DORNIER A-5 AIRFOIL (doa5-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: DORNIER A-5 AIRFOIL (doa5-il) Reynolds number: 500,000 Max Cl/Cd: 75.72 at α=3.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-doa5-il-500000.txt Download as CSV file: xf-doa5-il-500000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.250 -0.7250 0.07832 0.07534 -0.0731 1.0000 0.0304
-14.000 -0.7555 0.07232 0.06925 -0.0743 1.0000 0.0302
-13.750 -0.7934 0.06644 0.06321 -0.0747 1.0000 0.0302
-13.500 -0.8244 0.06064 0.05721 -0.0760 0.9993 0.0301
-13.250 -0.8469 0.05444 0.05072 -0.0794 0.9967 0.0300
-13.000 -0.8655 0.04948 0.04538 -0.0823 0.9938 0.0303
-12.750 -0.8752 0.04607 0.04168 -0.0831 0.9892 0.0304
-12.500 -0.8828 0.04181 0.03708 -0.0844 0.9854 0.0307
-12.250 -0.8714 0.03853 0.03360 -0.0860 0.9837 0.0310
-12.000 -0.8639 0.03672 0.03169 -0.0852 0.9780 0.0313
-11.750 -0.8453 0.03522 0.03010 -0.0861 0.9751 0.0317
-11.500 -0.8215 0.03389 0.02868 -0.0876 0.9734 0.0320
-11.250 -0.8044 0.03283 0.02756 -0.0872 0.9689 0.0325
-11.000 -0.7837 0.03142 0.02602 -0.0877 0.9651 0.0331
-10.750 -0.7582 0.02996 0.02440 -0.0889 0.9629 0.0338
-10.500 -0.7305 0.02839 0.02263 -0.0903 0.9615 0.0343
-10.250 -0.7008 0.02697 0.02103 -0.0918 0.9606 0.0347
-10.000 -0.6871 0.02607 0.02000 -0.0899 0.9538 0.0351
-9.750 -0.6603 0.02518 0.01896 -0.0907 0.9512 0.0354
-9.500 -0.6288 0.02360 0.01733 -0.0917 0.9506 0.0361
-9.250 -0.5973 0.02271 0.01647 -0.0930 0.9495 0.0369
-9.000 -0.5652 0.02196 0.01571 -0.0945 0.9486 0.0376
-8.750 -0.5324 0.02120 0.01491 -0.0960 0.9478 0.0384
-8.500 -0.5173 0.02064 0.01432 -0.0940 0.9413 0.0388
-8.250 -0.4891 0.01994 0.01358 -0.0945 0.9387 0.0395
-8.000 -0.4576 0.01925 0.01285 -0.0956 0.9371 0.0403
-7.750 -0.4250 0.01860 0.01215 -0.0971 0.9359 0.0410
-7.500 -0.3947 0.01764 0.01120 -0.0982 0.9348 0.0422
-7.250 -0.3624 0.01693 0.01051 -0.1000 0.9338 0.0433
-7.000 -0.3520 0.01655 0.01013 -0.0971 0.9266 0.0442
-6.750 -0.3237 0.01599 0.00955 -0.0979 0.9241 0.0454
-6.500 -0.2920 0.01544 0.00897 -0.0993 0.9224 0.0468
-6.250 -0.2594 0.01475 0.00826 -0.1012 0.9210 0.0484
-6.000 -0.2254 0.01414 0.00767 -0.1032 0.9196 0.0508
-5.750 -0.1895 0.01368 0.00721 -0.1054 0.9183 0.0537
-5.500 -0.1826 0.01345 0.00696 -0.1015 0.9103 0.0558
-5.250 -0.1516 0.01302 0.00656 -0.1027 0.9078 0.0605
-5.000 -0.1185 0.01254 0.00610 -0.1043 0.9057 0.0671
-4.750 -0.0831 0.01202 0.00560 -0.1065 0.9036 0.0782
-4.500 -0.0696 0.01176 0.00537 -0.1038 0.8967 0.0882
