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DAE-21 AIRFOIL (dae21-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: DAE-21 AIRFOIL (dae21-il)
Reynolds number: 1,000,000
Max Cl/Cd: 173.55 at α=5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-dae21-il-1000000.txt
Download as CSV file: xf-dae21-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: DAE-21 AIRFOIL                                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.0377   0.08638   0.08355  -0.0769   0.7247   0.0130
  -8.250  -0.0300   0.08379   0.08097  -0.0781   0.7223   0.0132
  -8.000  -0.0226   0.08120   0.07838  -0.0793   0.7200   0.0135
  -7.750   0.0006   0.06429   0.06165  -0.0745   0.7092   0.0148
  -7.500   0.0017   0.06024   0.05761  -0.0756   0.7071   0.0149
  -7.250   0.0087   0.05755   0.05493  -0.0763   0.7048   0.0150
  -7.000   0.0168   0.05517   0.05256  -0.0768   0.7024   0.0151
  -6.750   0.0229   0.05268   0.05006  -0.0775   0.7000   0.0153
  -6.500   0.0259   0.05021   0.04757  -0.0780   0.6971   0.0154
  -6.250   0.0294   0.04769   0.04509  -0.0789   0.6951   0.0157
  -6.000   0.0370   0.04458   0.04199  -0.0814   0.6927   0.0160
  -5.750   0.0465   0.04112   0.03853  -0.0848   0.6904   0.0164
  -5.500   0.0584   0.03693   0.03433  -0.0897   0.6881   0.0170
  -5.000   0.1099   0.03515   0.03204  -0.1210   0.6899   0.0181
  -4.750   0.1343   0.03290   0.02971  -0.1230   0.6875   0.0183
  -4.500   0.1621   0.01968   0.01535  -0.1295   0.6855   0.0179
  -4.250   0.1882   0.01733   0.01283  -0.1303   0.6829   0.0170
  -4.000   0.2156   0.01431   0.00926  -0.1309   0.6802   0.0167
  -3.750   0.2440   0.01280   0.00747  -0.1312   0.6781   0.0168
  -3.500   0.2727   0.01191   0.00640  -0.1313   0.6757   0.0171
  -3.250   0.3016   0.01147   0.00582  -0.1315   0.6730   0.0177
  -3.000   0.3300   0.01057   0.00479  -0.1316   0.6704   0.0182
  -2.750   0.3585   0.01014   0.00432  -0.1317   0.6677   0.0188
  -2.500   0.3870   0.00988   0.00399  -0.1318   0.6645   0.0194
  -2.250   0.4160   0.00956   0.00366  -0.1320   0.6622   0.0201
  -2.000   0.4449   0.00929   0.00335  -0.1321   0.6594   0.0207
  -1.750   0.4738   0.00897   0.00300  -0.1322   0.6565   0.0215
  -1.500   0.5025   0.00869   0.00271  -0.1324   0.6536   0.0225
  -1.250   0.5313   0.00858   0.00256  -0.1325   0.6504   0.0240
  -1.000   0.5602   0.00843   0.00238  -0.1326   0.6474   0.0253
  -0.750   0.5892   0.00822   0.00220  -0.1328   0.6443   0.0271
  -0.500   0.6182   0.00811   0.00208  -0.1330   0.6411   0.0291
  -0.250   0.6471   0.00797   0.00193  -0.1331   0.6377   0.0331
   0.000   0.6758   0.00787   0.00183  -0.1332   0.6342   0.0417
   0.250   0.7046   0.00768   0.00178  -0.1334   0.6309   0.0810
   0.500   0.7333   0.00744   0.00177  -0.1337   0.6274   0.1650
   0.750   0.7617   0.00718   0.00179  -0.1340   0.6236   0.2819
   1.000   0.7898   0.00695   0.00184  -0.1342   0.6197   0.4099
   1.250   0.8176   0.00674   0.00191  -0.1343   0.6157   0.5427
   1.500   0.8451   0.00583   0.00201  -0.1343   0.6118   1.0000
   1.750   0.8738   0.00588   0.00202  -0.1344   0.6073   1.0000
   2.000   0.9021   0.00598   0.00204  -0.1345   0.6026   1.0000
   2.250   0.9307   0.00603   0.00207  -0.1346   0.5982   1.0000
   2.500   0.9593   0.00609   0.00210  -0.1348   0.5932   1.0000
   2.750   0.9874   0.00618   0.00214  -0.1348   0.5879   1.0000
   3.000   1.0157   0.00626   0.00220  -0.1349   0.5828   1.0000
   3.250   1.0440   0.00633   0.00225  -0.1351   0.5769   1.0000
   3.500   1.0717   0.00645   0.00232  -0.1351   0.5709   1.0000
   3.750   1.1000   0.00652   0.00239  -0.1352   0.5650   1.0000
   4.000   1.1277   0.00663   0.00247  -0.1353   0.5583   1.0000
   4.250   1.1553   0.00675   0.00256  -0.1353   0.5518   1.0000
