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ARA-D 6% AIRFOIL (arad6-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: ARA-D 6% AIRFOIL (arad6-il)
Reynolds number: 200,000
Max Cl/Cd: 85.99 at α=3°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-arad6-il-200000-n5.txt
Download as CSV file: xf-arad6-il-200000-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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.2751   0.10181   0.09850  -0.0275   1.0000   0.0237
  -8.750  -0.2763   0.09966   0.09638  -0.0262   1.0000   0.0246
  -8.500  -0.3511   0.10542   0.10184  -0.0283   1.0000   0.0227
  -8.250  -0.3473   0.10301   0.09946  -0.0266   1.0000   0.0235
  -8.000  -0.3491   0.10120   0.09770  -0.0249   1.0000   0.0242
  -7.750  -0.3546   0.09964   0.09619  -0.0228   1.0000   0.0250
  -7.500  -0.3637   0.09829   0.09490  -0.0201   1.0000   0.0256
  -7.250  -0.3589   0.09553   0.09217  -0.0216   0.9978   0.0266
  -7.000  -0.3371   0.09122   0.08784  -0.0284   0.9939   0.0279
  -6.750  -0.3062   0.08667   0.08326  -0.0414   0.9882   0.0292
  -6.500  -0.2745   0.08174   0.07829  -0.0510   0.9851   0.0294
  -6.250  -0.2482   0.07719   0.07371  -0.0576   0.9804   0.0295
  -6.000  -0.2183   0.07235   0.06881  -0.0645   0.9769   0.0295
  -5.750  -0.1855   0.06730   0.06369  -0.0718   0.9744   0.0295
  -5.250  -0.1465   0.05935   0.05571  -0.0758   0.9671   0.0264
  -4.750  -0.0455   0.04437   0.04030  -0.0997   0.9624   0.0217
  -4.500  -0.0005   0.03908   0.03480  -0.1076   0.9610   0.0211
  -4.250   0.0506   0.03233   0.02768  -0.1165   0.9600   0.0206
  -4.000   0.1082   0.02197   0.01615  -0.1263   0.9596   0.0204
  -3.750   0.1444   0.01898   0.01247  -0.1287   0.9559   0.0209
  -3.500   0.1784   0.01758   0.01064  -0.1301   0.9521   0.0223
  -3.250   0.2130   0.01641   0.00928  -0.1318   0.9491   0.0238
  -3.000   0.2482   0.01546   0.00815  -0.1334   0.9466   0.0248
  -2.750   0.2813   0.01471   0.00727  -0.1344   0.9429   0.0261
  -2.500   0.3120   0.01412   0.00657  -0.1349   0.9373   0.0279
  -2.250   0.3454   0.01353   0.00589  -0.1360   0.9335   0.0310
  -2.000   0.3780   0.01314   0.00546  -0.1368   0.9294   0.0388
  -1.750   0.4072   0.01278   0.00516  -0.1371   0.9226   0.0546
  -1.500   0.4391   0.01251   0.00491  -0.1378   0.9179   0.0731
  -1.250   0.4677   0.01238   0.00485  -0.1379   0.9108   0.0960
  -1.000   0.4979   0.01220   0.00469  -0.1382   0.9047   0.1141
  -0.750   0.5269   0.01205   0.00455  -0.1383   0.8974   0.1307
  -0.500   0.5562   0.01190   0.00442  -0.1385   0.8904   0.1486
  -0.250   0.5848   0.01177   0.00435  -0.1385   0.8824   0.1697
   0.000   0.6139   0.01163   0.00426  -0.1386   0.8750   0.1945
   0.250   0.6419   0.01151   0.00424  -0.1385   0.8658   0.2259
   0.500   0.6699   0.01130   0.00416  -0.1383   0.8540   0.2768
   0.750   0.6920   0.01004   0.00414  -0.1368   0.8375   0.7778
   1.250   0.7426   0.00973   0.00371  -0.1345   0.7966   1.0000
   1.500   0.7697   0.00980   0.00365  -0.1340   0.7759   1.0000
   1.750   0.7969   0.00990   0.00365  -0.1335   0.7567   1.0000
   2.000   0.8240   0.01003   0.00368  -0.1332   0.7377   1.0000
   2.250   0.8509   0.01018   0.00372  -0.1327   0.7166   1.0000
   2.500   0.8775   0.01035   0.00379  -0.1322   0.6933   1.0000
   2.750   0.9038   0.01056   0.00389  -0.1317   0.6667   1.0000
   3.000   0.9296   0.01081   0.00401  -0.1311   0.6362   1.0000
   3.250   0.9547   0.01113   0.00415  -0.1304   0.6004   1.0000
