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ARA-D 6% AIRFOIL (arad6-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: ARA-D 6% AIRFOIL (arad6-il)
Reynolds number: 500,000
Max Cl/Cd: 122.48 at α=2.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-arad6-il-500000.txt
Download as CSV file: xf-arad6-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.2864   0.10688   0.10475  -0.0263   1.0000   0.0162
  -9.250  -0.2926   0.10483   0.10274  -0.0255   1.0000   0.0163
  -9.000  -0.2994   0.10283   0.10076  -0.0244   1.0000   0.0163
  -8.750  -0.2922   0.09871   0.09665  -0.0275   0.9987   0.0164
  -8.500  -0.2838   0.09448   0.09242  -0.0304   0.9972   0.0164
  -8.250  -0.2761   0.08879   0.08674  -0.0321   0.9960   0.0168
  -8.000  -0.2619   0.08494   0.08288  -0.0333   0.9950   0.0171
  -7.750  -0.2503   0.08128   0.07922  -0.0354   0.9933   0.0176
  -7.500  -0.2399   0.07761   0.07555  -0.0377   0.9907   0.0182
  -7.250  -0.3473   0.08947   0.08734  -0.0304   0.9948   0.0169
  -7.000  -0.3287   0.08615   0.08401  -0.0331   0.9928   0.0174
  -6.750  -0.3071   0.08254   0.08039  -0.0379   0.9898   0.0180
  -6.500  -0.2814   0.07847   0.07630  -0.0443   0.9872   0.0189
  -6.250  -0.2500   0.07375   0.07155  -0.0527   0.9851   0.0204
  -6.000  -0.1945   0.06728   0.06500  -0.0703   0.9834   0.0218
  -5.750  -0.1719   0.06098   0.05867  -0.0767   0.9788   0.0224
  -5.500  -0.1452   0.05796   0.05563  -0.0802   0.9765   0.0230
  -5.250  -0.1119   0.05461   0.05223  -0.0856   0.9747   0.0239
  -5.000  -0.0714   0.05049   0.04804  -0.0932   0.9735   0.0255
  -4.750  -0.0065   0.04424   0.04158  -0.1068   0.9727   0.0287
  -4.500   0.0354   0.03711   0.03428  -0.1158   0.9720   0.0302
  -4.250   0.0710   0.03497   0.03208  -0.1195   0.9710   0.0316
  -4.000   0.1092   0.03174   0.02868  -0.1238   0.9680   0.0342
  -3.750   0.1825   0.01487   0.00987  -0.1368   0.9699   0.0225
  -3.500   0.2138   0.01344   0.00814  -0.1375   0.9653   0.0224
  -3.250   0.2476   0.01205   0.00652  -0.1388   0.9622   0.0230
  -3.000   0.2812   0.01129   0.00566  -0.1399   0.9594   0.0242
  -2.750   0.3142   0.01074   0.00505  -0.1408   0.9566   0.0256
  -2.500   0.3417   0.01036   0.00461  -0.1406   0.9500   0.0273
  -2.250   0.3718   0.00992   0.00411  -0.1408   0.9451   0.0298
  -2.000   0.4008   0.00953   0.00371  -0.1408   0.9398   0.0348
  -1.750   0.4291   0.00915   0.00335  -0.1406   0.9331   0.0531
  -1.500   0.4572   0.00898   0.00322  -0.1404   0.9277   0.0723
  -1.250   0.4843   0.00888   0.00314  -0.1401   0.9197   0.0880
  -1.000   0.5120   0.00875   0.00304  -0.1398   0.9137   0.1065
  -0.750   0.5394   0.00865   0.00300  -0.1396   0.9052   0.1275
  -0.500   0.5664   0.00855   0.00290  -0.1391   0.8960   0.1475
  -0.250   0.5929   0.00840   0.00278  -0.1385   0.8827   0.1671
   0.000   0.6197   0.00830   0.00267  -0.1379   0.8685   0.1886
   0.250   0.6471   0.00820   0.00261  -0.1376   0.8555   0.2170
   0.500   0.6746   0.00807   0.00257  -0.1374   0.8411   0.2673
   0.750   0.6952   0.00646   0.00255  -0.1359   0.8276   1.0000
   1.000   0.7229   0.00653   0.00251  -0.1356   0.8137   1.0000
   1.250   0.7506   0.00661   0.00250  -0.1354   0.7994   1.0000
   1.500   0.7781   0.00671   0.00251  -0.1352   0.7839   1.0000
   1.750   0.8056   0.00682   0.00254  -0.1349   0.7671   1.0000
   2.000   0.8330   0.00694   0.00258  -0.1347   0.7487   1.0000
   2.250   0.8601   0.00709   0.00262  -0.1344   0.7283   1.0000
   2.500   0.8871   0.00726   0.00269  -0.1341   0.7056   1.0000
   2.750   0.9137   0.00746   0.00279  -0.1337   0.6800   1.0000
   3.000   0.9401   0.00769   0.00289  -0.1333   0.6509   1.0000