   4.500   1.1830   0.00686   0.00266  -0.1354   0.5444   1.0000
   4.750   1.2101   0.00700   0.00277  -0.1354   0.5370   1.0000
   5.000   1.2374   0.00713   0.00288  -0.1354   0.5283   1.0000
   5.250   1.2642   0.00729   0.00301  -0.1353   0.5196   1.0000
   5.500   1.2905   0.00748   0.00316  -0.1352   0.5095   1.0000
   5.750   1.3171   0.00765   0.00331  -0.1351   0.4996   1.0000
   6.000   1.3429   0.00786   0.00349  -0.1349   0.4891   1.0000
   6.500   1.3934   0.00834   0.00390  -0.1344   0.4644   1.0000
   6.750   1.4181   0.00861   0.00412  -0.1341   0.4512   1.0000
   7.000   1.4419   0.00892   0.00438  -0.1336   0.4366   1.0000
   7.250   1.4651   0.00925   0.00466  -0.1331   0.4218   1.0000
   7.500   1.4877   0.00961   0.00496  -0.1324   0.4067   1.0000
   7.750   1.5092   0.01000   0.00530  -0.1316   0.3906   1.0000
   8.000   1.5296   0.01043   0.00567  -0.1307   0.3739   1.0000
   8.250   1.5482   0.01092   0.00608  -0.1294   0.3558   1.0000
   8.500   1.5652   0.01145   0.00653  -0.1280   0.3383   1.0000
   8.750   1.5794   0.01205   0.00705  -0.1260   0.3198   1.0000
   9.000   1.5901   0.01265   0.00758  -0.1235   0.3034   1.0000
   9.250   1.5955   0.01335   0.00823  -0.1201   0.2881   1.0000
   9.500   1.6006   0.01421   0.00903  -0.1170   0.2728   1.0000
   9.750   1.6069   0.01517   0.00994  -0.1144   0.2580   1.0000
  10.000   1.6130   0.01625   0.01096  -0.1120   0.2421   1.0000
  10.250   1.6192   0.01741   0.01206  -0.1098   0.2269   1.0000
  10.500   1.6257   0.01861   0.01321  -0.1077   0.2128   1.0000
  10.750   1.6317   0.01990   0.01444  -0.1056   0.1986   1.0000
  11.000   1.6372   0.02125   0.01574  -0.1036   0.1848   1.0000
  11.250   1.6427   0.02266   0.01710  -0.1017   0.1715   1.0000
  11.500   1.6476   0.02414   0.01853  -0.0998   0.1584   1.0000
  11.750   1.6527   0.02565   0.01999  -0.0981   0.1461   1.0000
  12.000   1.6574   0.02722   0.02152  -0.0963   0.1345   1.0000
  12.250   1.6617   0.02886   0.02314  -0.0947   0.1237   1.0000
  12.500   1.6666   0.03049   0.02474  -0.0931   0.1144   1.0000
  12.750   1.6693   0.03234   0.02655  -0.0915   0.1047   1.0000
  13.000   1.6746   0.03405   0.02825  -0.0902   0.0966   1.0000
  13.250   1.6794   0.03586   0.03005  -0.0889   0.0889   1.0000
  13.500   1.6830   0.03784   0.03201  -0.0877   0.0818   1.0000
  13.750   1.6883   0.03970   0.03388  -0.0866   0.0756   1.0000
  14.000   1.6923   0.04174   0.03592  -0.0856   0.0695   1.0000
  14.250   1.6961   0.04385   0.03803  -0.0846   0.0641   1.0000
  14.500   1.7008   0.04593   0.04013  -0.0837   0.0594   1.0000
  14.750   1.7034   0.04826   0.04246  -0.0829   0.0547   1.0000
  15.000   1.7087   0.05037   0.04461  -0.0822   0.0512   1.0000
  15.250   1.7101   0.05293   0.04718  -0.0815   0.0472   1.0000
  15.500   1.7152   0.05514   0.04944  -0.0810   0.0443   1.0000
  15.750   1.7161   0.05789   0.05220  -0.0805   0.0411   1.0000
  16.000   1.7204   0.06027   0.05464  -0.0801   0.0386   1.0000
  16.250   1.7214   0.06311   0.05751  -0.0798   0.0361   1.0000
  16.500   1.7225   0.06597   0.06042  -0.0796   0.0338   1.0000
  16.750   1.7250   0.06872   0.06322  -0.0794   0.0320   1.0000
  17.000   1.7239   0.07199   0.06654  -0.0794   0.0300   1.0000
  17.250   1.7251   0.07500   0.06961  -0.0794   0.0286   1.0000
  17.500   1.7260   0.07811   0.07279  -0.0796   0.0273   1.0000
  17.750   1.7245   0.08160   0.07635  -0.0799   0.0260   1.0000
  18.000   1.7205   0.08553   0.08033  -0.0803   0.0246   1.0000
  18.250   1.7220   0.08869   0.08357  -0.0807   0.0238   1.0000
  18.500   1.7208   0.09227   0.08724  -0.0813   0.0228   1.0000
  18.750   1.7184   0.09609   0.09111  -0.0820   0.0219   1.0000
  19.000   1.7118   0.10066   0.09575  -0.0830   0.0210   1.0000
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