   3.500   0.9791   0.01151   0.00433  -0.1295   0.5574   1.0000
   3.750   1.0022   0.01201   0.00459  -0.1285   0.5027   1.0000
   4.000   1.0238   0.01268   0.00491  -0.1274   0.4359   1.0000
   4.250   1.0446   0.01349   0.00533  -0.1262   0.3638   1.0000
   4.500   1.0659   0.01427   0.00580  -0.1252   0.3061   1.0000
   4.750   1.0883   0.01495   0.00629  -0.1243   0.2669   1.0000
   5.000   1.1113   0.01554   0.00675  -0.1236   0.2390   1.0000
   5.250   1.1347   0.01609   0.00721  -0.1229   0.2177   1.0000
   5.500   1.1581   0.01661   0.00767  -0.1223   0.1995   1.0000
   5.750   1.1815   0.01712   0.00817  -0.1216   0.1840   1.0000
   6.000   1.2047   0.01763   0.00866  -0.1208   0.1699   1.0000
   6.250   1.2278   0.01814   0.00916  -0.1201   0.1578   1.0000
   6.500   1.2505   0.01867   0.00969  -0.1193   0.1462   1.0000
   6.750   1.2729   0.01922   0.01023  -0.1184   0.1344   1.0000
   7.000   1.2950   0.01978   0.01082  -0.1176   0.1229   1.0000
   7.250   1.3171   0.02032   0.01140  -0.1167   0.1122   1.0000
   7.500   1.3386   0.02091   0.01202  -0.1157   0.1027   1.0000
   7.750   1.3592   0.02158   0.01270  -0.1146   0.0944   1.0000
   8.000   1.3799   0.02221   0.01342  -0.1134   0.0861   1.0000
   8.250   1.3996   0.02291   0.01417  -0.1122   0.0787   1.0000
   8.500   1.4184   0.02369   0.01497  -0.1108   0.0717   1.0000
   8.750   1.4371   0.02444   0.01583  -0.1094   0.0663   1.0000
   9.000   1.4545   0.02526   0.01670  -0.1078   0.0603   1.0000
   9.250   1.4719   0.02605   0.01761  -0.1062   0.0544   1.0000
   9.500   1.4873   0.02696   0.01852  -0.1044   0.0481   1.0000
   9.750   1.5043   0.02771   0.01939  -0.1028   0.0426   1.0000
  10.000   1.5176   0.02873   0.02041  -0.1008   0.0376   1.0000
  10.250   1.5324   0.02957   0.02142  -0.0988   0.0335   1.0000
  10.500   1.5427   0.03063   0.02254  -0.0962   0.0296   1.0000
  10.750   1.5527   0.03176   0.02381  -0.0936   0.0264   1.0000
  11.000   1.5621   0.03298   0.02518  -0.0911   0.0228   1.0000
  11.250   1.5685   0.03450   0.02679  -0.0883   0.0198   1.0000
  11.500   1.5754   0.03600   0.02844  -0.0857   0.0170   1.0000
  11.750   1.5789   0.03783   0.03036  -0.0830   0.0149   1.0000
  12.000   1.5832   0.03960   0.03232  -0.0804   0.0133   1.0000
  12.250   1.5862   0.04154   0.03440  -0.0780   0.0121   1.0000
  12.500   1.5853   0.04389   0.03689  -0.0755   0.0114   1.0000
  12.750   1.5833   0.04643   0.03961  -0.0731   0.0108   1.0000
  13.000   1.5808   0.04912   0.04252  -0.0711   0.0104   1.0000
  13.250   1.5768   0.05209   0.04569  -0.0693   0.0100   1.0000
  13.500   1.5713   0.05536   0.04917  -0.0679   0.0097   1.0000
  13.750   1.5644   0.05897   0.05301  -0.0668   0.0094   1.0000
  14.000   1.5560   0.06295   0.05719  -0.0662   0.0092   1.0000
  14.250   1.5460   0.06738   0.06181  -0.0661   0.0090   1.0000
  14.500   1.5344   0.07228   0.06692  -0.0665   0.0088   1.0000
  14.750   1.5210   0.07776   0.07260  -0.0676   0.0087   1.0000
  15.000   1.5065   0.08382   0.07886  -0.0694   0.0086   1.0000
  15.250   1.4905   0.09056   0.08580  -0.0719   0.0086   1.0000
  15.500   1.4729   0.09798   0.09342  -0.0751   0.0086   1.0000
  15.750   1.4544   0.10606   0.10170  -0.0791   0.0086   1.0000
  16.000   1.4351   0.11473   0.11056  -0.0836   0.0086   1.0000
  16.250   1.4153   0.12389   0.11992  -0.0886   0.0086   1.0000
  16.500   1.3955   0.13335   0.12955  -0.0939   0.0087   1.0000
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