DORNIER A-5 AIRFOIL (doa5-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: DORNIER A-5 AIRFOIL (doa5-il) Reynolds number: 500,000 Max Cl/Cd: 59.01 at α=1.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-doa5-il-500000-n5.txt Download as CSV file: xf-doa5-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: DORNIER A-5 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
------ -------- --------- --------- -------- -------- --------
-17.500 -0.8171 0.09575 0.09259 -0.0706 1.0000 0.0214
-17.250 -0.8822 0.08023 0.07672 -0.0794 1.0000 0.0213
-17.000 -0.9082 0.07336 0.06967 -0.0823 1.0000 0.0214
-16.750 -0.9305 0.06761 0.06374 -0.0842 1.0000 0.0214
-16.500 -0.9459 0.06306 0.05903 -0.0853 0.9999 0.0216
-16.250 -0.9506 0.05866 0.05446 -0.0880 0.9992 0.0218
-16.000 -0.9522 0.05480 0.05042 -0.0904 0.9982 0.0220
-15.750 -0.9502 0.05146 0.04690 -0.0925 0.9970 0.0224
-15.500 -0.9464 0.04854 0.04382 -0.0942 0.9956 0.0225
-15.250 -0.9414 0.04589 0.04098 -0.0957 0.9942 0.0228
-15.000 -0.9346 0.04361 0.03855 -0.0968 0.9929 0.0229
-14.750 -0.9286 0.04143 0.03626 -0.0971 0.9912 0.0231
-14.500 -0.9197 0.03953 0.03428 -0.0976 0.9894 0.0233
-14.250 -0.9072 0.03797 0.03265 -0.0982 0.9876 0.0236
-14.000 -0.8933 0.03645 0.03107 -0.0989 0.9860 0.0238
-13.750 -0.8767 0.03521 0.02978 -0.0999 0.9846 0.0241
-13.500 -0.8591 0.03391 0.02841 -0.1008 0.9835 0.0243
-13.250 -0.8465 0.03273 0.02716 -0.1005 0.9803 0.0246
-13.000 -0.8305 0.03161 0.02596 -0.1007 0.9778 0.0249
-12.750 -0.8122 0.03048 0.02475 -0.1012 0.9759 0.0252
-12.500 -0.7921 0.02937 0.02356 -0.1019 0.9744 0.0255
-12.250 -0.7703 0.02836 0.02245 -0.1028 0.9732 0.0259
-12.000 -0.7472 0.02737 0.02138 -0.1037 0.9723 0.0261
-11.750 -0.7335 0.02655 0.02048 -0.1026 0.9681 0.0265
-11.500 -0.7120 0.02574 0.01958 -0.1029 0.9657 0.0268
-11.250 -0.6880 0.02493 0.01869 -0.1037 0.9640 0.0270
-11.000 -0.6640 0.02396 0.01770 -0.1044 0.9626 0.0274
-10.750 -0.6381 0.02310 0.01682 -0.1055 0.9615 0.0278
-10.500 -0.6204 0.02240 0.01610 -0.1048 0.9573 0.0281
-10.250 -0.6018 0.02174 0.01541 -0.1043 0.9531 0.0284
-10.000 -0.5773 0.02105 0.01469 -0.1049 0.9508 0.0288
-9.750 -0.5506 0.02037 0.01398 -0.1059 0.9491 0.0292
-9.500 -0.5396 0.01984 0.01343 -0.1037 0.9421 0.0295
-9.250 -0.5176 0.01922 0.01277 -0.1037 0.9384 0.0300
-9.000 -0.4911 0.01859 0.01210 -0.1046 0.9360 0.0304
-8.750 -0.4763 0.01808 0.01155 -0.1030 0.9298 0.0310
-8.500 -0.4520 0.01752 0.01094 -0.1034 0.9262 0.0315
-8.250 -0.4236 0.01681 0.01021 -0.1048 0.9236 0.0319
-8.000 -0.3973 0.01613 0.00952 -0.1058 0.9197 0.0326
-7.750 -0.3760 0.01556 0.00893 -0.1056 0.9136 0.0330
-7.500 -0.3441 0.01500 0.00834 -0.1074 0.9101 0.0338
-7.250 -0.3103 0.01449 0.00779 -0.1096 0.9074 0.0347
-7.000 -0.2957 0.01413 0.00741 -0.1077 0.9000 0.0354
