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ARA-D 6% AIRFOIL (arad6-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: ARA-D 6% AIRFOIL (arad6-il)
Reynolds number: 200,000
Max Cl/Cd: 93.01 at α=4°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-arad6-il-200000.txt
Download as CSV file: xf-arad6-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.3514   0.10046   0.09701  -0.0231   1.0000   0.0335
  -7.500  -0.3605   0.09908   0.09569  -0.0205   1.0000   0.0342
  -7.250  -0.3709   0.09781   0.09448  -0.0179   1.0000   0.0349
  -7.000  -0.3763   0.09621   0.09294  -0.0173   1.0000   0.0361
  -6.750  -0.3792   0.09513   0.09192  -0.0201   1.0000   0.0371
  -6.500  -0.3723   0.09344   0.09025  -0.0259   1.0000   0.0376
  -6.250  -0.3611   0.09069   0.08750  -0.0302   1.0000   0.0378
  -6.000  -0.3594   0.08579   0.08264  -0.0302   1.0000   0.0382
  -5.750  -0.3605   0.08245   0.07934  -0.0266   1.0000   0.0388
  -5.500  -0.3474   0.07914   0.07604  -0.0265   0.9986   0.0398
  -5.250  -0.3181   0.07517   0.07203  -0.0315   0.9955   0.0414
  -5.000  -0.2824   0.07086   0.06766  -0.0391   0.9921   0.0438
  -4.750  -0.1989   0.06513   0.06163  -0.0620   0.9879   0.0487
  -4.500  -0.1699   0.05860   0.05507  -0.0674   0.9854   0.0499
  -4.250  -0.1437   0.05546   0.05194  -0.0693   0.9833   0.0517
  -4.000  -0.1110   0.05239   0.04881  -0.0734   0.9785   0.0553
  -3.750  -0.0440   0.04622   0.04229  -0.0873   0.9758   0.0629
  -3.500  -0.0112   0.04350   0.03955  -0.0903   0.9732   0.0654
  -2.750   0.1572   0.02570   0.02012  -0.1134   0.9707   0.0465
  -2.500   0.2003   0.02222   0.01599  -0.1169   0.9686   0.0454
  -2.250   0.2392   0.02037   0.01361  -0.1190   0.9650   0.0472
  -2.000   0.2802   0.01893   0.01177  -0.1214   0.9625   0.0486
  -1.750   0.3218   0.01749   0.01020  -0.1243   0.9607   0.0541
  -1.500   0.3636   0.01677   0.00945  -0.1271   0.9585   0.0691
  -1.250   0.4067   0.01620   0.00889  -0.1302   0.9567   0.0982
  -1.000   0.4370   0.01608   0.00882  -0.1308   0.9490   0.1230
  -0.750   0.4779   0.01566   0.00842  -0.1335   0.9458   0.1485
  -0.500   0.5211   0.01516   0.00800  -0.1367   0.9438   0.1776
  -0.250   0.5569   0.01480   0.00778  -0.1384   0.9384   0.2091
   0.000   0.5933   0.01440   0.00752  -0.1401   0.9330   0.2492
   0.250   0.6333   0.01368   0.00724  -0.1427   0.9299   0.3515
   0.500   0.6579   0.01221   0.00697  -0.1413   0.9214   1.0000
   0.750   0.6965   0.01166   0.00628  -0.1425   0.9138   1.0000
   1.000   0.7250   0.01132   0.00585  -0.1417   0.9006   1.0000
   1.250   0.7523   0.01108   0.00555  -0.1407   0.8874   1.0000
   1.500   0.7793   0.01093   0.00534  -0.1399   0.8746   1.0000
   1.750   0.8064   0.01085   0.00523  -0.1392   0.8624   1.0000
   2.000   0.8335   0.01079   0.00513  -0.1385   0.8500   1.0000
   2.250   0.8604   0.01074   0.00505  -0.1377   0.8362   1.0000
   2.500   0.8871   0.01072   0.00499  -0.1370   0.8210   1.0000
   2.750   0.9136   0.01072   0.00498  -0.1362   0.8043   1.0000
   3.000   0.9402   0.01074   0.00495  -0.1354   0.7863   1.0000
   3.250   0.9663   0.01080   0.00497  -0.1346   0.7652   1.0000
   3.500   0.9923   0.01089   0.00499  -0.1337   0.7419   1.0000
   3.750   1.0177   0.01102   0.00508  -0.1328   0.7144   1.0000