-4.250 -0.0414 0.01129 0.00499 -0.1043 0.8919 0.1096
-4.000 -0.0088 0.01057 0.00452 -0.1060 0.8882 0.1727
-3.750 -0.0085 0.00877 0.00375 -0.1025 0.8805 0.4383
-3.500 0.0165 0.00829 0.00357 -0.1022 0.8755 0.5307
-3.250 0.0503 0.00810 0.00343 -0.1034 0.8718 0.5680
-3.000 0.0735 0.00806 0.00342 -0.1024 0.8664 0.5868
-2.750 0.1002 0.00802 0.00339 -0.1020 0.8617 0.6018
-2.500 0.1316 0.00799 0.00335 -0.1027 0.8578 0.6163
-2.250 0.1648 0.00799 0.00334 -0.1037 0.8540 0.6304
-2.000 0.1885 0.00803 0.00336 -0.1027 0.8484 0.6415
-1.750 0.2184 0.00804 0.00338 -0.1030 0.8436 0.6477
-1.500 0.2542 0.00805 0.00334 -0.1046 0.8396 0.6545
-1.250 0.2795 0.00810 0.00339 -0.1040 0.8342 0.6604
-1.000 0.3074 0.00815 0.00343 -0.1039 0.8285 0.6647
-0.750 0.3428 0.00819 0.00341 -0.1054 0.8227 0.6693
-0.500 0.3659 0.00823 0.00341 -0.1043 0.8154 0.6747
-0.250 0.3944 0.00829 0.00347 -0.1043 0.8082 0.6786
0.000 0.4229 0.00839 0.00357 -0.1043 0.8018 0.6830
0.250 0.4463 0.00844 0.00363 -0.1032 0.7944 0.6881
0.500 0.4764 0.00851 0.00365 -0.1036 0.7880 0.6931
0.750 0.4974 0.00858 0.00377 -0.1020 0.7799 0.6964
1.000 0.5231 0.00863 0.00382 -0.1013 0.7717 0.6998
1.250 0.5453 0.00866 0.00386 -0.1000 0.7629 0.7034
1.500 0.5700 0.00866 0.00382 -0.0993 0.7542 0.7074
1.750 0.5913 0.00866 0.00385 -0.0978 0.7436 0.7101
2.000 0.6126 0.00870 0.00388 -0.0963 0.7299 0.7124
2.250 0.6340 0.00877 0.00392 -0.0947 0.7154 0.7149
2.500 0.6546 0.00885 0.00396 -0.0931 0.6993 0.7179
2.750 0.6718 0.00894 0.00398 -0.0907 0.6760 0.7215
3.000 0.6869 0.00909 0.00398 -0.0880 0.6519 0.7253
3.250 0.7012 0.00926 0.00408 -0.0850 0.6252 0.7273
3.500 0.7123 0.00952 0.00423 -0.0814 0.5908 0.7296
3.750 0.7204 0.00989 0.00443 -0.0773 0.5546 0.7323
4.000 0.7287 0.01032 0.00469 -0.0733 0.5108 0.7355
4.250 0.7297 0.01099 0.00502 -0.0681 0.4470 0.7394
4.500 0.7367 0.01157 0.00537 -0.0642 0.4037 0.7425
4.750 0.7508 0.01198 0.00568 -0.0616 0.3823 0.7446
5.000 0.7674 0.01233 0.00598 -0.0595 0.3636 0.7470
5.250 0.7847 0.01266 0.00626 -0.0576 0.3470 0.7498
5.500 0.8023 0.01300 0.00653 -0.0558 0.3323 0.7532
5.750 0.8202 0.01336 0.00682 -0.0542 0.3170 0.7569
6.000 0.8379 0.01364 0.00708 -0.0524 0.3008 0.7595
6.250 0.8548 0.01397 0.00736 -0.0505 0.2801 0.7619
6.750 0.8810 0.01504 0.00810 -0.0457 0.2091 0.7679
7.000 0.8951 0.01558 0.00853 -0.0436 0.1916 0.7710
7.250 0.9110 0.01605 0.00894 -0.0418 0.1802 0.7737
7.500 0.9260 0.01648 0.00934 -0.0398 0.1707 0.7758