-6.750 -0.2690 0.01375 0.00698 -0.1081 0.8953 0.0363
-6.500 -0.2386 0.01334 0.00653 -0.1094 0.8919 0.0373
-6.250 -0.2275 0.01304 0.00624 -0.1065 0.8833 0.0385
-6.000 -0.2023 0.01271 0.00590 -0.1065 0.8782 0.0402
-5.750 -0.1808 0.01244 0.00561 -0.1056 0.8724 0.0420
-5.500 -0.1590 0.01215 0.00532 -0.1048 0.8659 0.0442
-5.250 -0.1316 0.01185 0.00501 -0.1051 0.8608 0.0475
-5.000 -0.1079 0.01159 0.00476 -0.1046 0.8541 0.0517
-4.750 -0.0788 0.01133 0.00449 -0.1052 0.8472 0.0586
-4.500 -0.0517 0.01114 0.00428 -0.1053 0.8410 0.0660
-4.250 -0.0242 0.01092 0.00404 -0.1055 0.8341 0.0730
-4.000 0.0055 0.01073 0.00381 -0.1062 0.8285 0.0801
-3.750 0.0291 0.01053 0.00366 -0.1056 0.8236 0.0892
-3.500 0.0542 0.01029 0.00348 -0.1054 0.8192 0.1105
-3.250 0.0803 0.00997 0.00329 -0.1055 0.8144 0.1508
-3.000 0.1065 0.00974 0.00312 -0.1055 0.8097 0.1811
-2.750 0.1152 0.00811 0.00248 -0.1034 0.8032 0.4582
-2.500 0.1402 0.00787 0.00240 -0.1030 0.7972 0.5158
-2.250 0.1662 0.00777 0.00238 -0.1027 0.7908 0.5469
-2.000 0.1899 0.00771 0.00237 -0.1018 0.7839 0.5690
-1.750 0.2161 0.00769 0.00236 -0.1014 0.7765 0.5845
-1.500 0.2403 0.00767 0.00235 -0.1006 0.7687 0.5940
-1.250 0.2653 0.00767 0.00233 -0.1000 0.7606 0.6006
-1.000 0.2909 0.00767 0.00231 -0.0994 0.7534 0.6081
-0.750 0.3154 0.00766 0.00231 -0.0987 0.7442 0.6158
-0.500 0.3402 0.00768 0.00227 -0.0980 0.7339 0.6218
-0.250 0.3640 0.00770 0.00226 -0.0970 0.7220 0.6269
0.000 0.3877 0.00773 0.00227 -0.0961 0.7099 0.6324
0.250 0.4108 0.00778 0.00227 -0.0950 0.6954 0.6379
0.500 0.4317 0.00786 0.00229 -0.0935 0.6751 0.6427
0.750 0.4516 0.00798 0.00235 -0.0917 0.6567 0.6492
1.000 0.4704 0.00812 0.00240 -0.0898 0.6378 0.6561
1.250 0.4875 0.00827 0.00248 -0.0874 0.6138 0.6610
1.500 0.5016 0.00850 0.00258 -0.0845 0.5819 0.6654
1.750 0.5140 0.00879 0.00270 -0.0813 0.5484 0.6695
2.000 0.5241 0.00918 0.00286 -0.0777 0.4987 0.6739
2.250 0.5300 0.00974 0.00315 -0.0733 0.4369 0.6768
2.500 0.5431 0.01018 0.00342 -0.0705 0.3968 0.6808
2.750 0.5618 0.01047 0.00362 -0.0687 0.3780 0.6855
3.000 0.5814 0.01073 0.00380 -0.0672 0.3601 0.6902
3.250 0.6002 0.01102 0.00403 -0.0655 0.3422 0.6932
3.500 0.6194 0.01131 0.00426 -0.0639 0.3265 0.6966
3.750 0.6394 0.01156 0.00447 -0.0625 0.3157 0.6998
4.000 0.6609 0.01176 0.00464 -0.0614 0.3037 0.7031
4.250 0.6820 0.01198 0.00482 -0.0602 0.2933 0.7064
4.500 0.7014 0.01226 0.00505 -0.0587 0.2783 0.7089
4.750 0.7195 0.01259 0.00531 -0.0570 0.2518 0.7113
5.000 0.7328 0.01315 0.00564 -0.0545 0.2071 0.7141
5.250 0.7502 0.01355 0.00595 -0.0528 0.1889 0.7172
5.500 0.7686 0.01392 0.00626 -0.0512 0.1762 0.7207
5.750 0.7876 0.01426 0.00654 -0.0498 0.1666 0.7239
6.000 0.8066 0.01458 0.00687 -0.0484 0.1603 0.7260
6.250 0.8257 0.01492 0.00720 -0.0470 0.1550 0.7282
