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DAE-21 AIRFOIL (dae21-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: DAE-21 AIRFOIL (dae21-il)
Reynolds number: 500,000
Max Cl/Cd: 130.38 at α=5.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-dae21-il-500000-n5.txt
Download as CSV file: xf-dae21-il-500000-n5.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 =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.0593   0.08943   0.08585  -0.0749   0.7204   0.0147
  -8.500  -0.0545   0.08629   0.08271  -0.0765   0.7180   0.0147
  -8.250  -0.0480   0.08343   0.07985  -0.0778   0.7158   0.0147
  -8.000  -0.0414   0.08060   0.07700  -0.0790   0.7137   0.0147
  -7.500  -0.0230   0.07595   0.07240  -0.0804   0.7091   0.0145
  -7.250  -0.0148   0.07375   0.07021  -0.0811   0.7065   0.0137
  -7.000  -0.0112   0.07099   0.06747  -0.0821   0.7037   0.0134
  -6.750  -0.0100   0.06838   0.06487  -0.0829   0.7011   0.0133
  -6.500  -0.0029   0.06549   0.06198  -0.0853   0.6988   0.0135
  -6.250   0.0062   0.06214   0.05862  -0.0888   0.6964   0.0140
  -6.000   0.0183   0.05848   0.05497  -0.0929   0.6938   0.0139
  -5.750   0.0331   0.05444   0.05092  -0.0978   0.6911   0.0134
  -5.500   0.0512   0.04873   0.04515  -0.1050   0.6884   0.0130
  -5.250   0.0751   0.04056   0.03681  -0.1148   0.6858   0.0127
  -5.000   0.1031   0.03070   0.02653  -0.1236   0.6836   0.0129
  -4.750   0.1285   0.01764   0.01200  -0.1294   0.6817   0.0139
  -4.500   0.1563   0.01574   0.00960  -0.1299   0.6794   0.0146
  -4.250   0.1844   0.01469   0.00834  -0.1302   0.6768   0.0150
  -4.000   0.2126   0.01406   0.00761  -0.1304   0.6740   0.0153
  -3.750   0.2410   0.01352   0.00697  -0.1306   0.6713   0.0157
  -3.500   0.2694   0.01300   0.00633  -0.1307   0.6686   0.0162
  -3.250   0.2978   0.01252   0.00572  -0.1308   0.6661   0.0167
  -3.000   0.3263   0.01208   0.00517  -0.1309   0.6636   0.0172
  -2.750   0.3549   0.01171   0.00472  -0.1310   0.6607   0.0178
  -2.500   0.3834   0.01133   0.00433  -0.1312   0.6577   0.0184
  -2.250   0.4120   0.01111   0.00411  -0.1313   0.6546   0.0193
  -2.000   0.4406   0.01090   0.00384  -0.1314   0.6517   0.0204
  -1.750   0.4692   0.01068   0.00354  -0.1315   0.6490   0.0213
  -1.500   0.4979   0.01043   0.00332  -0.1317   0.6460   0.0222
  -1.250   0.5266   0.01026   0.00314  -0.1318   0.6426   0.0235
  -1.000   0.5553   0.01012   0.00297  -0.1319   0.6392   0.0249
  -0.750   0.5839   0.00998   0.00282  -0.1320   0.6359   0.0274
  -0.250   0.6412   0.00976   0.00259  -0.1323   0.6293   0.0347
   0.000   0.6698   0.00966   0.00252  -0.1324   0.6255   0.0439
   0.250   0.6983   0.00954   0.00246  -0.1325   0.6216   0.0666
   0.500   0.7265   0.00941   0.00243  -0.1327   0.6182   0.1110
   0.750   0.7548   0.00921   0.00245  -0.1329   0.6143   0.1939
   1.000   0.7829   0.00896   0.00251  -0.1332   0.6101   0.3134
   1.250   0.8104   0.00870   0.00260  -0.1333   0.6058   0.4579
   1.500   0.8369   0.00839   0.00269  -0.1332   0.6018   0.6237
   1.750   0.8654   0.00771   0.00273  -0.1331   0.5973   1.0000
   2.000   0.8936   0.00779   0.00276  -0.1332   0.5923   1.0000
   2.250   0.9216   0.00789   0.00279  -0.1332   0.5874   1.0000
   2.500   0.9496   0.00798   0.00284  -0.1333   0.5823   1.0000
   2.750   0.9776   0.00807   0.00290  -0.1333   0.5765   1.0000
   3.000   1.0051   0.00819   0.00296  -0.1333   0.5708   1.0000
   3.250   1.0329   0.00829   0.00304  -0.1333   0.5647   1.0000
   3.500   1.0603   0.00842   0.00313  -0.1333   0.5580   1.0000
   3.750   1.0875   0.00855   0.00323  -0.1333   0.5513   1.0000
   4.000   1.1146   0.00868   0.00334  -0.1332   0.5436   1.0000
   4.250   1.1415   0.00884   0.00345  -0.1331   0.5361   1.0000
   4.500   1.1681   0.00900   0.00359  -0.1330   0.5277   1.0000
