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ARA-D 6% AIRFOIL (arad6-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: ARA-D 6% AIRFOIL (arad6-il)
Reynolds number: 500,000
Max Cl/Cd: 105.58 at α=1.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-arad6-il-500000-n5.txt
Download as CSV file: xf-arad6-il-500000-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 =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.3526   0.10949   0.10713  -0.0289   1.0000   0.0120
  -9.000  -0.3530   0.10691   0.10457  -0.0286   1.0000   0.0120
  -8.750  -0.3560   0.10460   0.10230  -0.0276   1.0000   0.0120
  -8.500  -0.3473   0.10097   0.09868  -0.0301   0.9982   0.0120
  -8.250  -0.3350   0.09696   0.09467  -0.0338   0.9957   0.0120
  -7.250  -0.2742   0.08020   0.07791  -0.0514   0.9832   0.0125
  -7.000  -0.2558   0.07814   0.07585  -0.0535   0.9797   0.0132
  -6.750  -0.2332   0.07485   0.07255  -0.0586   0.9762   0.0147
  -6.250  -0.1784   0.06213   0.05973  -0.0771   0.9663   0.0118
  -6.000  -0.1486   0.05715   0.05469  -0.0845   0.9621   0.0117
  -5.750  -0.1131   0.05131   0.04877  -0.0935   0.9587   0.0117
  -5.500  -0.0770   0.04512   0.04246  -0.1020   0.9530   0.0119
  -5.000   0.0389   0.01667   0.01206  -0.1323   0.9483   0.0122
  -4.750   0.0715   0.01450   0.00943  -0.1340   0.9451   0.0124
  -4.500   0.1012   0.01325   0.00791  -0.1347   0.9397   0.0127
  -4.250   0.1307   0.01246   0.00695  -0.1351   0.9346   0.0131
  -4.000   0.1601   0.01185   0.00620  -0.1354   0.9303   0.0136
  -3.750   0.1888   0.01133   0.00558  -0.1356   0.9242   0.0140
  -3.500   0.2177   0.01087   0.00501  -0.1357   0.9187   0.0145
  -3.250   0.2466   0.01047   0.00451  -0.1358   0.9130   0.0150
  -3.000   0.2753   0.01013   0.00411  -0.1359   0.9066   0.0157
  -2.750   0.3038   0.00989   0.00380  -0.1359   0.9006   0.0164
  -2.500   0.3327   0.00954   0.00338  -0.1360   0.8935   0.0175
  -2.250   0.3613   0.00930   0.00308  -0.1360   0.8869   0.0188
  -2.000   0.3899   0.00910   0.00285  -0.1361   0.8791   0.0209
  -1.750   0.4185   0.00891   0.00266  -0.1361   0.8718   0.0271
  -1.500   0.4470   0.00875   0.00252  -0.1361   0.8633   0.0420
  -1.250   0.4754   0.00865   0.00243  -0.1361   0.8551   0.0548
  -1.000   0.5037   0.00855   0.00237  -0.1361   0.8463   0.0732
  -0.750   0.5321   0.00848   0.00232  -0.1362   0.8369   0.0897
  -0.500   0.5601   0.00842   0.00228  -0.1361   0.8242   0.1098
  -0.250   0.5873   0.00843   0.00222  -0.1357   0.8023   0.1261
   0.000   0.6145   0.00846   0.00217  -0.1354   0.7771   0.1398
   0.250   0.6420   0.00851   0.00215  -0.1352   0.7563   0.1544
   0.500   0.6694   0.00857   0.00216  -0.1350   0.7323   0.1732
   0.750   0.6967   0.00863   0.00219  -0.1349   0.7082   0.1996
   1.000   0.7242   0.00869   0.00223  -0.1348   0.6867   0.2346
   1.250   0.7519   0.00869   0.00231  -0.1348   0.6651   0.2956
   1.750   0.7992   0.00757   0.00244  -0.1331   0.6168   1.0000
   2.000   0.8259   0.00783   0.00253  -0.1328   0.5860   1.0000
   2.250   0.8523   0.00813   0.00264  -0.1325   0.5512   1.0000
   2.500   0.8782   0.00849   0.00279  -0.1321   0.5090   1.0000
   2.750   0.9034   0.00896   0.00300  -0.1317   0.4550   1.0000
   3.000   0.9279   0.00953   0.00325  -0.1312   0.3919   1.0000
   3.250   0.9522   0.01015   0.00354  -0.1307   0.3271   1.0000
   3.500   0.9772   0.01066   0.00382  -0.1303   0.2830   1.0000
   3.750   1.0025   0.01111   0.00410  -0.1300   0.2495   1.0000