6.500 0.8446 0.01526 0.00754 -0.0456 0.1508 0.7306
6.750 0.8642 0.01557 0.00787 -0.0443 0.1470 0.7334
7.000 0.8844 0.01586 0.00818 -0.0432 0.1436 0.7362
7.250 0.9035 0.01621 0.00852 -0.0419 0.1391 0.7388
7.500 0.9216 0.01661 0.00890 -0.0405 0.1345 0.7411
7.750 0.9414 0.01690 0.00925 -0.0393 0.1308 0.7429
8.000 0.9605 0.01724 0.00962 -0.0380 0.1256 0.7447
8.250 0.9785 0.01764 0.01001 -0.0367 0.1195 0.7466
8.500 0.9973 0.01800 0.01038 -0.0354 0.1129 0.7489
8.750 1.0145 0.01847 0.01081 -0.0340 0.1058 0.7513
9.000 1.0308 0.01898 0.01126 -0.0325 0.0999 0.7534
9.250 1.0477 0.01947 0.01175 -0.0311 0.0960 0.7553
9.500 1.0647 0.01995 0.01226 -0.0298 0.0933 0.7569
9.750 1.0805 0.02047 0.01281 -0.0283 0.0908 0.7583
10.000 1.0950 0.02108 0.01343 -0.0266 0.0877 0.7598
10.250 1.1111 0.02161 0.01400 -0.0252 0.0855 0.7614
10.500 1.1281 0.02210 0.01456 -0.0240 0.0835 0.7632
10.750 1.1441 0.02265 0.01516 -0.0226 0.0809 0.7653
11.000 1.1590 0.02328 0.01582 -0.0212 0.0785 0.7675
11.250 1.1731 0.02397 0.01653 -0.0198 0.0762 0.7697
11.500 1.1892 0.02456 0.01716 -0.0186 0.0736 0.7716
11.750 1.2038 0.02522 0.01786 -0.0173 0.0713 0.7733
12.000 1.2177 0.02593 0.01860 -0.0159 0.0690 0.7749
12.250 1.2307 0.02670 0.01941 -0.0145 0.0669 0.7764
12.500 1.2447 0.02745 0.02022 -0.0132 0.0652 0.7780
12.750 1.2577 0.02827 0.02108 -0.0120 0.0632 0.7795
13.000 1.2698 0.02917 0.02200 -0.0107 0.0611 0.7810
13.250 1.2803 0.03020 0.02305 -0.0093 0.0588 0.7823
13.500 1.2934 0.03107 0.02400 -0.0082 0.0573 0.7837
13.750 1.3054 0.03204 0.02503 -0.0070 0.0554 0.7849
14.000 1.3158 0.03314 0.02617 -0.0058 0.0535 0.7861
14.250 1.3251 0.03436 0.02742 -0.0046 0.0519 0.7873
14.500 1.3346 0.03558 0.02870 -0.0035 0.0503 0.7885
14.750 1.3459 0.03667 0.02989 -0.0026 0.0488 0.7899
15.000 1.3555 0.03792 0.03122 -0.0016 0.0469 0.7913
15.250 1.3641 0.03930 0.03265 -0.0007 0.0452 0.7927
15.500 1.3710 0.04085 0.03425 0.0003 0.0436 0.7941
15.750 1.3797 0.04230 0.03579 0.0010 0.0422 0.7954
16.000 1.3869 0.04391 0.03747 0.0017 0.0405 0.7966
16.250 1.3929 0.04569 0.03931 0.0024 0.0391 0.7978
16.500 1.3976 0.04765 0.04132 0.0029 0.0377 0.7989
16.750 1.4029 0.04961 0.04336 0.0034 0.0364 0.8000
17.000 1.4070 0.05175 0.04558 0.0037 0.0350 0.8010
17.250 1.4098 0.05409 0.04798 0.0039 0.0339 0.8021
17.500 1.4102 0.05675 0.05071 0.0040 0.0328 0.8032
17.750 1.4121 0.05934 0.05340 0.0039 0.0319 0.8043
18.000 1.4131 0.06211 0.05628 0.0036 0.0309 0.8055
18.250 1.4125 0.06515 0.05943 0.0032 0.0301 0.8070
18.500 1.4102 0.06849 0.06286 0.0026 0.0292 0.8083
18.750 1.4058 0.07223 0.06670 0.0016 0.0284 0.8095
19.000 1.4002 0.07629 0.07086 0.0004 0.0276 0.8105
19.250 1.3962 0.08026 0.07496 -0.0010 0.0271 0.8116
|
Polar data table (+)
Polar graphs
<< Back to DORNIER A-5 AIRFOIL (doa5-il)