
   0.000   0.4433   0.01550   0.00662  -0.0853   0.7773   0.3425
   0.500   0.4924   0.01377   0.00618  -0.0821   0.7402   1.0000
   0.750   0.5199   0.01387   0.00609  -0.0815   0.7204   1.0000
   1.000   0.5473   0.01399   0.00603  -0.0810   0.6997   1.0000
   1.250   0.5746   0.01413   0.00599  -0.0804   0.6788   1.0000
   1.500   0.6018   0.01429   0.00598  -0.0799   0.6576   1.0000
   1.750   0.6289   0.01447   0.00599  -0.0794   0.6356   1.0000
   2.000   0.6559   0.01466   0.00604  -0.0789   0.6118   1.0000
   2.250   0.6827   0.01489   0.00609  -0.0784   0.5876   1.0000
   2.500   0.7094   0.01513   0.00619  -0.0779   0.5607   1.0000
   2.750   0.7357   0.01540   0.00630  -0.0774   0.5325   1.0000
   3.000   0.7618   0.01572   0.00643  -0.0768   0.5022   1.0000
   3.250   0.7875   0.01608   0.00660  -0.0763   0.4698   1.0000
   3.500   0.8128   0.01648   0.00681  -0.0757   0.4360   1.0000
   3.750   0.8379   0.01694   0.00706  -0.0752   0.4027   1.0000
   4.000   0.8627   0.01744   0.00736  -0.0746   0.3714   1.0000
   4.250   0.8874   0.01796   0.00770  -0.0741   0.3435   1.0000
   4.500   0.9118   0.01852   0.00808  -0.0736   0.3210   1.0000
   4.750   0.9365   0.01906   0.00851  -0.0731   0.3018   1.0000
   5.000   0.9610   0.01962   0.00895  -0.0726   0.2857   1.0000
   5.250   0.9852   0.02020   0.00942  -0.0721   0.2721   1.0000
   5.500   1.0098   0.02074   0.00991  -0.0716   0.2598   1.0000
   5.750   1.0342   0.02130   0.01044  -0.0711   0.2491   1.0000
   6.000   1.0578   0.02193   0.01097  -0.0705   0.2399   1.0000
   6.250   1.0824   0.02246   0.01154  -0.0701   0.2306   1.0000
   6.500   1.1057   0.02310   0.01212  -0.0694   0.2230   1.0000
   6.750   1.1298   0.02366   0.01273  -0.0689   0.2149   1.0000
   7.000   1.1526   0.02435   0.01334  -0.0683   0.2085   1.0000
   7.250   1.1764   0.02493   0.01402  -0.0677   0.2014   1.0000
   7.500   1.1991   0.02559   0.01468  -0.0670   0.1952   1.0000
   7.750   1.2218   0.02629   0.01539  -0.0664   0.1894   1.0000
   8.000   1.2444   0.02695   0.01615  -0.0657   0.1835   1.0000
   8.250   1.2659   0.02770   0.01686  -0.0649   0.1784   1.0000
   8.500   1.2879   0.02843   0.01770  -0.0641   0.1731   1.0000
   8.750   1.3091   0.02917   0.01853  -0.0633   0.1678   1.0000
   9.000   1.3295   0.02997   0.01931  -0.0624   0.1635   1.0000
   9.250   1.3500   0.03080   0.02027  -0.0615   0.1588   1.0000
   9.500   1.3697   0.03162   0.02120  -0.0605   0.1540   1.0000
   9.750   1.3883   0.03246   0.02208  -0.0594   0.1500   1.0000
  10.000   1.4069   0.03341   0.02311  -0.0583   0.1461   1.0000
  10.250   1.4243   0.03435   0.02424  -0.0570   0.1417   1.0000
  10.500   1.4406   0.03527   0.02525  -0.0556   0.1379   1.0000
  10.750   1.4563   0.03624   0.02622  -0.0542   0.1347   1.0000
  11.000   1.4706   0.03737   0.02756  -0.0526   0.1311   1.0000
  11.250   1.4832   0.03849   0.02886  -0.0508   0.1275   1.0000
  11.500   1.4945   0.03956   0.03004  -0.0489   0.1243   1.0000
  11.750   1.5040   0.04065   0.03115  -0.0468   0.1218   1.0000
  12.000   1.5118   0.04204   0.03271  -0.0446   0.1191   1.0000
  12.250   1.5173   0.04356   0.03447  -0.0423   0.1161   1.0000
  12.500   1.5227   0.04508   0.03614  -0.0402   0.1133   1.0000
  12.750   1.5284   0.04656   0.03772  -0.0383   0.1109   1.0000
  13.000   1.5353   0.04805   0.03924  -0.0367   0.1089   1.0000
  13.250   1.5364   0.05022   0.04164  -0.0349   0.1066   1.0000
  13.500   1.5352   0.05262   0.04432  -0.0333   0.1042   1.0000
  13.750   1.5342   0.05504   0.04693  -0.0319   0.1020   1.0000
  14.000   1.5339   0.05741   0.04944  -0.0309   0.1000   1.0000
  14.250   1.5353   0.05968   0.05179  -0.0301   0.0982   1.0000
  14.500   1.5382   0.06194   0.05407  -0.0293   0.0965   1.0000
  14.750   1.5247   0.06623   0.05871  -0.0291   0.0949   1.0000
  15.000   1.5101   0.07088   0.06366  -0.0294   0.0933   1.0000
  15.250   1.4945   0.07590   0.06894  -0.0303   0.0918   1.0000
  15.500   1.4781   0.08125   0.07450  -0.0317   0.0904   1.0000
  15.750   1.4616   0.08686   0.08030  -0.0335   0.0891   1.0000
  16.000   1.4482   0.09226   0.08584  -0.0355   0.0879   1.0000
  16.250   1.4451   0.09604   0.08967  -0.0367   0.0865   1.0000
  16.500   1.4324   0.10166   0.09539  -0.0390   0.0854   1.0000
  16.750   1.3524   0.12125   0.11541  -0.0509   0.0850   1.0000
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