   4.000   1.0282   0.01148   0.00436  -0.1297   0.2249   1.0000
   4.250   1.0539   0.01184   0.00461  -0.1294   0.2052   1.0000
   4.500   1.0798   0.01217   0.00487  -0.1291   0.1887   1.0000
   4.750   1.1055   0.01249   0.00514  -0.1288   0.1746   1.0000
   5.000   1.1311   0.01282   0.00542  -0.1285   0.1616   1.0000
   5.250   1.1567   0.01314   0.00570  -0.1281   0.1513   1.0000
   5.500   1.1822   0.01344   0.00598  -0.1278   0.1412   1.0000
   5.750   1.2073   0.01380   0.00631  -0.1274   0.1289   1.0000
   6.000   1.2321   0.01416   0.00664  -0.1269   0.1177   1.0000
   6.250   1.2567   0.01454   0.00698  -0.1264   0.1081   1.0000
   6.500   1.2814   0.01489   0.00733  -0.1259   0.0996   1.0000
   6.750   1.3056   0.01529   0.00773  -0.1254   0.0909   1.0000
   7.000   1.3292   0.01573   0.00814  -0.1248   0.0820   1.0000
   7.250   1.3530   0.01614   0.00856  -0.1241   0.0747   1.0000
   7.500   1.3761   0.01660   0.00901  -0.1234   0.0672   1.0000
   7.750   1.3985   0.01713   0.00952  -0.1226   0.0585   1.0000
   8.000   1.4209   0.01762   0.01001  -0.1218   0.0516   1.0000
   8.250   1.4428   0.01815   0.01055  -0.1209   0.0454   1.0000
   8.500   1.4641   0.01872   0.01111  -0.1199   0.0396   1.0000
   8.750   1.4856   0.01925   0.01168  -0.1189   0.0356   1.0000
   9.000   1.5061   0.01984   0.01230  -0.1178   0.0311   1.0000
   9.250   1.5261   0.02044   0.01294  -0.1166   0.0273   1.0000
   9.500   1.5454   0.02108   0.01360  -0.1153   0.0233   1.0000
   9.750   1.5638   0.02177   0.01432  -0.1138   0.0195   1.0000
  10.000   1.5807   0.02256   0.01512  -0.1122   0.0153   1.0000
  10.500   1.6110   0.02432   0.01697  -0.1082   0.0088   1.0000
  10.750   1.6246   0.02525   0.01797  -0.1060   0.0075   1.0000
  11.000   1.6372   0.02618   0.01900  -0.1036   0.0067   1.0000
  11.250   1.6463   0.02719   0.02011  -0.1007   0.0062   1.0000
  11.500   1.6542   0.02836   0.02138  -0.0976   0.0057   1.0000
  11.750   1.6620   0.02956   0.02271  -0.0947   0.0054   1.0000
  12.000   1.6705   0.03074   0.02402  -0.0921   0.0051   1.0000
  12.250   1.6779   0.03203   0.02544  -0.0895   0.0049   1.0000
  12.500   1.6844   0.03343   0.02698  -0.0869   0.0046   1.0000
  12.750   1.6896   0.03496   0.02865  -0.0843   0.0044   1.0000
  13.000   1.6934   0.03668   0.03051  -0.0818   0.0043   1.0000
  13.250   1.6958   0.03858   0.03255  -0.0793   0.0041   1.0000
  13.500   1.6962   0.04071   0.03483  -0.0769   0.0040   1.0000
  13.750   1.6947   0.04314   0.03740  -0.0747   0.0039   1.0000
  14.000   1.6910   0.04590   0.04032  -0.0726   0.0038   1.0000
  14.250   1.6846   0.04906   0.04365  -0.0708   0.0037   1.0000
  14.500   1.6752   0.05278   0.04754  -0.0694   0.0036   1.0000
  14.750   1.6642   0.05693   0.05187  -0.0684   0.0036   1.0000
  15.000   1.6544   0.06114   0.05625  -0.0680   0.0035   1.0000
  15.250   1.6446   0.06563   0.06091  -0.0681   0.0035   1.0000
  15.500   1.6329   0.07073   0.06618  -0.0688   0.0035   1.0000
  15.750   1.6190   0.07649   0.07212  -0.0701   0.0035   1.0000
  16.000   1.6027   0.08302   0.07883  -0.0722   0.0035   1.0000
  16.250   1.5843   0.09035   0.08634  -0.0751   0.0034   1.0000
  16.500   1.5631   0.09864   0.09482  -0.0787   0.0034   1.0000
  16.750   1.5392   0.10790   0.10427  -0.0832   0.0035   1.0000
  17.000   1.5131   0.11806   0.11461  -0.0884   0.0035   1.0000
  17.250   1.4867   0.12859   0.12531  -0.0938   0.0035   1.0000
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