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DAE-11 AIRFOIL (dae11-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: DAE-11 AIRFOIL (dae11-il)
Reynolds number: 1,000,000
Max Cl/Cd: 165.02 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-dae11-il-1000000-n5.txt
Download as CSV file: xf-dae11-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: DAE-11 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.0770   0.08860   0.08544  -0.0736   0.6568   0.0077
  -9.000  -0.0712   0.08560   0.08244  -0.0750   0.6553   0.0080
  -8.500  -0.2731   0.02894   0.02548  -0.1159   0.6532   0.0092
  -8.250  -0.2677   0.02020   0.01583  -0.1202   0.6517   0.0094
  -8.000  -0.2437   0.01865   0.01405  -0.1208   0.6502   0.0096
  -7.750  -0.2181   0.01755   0.01278  -0.1212   0.6487   0.0097
  -7.500  -0.1917   0.01674   0.01183  -0.1214   0.6470   0.0098
  -7.250  -0.1650   0.01600   0.01095  -0.1216   0.6453   0.0099
  -7.000  -0.1380   0.01530   0.01011  -0.1219   0.6438   0.0101
  -6.750  -0.1106   0.01462   0.00932  -0.1221   0.6426   0.0102
  -6.500  -0.0831   0.01398   0.00857  -0.1223   0.6412   0.0104
  -6.250  -0.0553   0.01339   0.00787  -0.1224   0.6397   0.0106
  -6.000  -0.0275   0.01285   0.00722  -0.1226   0.6379   0.0107
  -5.750   0.0005   0.01234   0.00660  -0.1228   0.6363   0.0109
  -5.500   0.0287   0.01188   0.00605  -0.1229   0.6347   0.0111
  -5.250   0.0569   0.01148   0.00556  -0.1230   0.6329   0.0114
  -5.000   0.0854   0.01118   0.00518  -0.1232   0.6312   0.0116
  -4.750   0.1138   0.01092   0.00484  -0.1233   0.6294   0.0118
  -4.500   0.1421   0.01045   0.00431  -0.1235   0.6280   0.0122
  -4.250   0.1708   0.01017   0.00400  -0.1237   0.6265   0.0125
  -4.000   0.1996   0.00994   0.00375  -0.1239   0.6248   0.0129
  -3.750   0.2284   0.00972   0.00350  -0.1240   0.6230   0.0133
  -3.500   0.2573   0.00951   0.00326  -0.1242   0.6212   0.0137
  -3.250   0.2861   0.00933   0.00304  -0.1244   0.6193   0.0142
  -3.000   0.3149   0.00916   0.00283  -0.1246   0.6174   0.0146
  -2.750   0.3437   0.00897   0.00261  -0.1247   0.6155   0.0152
  -2.500   0.3725   0.00884   0.00245  -0.1249   0.6136   0.0160
  -2.250   0.4016   0.00870   0.00232  -0.1251   0.6120   0.0169
  -2.000   0.4306   0.00859   0.00220  -0.1254   0.6100   0.0179
  -1.750   0.4596   0.00846   0.00208  -0.1256   0.6078   0.0195
  -1.500   0.4886   0.00837   0.00198  -0.1258   0.6056   0.0213
  -1.250   0.5175   0.00828   0.00188  -0.1260   0.6033   0.0235
  -1.000   0.5463   0.00821   0.00180  -0.1262   0.6009   0.0263
  -0.750   0.5751   0.00814   0.00174  -0.1264   0.5985   0.0315
  -0.500   0.6042   0.00805   0.00169  -0.1266   0.5962   0.0409
  -0.250   0.6331   0.00796   0.00165  -0.1269   0.5934   0.0541
   0.000   0.6619   0.00787   0.00162  -0.1271   0.5904   0.0771
   0.250   0.6906   0.00776   0.00160  -0.1274   0.5875   0.1138
   0.500   0.7190   0.00764   0.00160  -0.1276   0.5846   0.1690
   0.750   0.7476   0.00746   0.00162  -0.1279   0.5820   0.2459
   1.000   0.7761   0.00729   0.00166  -0.1283   0.5789   0.3323
   1.250   0.8044   0.00714   0.00171  -0.1285   0.5755   0.4178
   1.500   0.8324   0.00701   0.00177  -0.1287   0.5719   0.5053
   1.750   0.8599   0.00684   0.00184  -0.1288   0.5684   0.6144
   2.000   0.8850   0.00646   0.00195  -0.1284   0.5646   0.7965
   2.500   0.9458   0.00626   0.00202  -0.1294   0.5556   1.0000
   2.750   0.9742   0.00633   0.00207  -0.1296   0.5514   1.0000
   3.000   1.0025   0.00642   0.00213  -0.1298   0.5464   1.0000
   3.250   1.0304   0.00653   0.00219  -0.1300   0.5410   1.0000
   3.500   1.0586   0.00662   0.00227  -0.1301   0.5360   1.0000
   3.750   1.0864   0.00672   0.00235  -0.1303   0.5298   1.0000