   3.250   0.9660   0.00797   0.00302  -0.1328   0.6154   1.0000
   3.500   0.9916   0.00830   0.00318  -0.1323   0.5760   1.0000
   3.750   1.0159   0.00877   0.00341  -0.1317   0.5218   1.0000
   4.000   1.0391   0.00941   0.00370  -0.1309   0.4505   1.0000
   4.250   1.0612   0.01024   0.00409  -0.1300   0.3637   1.0000
   4.500   1.0836   0.01104   0.00451  -0.1292   0.2931   1.0000
   4.750   1.1076   0.01162   0.00490  -0.1287   0.2533   1.0000
   5.000   1.1322   0.01212   0.00525  -0.1282   0.2250   1.0000
   5.250   1.1569   0.01257   0.00559  -0.1278   0.2045   1.0000
   5.500   1.1818   0.01296   0.00592  -0.1273   0.1875   1.0000
   5.750   1.2067   0.01336   0.00628  -0.1269   0.1722   1.0000
   6.000   1.2314   0.01375   0.00663  -0.1264   0.1584   1.0000
   6.250   1.2558   0.01416   0.00700  -0.1259   0.1459   1.0000
   6.500   1.2801   0.01457   0.00737  -0.1253   0.1342   1.0000
   6.750   1.3045   0.01496   0.00776  -0.1248   0.1229   1.0000
   7.000   1.3284   0.01538   0.00817  -0.1242   0.1117   1.0000
   7.250   1.3518   0.01584   0.00862  -0.1235   0.1015   1.0000
   7.500   1.3746   0.01636   0.00911  -0.1227   0.0915   1.0000
   8.000   1.4195   0.01739   0.01011  -0.1211   0.0717   1.0000
   8.250   1.4415   0.01791   0.01064  -0.1202   0.0636   1.0000
   8.500   1.4622   0.01857   0.01127  -0.1191   0.0561   1.0000
   8.750   1.4839   0.01907   0.01182  -0.1181   0.0508   1.0000
   9.000   1.5034   0.01980   0.01256  -0.1168   0.0452   1.0000
   9.250   1.5245   0.02029   0.01312  -0.1158   0.0409   1.0000
   9.500   1.5426   0.02108   0.01390  -0.1143   0.0357   1.0000
   9.750   1.5628   0.02158   0.01447  -0.1131   0.0313   1.0000
  10.000   1.5800   0.02238   0.01528  -0.1115   0.0257   1.0000
  10.250   1.5943   0.02341   0.01631  -0.1093   0.0193   1.0000
  10.500   1.6048   0.02473   0.01767  -0.1066   0.0150   1.0000
  10.750   1.6183   0.02566   0.01871  -0.1043   0.0133   1.0000
  11.000   1.6283   0.02676   0.01989  -0.1014   0.0121   1.0000
  11.250   1.6291   0.02840   0.02164  -0.0971   0.0111   1.0000
  11.500   1.6346   0.02975   0.02313  -0.0938   0.0106   1.0000
  11.750   1.6414   0.03105   0.02457  -0.0908   0.0101   1.0000
  12.000   1.6474   0.03245   0.02609  -0.0880   0.0095   1.0000
  12.250   1.6525   0.03397   0.02773  -0.0852   0.0091   1.0000
  12.500   1.6557   0.03569   0.02958  -0.0825   0.0087   1.0000
  12.750   1.6551   0.03780   0.03183  -0.0796   0.0084   1.0000
  13.000   1.6498   0.04046   0.03463  -0.0765   0.0081   1.0000
  13.250   1.6408   0.04363   0.03797  -0.0736   0.0079   1.0000
  13.500   1.6284   0.04738   0.04192  -0.0709   0.0078   1.0000
  13.750   1.6248   0.05033   0.04503  -0.0692   0.0077   1.0000
  14.000   1.6204   0.05354   0.04841  -0.0679   0.0076   1.0000
  14.250   1.6138   0.05717   0.05222  -0.0669   0.0075   1.0000
  14.500   1.6056   0.06117   0.05639  -0.0663   0.0075   1.0000
  14.750   1.5957   0.06561   0.06102  -0.0662   0.0074   1.0000
  15.000   1.5846   0.07052   0.06611  -0.0666   0.0073   1.0000
  15.250   1.5720   0.07591   0.07168  -0.0675   0.0073   1.0000
  15.500   1.5585   0.08178   0.07773  -0.0691   0.0072   1.0000
  15.750   1.5435   0.08821   0.08434  -0.0712   0.0072   1.0000
  16.000   1.5274   0.09518   0.09149  -0.0740   0.0072   1.0000
  16.250   1.5103   0.10263   0.09911  -0.0772   0.0072   1.0000
  16.500   1.4928   0.11052   0.10718  -0.0811   0.0072   1.0000
  16.750   1.4746   0.11885   0.11567  -0.0854   0.0072   1.0000
  17.000   1.4563   0.12746   0.12445  -0.0900   0.0072   1.0000
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