   4.750   1.1945   0.00917   0.00374  -0.1329   0.5195   1.0000
   5.000   1.2205   0.00937   0.00390  -0.1327   0.5102   1.0000
   5.250   1.2464   0.00956   0.00407  -0.1325   0.5010   1.0000
   5.500   1.2715   0.00980   0.00428  -0.1321   0.4911   1.0000
   5.750   1.2964   0.01004   0.00449  -0.1318   0.4799   1.0000
   6.000   1.3208   0.01031   0.00472  -0.1314   0.4684   1.0000
   6.250   1.3444   0.01061   0.00498  -0.1309   0.4562   1.0000
   6.500   1.3671   0.01095   0.00528  -0.1302   0.4433   1.0000
   7.000   1.4101   0.01171   0.00595  -0.1286   0.4152   1.0000
   7.250   1.4299   0.01215   0.00634  -0.1275   0.3999   1.0000
   7.500   1.4478   0.01265   0.00678  -0.1262   0.3836   1.0000
   7.750   1.4640   0.01319   0.00726  -0.1246   0.3675   1.0000
   8.000   1.4775   0.01379   0.00780  -0.1226   0.3510   1.0000
   8.250   1.4857   0.01444   0.00841  -0.1196   0.3355   1.0000
   8.500   1.4920   0.01524   0.00916  -0.1167   0.3201   1.0000
   8.750   1.4996   0.01613   0.01000  -0.1142   0.3056   1.0000
   9.000   1.5071   0.01713   0.01095  -0.1120   0.2907   1.0000
   9.250   1.5146   0.01821   0.01199  -0.1098   0.2759   1.0000
   9.500   1.5214   0.01939   0.01313  -0.1077   0.2608   1.0000
   9.750   1.5280   0.02065   0.01433  -0.1058   0.2458   1.0000
  10.000   1.5342   0.02198   0.01561  -0.1038   0.2309   1.0000
  10.250   1.5401   0.02338   0.01696  -0.1019   0.2164   1.0000
  10.500   1.5462   0.02480   0.01834  -0.1002   0.2025   1.0000
  10.750   1.5531   0.02620   0.01971  -0.0985   0.1906   1.0000
  11.000   1.5585   0.02774   0.02122  -0.0969   0.1778   1.0000
  11.250   1.5641   0.02931   0.02275  -0.0953   0.1660   1.0000
  11.500   1.5686   0.03100   0.02441  -0.0937   0.1537   1.0000
  11.750   1.5723   0.03279   0.02616  -0.0922   0.1418   1.0000
  12.000   1.5771   0.03452   0.02788  -0.0908   0.1314   1.0000
  12.250   1.5821   0.03632   0.02966  -0.0895   0.1214   1.0000
  12.500   1.5872   0.03816   0.03149  -0.0883   0.1124   1.0000
  12.750   1.5911   0.04018   0.03349  -0.0871   0.1036   1.0000
  13.000   1.5954   0.04219   0.03550  -0.0861   0.0953   1.0000
  13.250   1.6008   0.04416   0.03749  -0.0852   0.0883   1.0000
  13.500   1.6042   0.04638   0.03971  -0.0842   0.0817   1.0000
  13.750   1.6091   0.04850   0.04184  -0.0835   0.0752   1.0000
  14.000   1.6129   0.05077   0.04414  -0.0827   0.0700   1.0000
  14.250   1.6169   0.05307   0.04647  -0.0821   0.0648   1.0000
  14.500   1.6208   0.05544   0.04887  -0.0815   0.0605   1.0000
  14.750   1.6238   0.05797   0.05142  -0.0810   0.0559   1.0000
  15.000   1.6276   0.06044   0.05394  -0.0806   0.0525   1.0000
  15.250   1.6303   0.06308   0.05663  -0.0803   0.0491   1.0000
  15.500   1.6328   0.06579   0.05939  -0.0800   0.0462   1.0000
  15.750   1.6356   0.06853   0.06220  -0.0799   0.0433   1.0000
  16.000   1.6365   0.07156   0.06527  -0.0798   0.0407   1.0000
  16.250   1.6389   0.07444   0.06822  -0.0798   0.0384   1.0000
  16.500   1.6397   0.07756   0.07141  -0.0799   0.0361   1.0000
  16.750   1.6394   0.08090   0.07481  -0.0800   0.0342   1.0000
  17.000   1.6407   0.08407   0.07807  -0.0803   0.0324   1.0000
  17.250   1.6407   0.08747   0.08154  -0.0807   0.0309   1.0000
  17.500   1.6390   0.09114   0.08527  -0.0812   0.0294   1.0000
  17.750   1.6385   0.09471   0.08893  -0.0818   0.0282   1.0000
  18.000   1.6378   0.09835   0.09267  -0.0825   0.0270   1.0000
  18.250   1.6361   0.10216   0.09657  -0.0833   0.0258   1.0000
  18.500   1.6321   0.10640   0.10088  -0.0843   0.0248   1.0000
  18.750   1.6307   0.11024   0.10482  -0.0853   0.0239   1.0000
  19.000   1.6290   0.11417   0.10885  -0.0865   0.0229   1.0000
  19.250   1.6260   0.11834   0.11311  -0.0878   0.0220   1.0000
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