   4.000   1.1140   0.00685   0.00245  -0.1304   0.5239   1.0000
   4.250   1.1418   0.00696   0.00255  -0.1305   0.5175   1.0000
   4.750   1.1964   0.00725   0.00278  -0.1307   0.5038   1.0000
   5.250   1.2500   0.00758   0.00307  -0.1308   0.4874   1.0000
   5.500   1.2761   0.00779   0.00324  -0.1307   0.4784   1.0000
   5.750   1.3021   0.00800   0.00342  -0.1306   0.4679   1.0000
   6.000   1.3279   0.00822   0.00361  -0.1305   0.4576   1.0000
   6.250   1.3529   0.00848   0.00383  -0.1303   0.4465   1.0000
   6.500   1.3773   0.00878   0.00408  -0.1300   0.4340   1.0000
   6.750   1.4009   0.00910   0.00436  -0.1296   0.4203   1.0000
   7.000   1.4238   0.00946   0.00467  -0.1291   0.4058   1.0000
   7.250   1.4456   0.00986   0.00501  -0.1284   0.3901   1.0000
   7.500   1.4664   0.01030   0.00538  -0.1276   0.3743   1.0000
   7.750   1.4859   0.01077   0.00580  -0.1266   0.3577   1.0000
   8.000   1.5035   0.01130   0.00625  -0.1253   0.3403   1.0000
   8.250   1.5189   0.01188   0.00676  -0.1237   0.3229   1.0000
   8.500   1.5301   0.01255   0.00736  -0.1214   0.3051   1.0000
   8.750   1.5333   0.01329   0.00805  -0.1177   0.2897   1.0000
   9.000   1.5339   0.01433   0.00903  -0.1142   0.2744   1.0000
   9.250   1.5358   0.01558   0.01023  -0.1114   0.2587   1.0000
   9.500   1.5384   0.01698   0.01157  -0.1089   0.2428   1.0000
  10.000   1.5437   0.02004   0.01450  -0.1045   0.2104   1.0000
  10.250   1.5489   0.02148   0.01591  -0.1027   0.1983   1.0000
  10.500   1.5514   0.02313   0.01750  -0.1007   0.1833   1.0000
  10.750   1.5554   0.02472   0.01904  -0.0989   0.1708   1.0000
  11.250   1.5611   0.02814   0.02238  -0.0954   0.1450   1.0000
  11.500   1.5628   0.02999   0.02417  -0.0937   0.1316   1.0000
  11.750   1.5668   0.03170   0.02585  -0.0922   0.1210   1.0000
  12.000   1.5706   0.03348   0.02760  -0.0907   0.1113   1.0000
  12.250   1.5737   0.03539   0.02947  -0.0894   0.1003   1.0000
  12.500   1.5759   0.03745   0.03150  -0.0881   0.0899   1.0000
  12.750   1.5805   0.03932   0.03335  -0.0869   0.0819   1.0000
  13.000   1.5839   0.04139   0.03540  -0.0859   0.0733   1.0000
  13.250   1.5887   0.04335   0.03735  -0.0849   0.0657   1.0000
  13.500   1.5911   0.04560   0.03957  -0.0839   0.0582   1.0000
  13.750   1.5951   0.04773   0.04170  -0.0831   0.0519   1.0000
  14.000   1.6006   0.04977   0.04377  -0.0824   0.0477   1.0000
  14.250   1.6045   0.05200   0.04599  -0.0817   0.0429   1.0000
  14.500   1.6088   0.05424   0.04825  -0.0811   0.0386   1.0000
  14.750   1.6127   0.05654   0.05057  -0.0805   0.0348   1.0000
  15.000   1.6166   0.05892   0.05297  -0.0800   0.0316   1.0000
  15.250   1.6206   0.06131   0.05538  -0.0796   0.0288   1.0000
  15.500   1.6241   0.06380   0.05792  -0.0793   0.0261   1.0000
  15.750   1.6274   0.06635   0.06049  -0.0790   0.0238   1.0000
  16.000   1.6309   0.06894   0.06313  -0.0788   0.0219   1.0000
  16.250   1.6334   0.07167   0.06589  -0.0787   0.0200   1.0000
  16.500   1.6367   0.07436   0.06864  -0.0786   0.0187   1.0000
  16.750   1.6393   0.07713   0.07146  -0.0786   0.0172   1.0000
  17.000   1.6402   0.08023   0.07461  -0.0787   0.0159   1.0000
  17.250   1.6434   0.08302   0.07746  -0.0789   0.0148   1.0000
  17.500   1.6443   0.08619   0.08070  -0.0791   0.0138   1.0000
  17.750   1.6447   0.08945   0.08400  -0.0795   0.0128   1.0000
  18.000   1.6463   0.09258   0.08721  -0.0799   0.0121   1.0000
  18.250   1.6472   0.09585   0.09055  -0.0804   0.0114   1.0000
  18.500   1.6469   0.09933   0.09408  -0.0810   0.0107   1.0000
  18.750   1.6455   0.10304   0.09786  -0.0818   0.0100   1.0000
  19.000   1.6465   0.10636   0.10126  -0.0825   0.0096   1.0000
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