7.750 0.9429 0.01686 0.00974 -0.0381 0.1638 0.7780
8.000 0.9582 0.01734 0.01019 -0.0363 0.1565 0.7805
8.250 0.9748 0.01778 0.01065 -0.0347 0.1504 0.7831
8.500 0.9920 0.01821 0.01109 -0.0332 0.1441 0.7858
8.750 1.0057 0.01886 0.01168 -0.0313 0.1369 0.7884
9.000 1.0255 0.01908 0.01197 -0.0302 0.1313 0.7907
9.250 1.0411 0.01954 0.01242 -0.0286 0.1246 0.7933
9.500 1.0581 0.01996 0.01289 -0.0271 0.1195 0.7960
9.750 1.0756 0.02038 0.01331 -0.0258 0.1137 0.7990
10.000 1.0904 0.02097 0.01387 -0.0242 0.1084 0.8016
10.250 1.1067 0.02151 0.01442 -0.0229 0.1045 0.8036
10.500 1.1204 0.02213 0.01503 -0.0212 0.1003 0.8056
10.750 1.1310 0.02291 0.01582 -0.0192 0.0965 0.8076
11.000 1.1468 0.02345 0.01644 -0.0179 0.0937 0.8097
11.250 1.1603 0.02414 0.01717 -0.0163 0.0908 0.8120
11.500 1.1712 0.02501 0.01805 -0.0145 0.0877 0.8145
11.750 1.1795 0.02609 0.01914 -0.0125 0.0848 0.8170
12.000 1.1968 0.02663 0.01976 -0.0116 0.0827 0.8192
12.250 1.2115 0.02729 0.02048 -0.0104 0.0802 0.8212
12.500 1.2248 0.02804 0.02129 -0.0092 0.0778 0.8232
12.750 1.2335 0.02915 0.02240 -0.0075 0.0752 0.8251
13.000 1.2465 0.02999 0.02332 -0.0063 0.0730 0.8271
13.250 1.2616 0.03070 0.02411 -0.0054 0.0708 0.8290
13.500 1.2746 0.03157 0.02501 -0.0043 0.0683 0.8312
13.750 1.2834 0.03278 0.02621 -0.0030 0.0658 0.8333
14.000 1.2934 0.03394 0.02745 -0.0018 0.0638 0.8352
14.250 1.3059 0.03492 0.02850 -0.0009 0.0616 0.8373
14.500 1.3156 0.03612 0.02975 0.0001 0.0594 0.8392
14.750 1.3200 0.03778 0.03143 0.0014 0.0572 0.8411
15.000 1.3289 0.03915 0.03290 0.0023 0.0554 0.8431
15.250 1.3388 0.04048 0.03432 0.0031 0.0535 0.8452
15.500 1.3465 0.04204 0.03594 0.0038 0.0518 0.8472
15.750 1.3501 0.04399 0.03791 0.0046 0.0500 0.8492
16.000 1.3542 0.04598 0.03998 0.0053 0.0483 0.8513
16.250 1.3628 0.04760 0.04172 0.0057 0.0467 0.8536
16.500 1.3688 0.04951 0.04372 0.0061 0.0451 0.8563
16.750 1.3728 0.05176 0.04602 0.0062 0.0437 0.8592
17.000 1.3707 0.05469 0.04901 0.0063 0.0423 0.8623
17.250 1.3770 0.05684 0.05130 0.0062 0.0411 0.8654
17.500 1.3821 0.05922 0.05377 0.0059 0.0397 0.8680
17.750 1.3842 0.06206 0.05671 0.0053 0.0385 0.8708
18.000 1.3821 0.06550 0.06020 0.0045 0.0373 0.8738
18.250 1.3780 0.06928 0.06408 0.0035 0.0363 0.8768
18.500 1.3792 0.07260 0.06755 0.0023 0.0353 0.8804
18.750 1.3781 0.07636 0.07144 0.0008 0.0344 0.8842
19.000 1.3764 0.08049 0.07569 -0.0012 0.0334 0.8888
19.250 1.3715 0.08519 0.08049 -0.0036 0.0327 0.8942
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