   4.000   1.0426   0.01121   0.00517  -0.1318   0.6820   1.0000
   4.250   1.0668   0.01148   0.00530  -0.1307   0.6414   1.0000
   4.500   1.0897   0.01187   0.00549  -0.1294   0.5883   1.0000
   4.750   1.1099   0.01252   0.00579  -0.1276   0.5117   1.0000
   5.000   1.1263   0.01360   0.00627  -0.1255   0.4068   1.0000
   5.250   1.1428   0.01481   0.00694  -0.1236   0.3207   1.0000
   5.500   1.1621   0.01580   0.00762  -0.1222   0.2753   1.0000
   5.750   1.1829   0.01664   0.00827  -0.1211   0.2467   1.0000
   6.000   1.2048   0.01734   0.00893  -0.1202   0.2240   1.0000
   6.250   1.2262   0.01809   0.00957  -0.1191   0.2057   1.0000
   6.500   1.2473   0.01885   0.01026  -0.1181   0.1896   1.0000
   6.750   1.2690   0.01953   0.01092  -0.1171   0.1743   1.0000
   7.000   1.2901   0.02025   0.01164  -0.1160   0.1602   1.0000
   7.250   1.3108   0.02099   0.01236  -0.1149   0.1468   1.0000
   7.500   1.3316   0.02169   0.01308  -0.1137   0.1343   1.0000
   7.750   1.3523   0.02239   0.01386  -0.1125   0.1229   1.0000
   8.000   1.3719   0.02321   0.01474  -0.1112   0.1121   1.0000
   8.250   1.3905   0.02414   0.01568  -0.1097   0.1024   1.0000
   8.500   1.4079   0.02522   0.01672  -0.1081   0.0939   1.0000
   8.750   1.4270   0.02604   0.01770  -0.1066   0.0862   1.0000
   9.000   1.4432   0.02724   0.01890  -0.1049   0.0790   1.0000
   9.250   1.4602   0.02787   0.01965  -0.1032   0.0717   1.0000
   9.500   1.4751   0.02889   0.02078  -0.1013   0.0647   1.0000
   9.750   1.4887   0.02977   0.02170  -0.0992   0.0585   1.0000
  10.000   1.5017   0.03096   0.02304  -0.0970   0.0529   1.0000
  10.250   1.5108   0.03201   0.02413  -0.0943   0.0472   1.0000
  10.500   1.5193   0.03335   0.02565  -0.0913   0.0416   1.0000
  10.750   1.5226   0.03513   0.02743  -0.0880   0.0367   1.0000
  11.000   1.5289   0.03695   0.02949  -0.0849   0.0323   1.0000
  11.250   1.5330   0.03865   0.03129  -0.0820   0.0292   1.0000
  11.500   1.5338   0.04145   0.03422  -0.0788   0.0268   1.0000
  11.750   1.5381   0.04331   0.03633  -0.0762   0.0248   1.0000
  12.000   1.5408   0.04532   0.03849  -0.0737   0.0232   1.0000
  12.250   1.5416   0.04765   0.04093  -0.0713   0.0221   1.0000
  12.500   1.5395   0.05075   0.04416  -0.0688   0.0212   1.0000
  12.750   1.5319   0.05512   0.04879  -0.0661   0.0205   1.0000
  13.000   1.5264   0.05834   0.05230  -0.0640   0.0202   1.0000
  13.250   1.5182   0.06205   0.05630  -0.0622   0.0199   1.0000
  13.500   1.5073   0.06622   0.06077  -0.0608   0.0196   1.0000
  13.750   1.4938   0.07089   0.06572  -0.0600   0.0194   1.0000
  14.000   1.4780   0.07607   0.07117  -0.0598   0.0193   1.0000
  14.250   1.4602   0.08182   0.07719  -0.0605   0.0192   1.0000
  14.500   1.4408   0.08819   0.08381  -0.0621   0.0192   1.0000
  14.750   1.4201   0.09524   0.09111  -0.0647   0.0193   1.0000
  15.000   1.3985   0.10313   0.09923  -0.0685   0.0194   1.0000
  15.250   1.3762   0.11188   0.10820  -0.0734   0.0195   1.0000
  15.500   1.3534   0.12150   0.11802  -0.0794   0.0197   1.0000
  15.750   1.3296   0.13224   0.12894  -0.0865   0.0199   1.0000
  16.000   1.3049   0.14408   0.14093  -0.0945   0.0202   1.0000
  16.250   0.8998   0.17495   0.17206  -0.0901   0.0351   1.0000
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