DORNIER A-5 AIRFOIL (doa5-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: DORNIER A-5 AIRFOIL (doa5-il) Reynolds number: 200,000 Max Cl/Cd: 49.24 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-doa5-il-200000-n5.txt Download as CSV file: xf-doa5-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.000 -0.6821 0.08107 0.07662 -0.0736 1.0000 0.0314
-13.750 -0.7274 0.07301 0.06837 -0.0762 1.0000 0.0313
-13.500 -0.7669 0.06690 0.06205 -0.0767 1.0000 0.0313
-13.250 -0.7974 0.06170 0.05661 -0.0771 0.9993 0.0313
-13.000 -0.8206 0.05570 0.05021 -0.0799 0.9961 0.0315
-12.750 -0.8293 0.05164 0.04586 -0.0815 0.9930 0.0317
-12.500 -0.8265 0.04904 0.04312 -0.0821 0.9895 0.0319
-12.250 -0.8189 0.04681 0.04076 -0.0830 0.9861 0.0322
-12.000 -0.8077 0.04470 0.03848 -0.0843 0.9834 0.0325
-11.750 -0.8015 0.04288 0.03653 -0.0840 0.9783 0.0328
-11.500 -0.7894 0.04126 0.03477 -0.0845 0.9745 0.0333
-11.250 -0.7768 0.03964 0.03299 -0.0848 0.9708 0.0338
-11.000 -0.7681 0.03814 0.03132 -0.0840 0.9650 0.0344
-10.750 -0.7501 0.03636 0.02928 -0.0845 0.9619 0.0350
-10.500 -0.7358 0.03476 0.02746 -0.0838 0.9571 0.0355
-10.250 -0.7179 0.03325 0.02573 -0.0834 0.9526 0.0360
-10.000 -0.6937 0.03182 0.02405 -0.0839 0.9501 0.0365
-9.750 -0.6662 0.03054 0.02262 -0.0848 0.9486 0.0370
-9.500 -0.6537 0.02974 0.02181 -0.0827 0.9421 0.0375
-9.250 -0.6297 0.02891 0.02097 -0.0829 0.9391 0.0382
-9.000 -0.6026 0.02807 0.02008 -0.0836 0.9371 0.0390
-8.750 -0.5739 0.02721 0.01915 -0.0845 0.9356 0.0399
-8.500 -0.5624 0.02662 0.01849 -0.0820 0.9289 0.0406
-8.250 -0.5369 0.02585 0.01764 -0.0820 0.9263 0.0413
-8.000 -0.5094 0.02508 0.01680 -0.0824 0.9244 0.0421
-7.750 -0.4803 0.02434 0.01599 -0.0832 0.9229 0.0428
-7.500 -0.4646 0.02368 0.01536 -0.0815 0.9173 0.0435
-7.250 -0.4435 0.02303 0.01472 -0.0809 0.9130 0.0445
-7.000 -0.4171 0.02237 0.01406 -0.0813 0.9106 0.0457
-6.750 -0.3885 0.02171 0.01338 -0.0821 0.9088 0.0475
-6.500 -0.3590 0.02104 0.01266 -0.0830 0.9074 0.0491
-6.250 -0.3559 0.02073 0.01236 -0.0789 0.8988 0.0502
-6.000 -0.3320 0.02017 0.01181 -0.0789 0.8961 0.0519
-5.750 -0.3045 0.01962 0.01125 -0.0795 0.8941 0.0541
-5.500 -0.2750 0.01908 0.01067 -0.0804 0.8927 0.0569
-5.250 -0.2691 0.01884 0.01045 -0.0767 0.8847 0.0589
-5.000 -0.2441 0.01840 0.01000 -0.0767 0.8812 0.0633
-4.750 -0.2148 0.01785 0.00946 -0.0775 0.8789 0.0691
-4.500 -0.1832 0.01733 0.00891 -0.0788 0.8772 0.0769
-4.250 -0.1744 0.01711 0.00873 -0.0756 0.8698 0.0829
-4.000 -0.1489 0.01667 0.00833 -0.0756 0.8662 0.0936
-3.750 -0.1183 0.01614 0.00787 -0.0767 0.8639 0.1146
-3.500 -0.0854 0.01541 0.00735 -0.0784 0.8619 0.1651
-3.250 -0.0776 0.01410 0.00675 -0.0761 0.8547 0.3249
-3.000 -0.0555 0.01317 0.00668 -0.0757 0.8510 0.5335
-2.750 -0.0226 0.01305 0.00666 -0.0765 0.8487 0.5744
-2.500 0.0136 0.01301 0.00667 -0.0779 0.8469 0.6015
-2.250 0.0412 0.01305 0.00670 -0.0777 0.8429 0.6199
-2.000 0.0652 0.01315 0.00682 -0.0766 0.8374 0.6316
-1.750 0.1013 0.01306 0.00665 -0.0782 0.8340 0.6413
-1.500 0.1418 0.01306 0.00665 -0.0803 0.8312 0.6481
-1.250 0.1767 0.01299 0.00653 -0.0816 0.8264 0.6550
-1.000 0.2017 0.01303 0.00655 -0.0809 0.8193 0.6603
-0.750 0.2436 0.01298 0.00646 -0.0834 0.8139 0.6663
-0.500 0.2738 0.01294 0.00634 -0.0839 0.8073 0.6741
-0.250 0.2981 0.01307 0.00650 -0.0829 0.7995 0.6779
0.000 0.3360 0.01308 0.00647 -0.0847 0.7943 0.6821
0.250 0.3549 0.01312 0.00651 -0.0829 0.7865 0.6870
0.500 0.3809 0.01309 0.00645 -0.0826 0.7796 0.6912
0.750 0.4101 0.01310 0.00646 -0.0827 0.7719 0.6933
1.000 0.4272 0.01315 0.00654 -0.0804 0.7617 0.6959
1.250 0.4504 0.01316 0.00655 -0.0793 0.7525 0.6990
1.500 0.4731 0.01312 0.00649 -0.0782 0.7416 0.7027
1.750 0.4935 0.01307 0.00642 -0.0767 0.7300 0.7072
2.000 0.5209 0.01307 0.00642 -0.0764 0.7196 0.7092
2.250 0.5448 0.01310 0.00644 -0.0755 0.7075 0.7116
2.500 0.5659 0.01313 0.00647 -0.0740 0.6918 0.7146
2.750 0.5920 0.01313 0.00641 -0.0735 0.6721 0.7182
3.000 0.6205 0.01315 0.00627 -0.0736 0.6473 0.7230
3.250 0.6412 0.01329 0.00632 -0.0720 0.6175 0.7256
3.500 0.6600 0.01349 0.00640 -0.0700 0.5853 0.7281
3.750 0.6770 0.01375 0.00651 -0.0678 0.5546 0.7310
4.000 0.6912 0.01406 0.00667 -0.0651 0.5167 0.7345
4.250 0.7010 0.01452 0.00688 -0.0617 0.4704 0.7389
4.500 0.7080 0.01507 0.00720 -0.0579 0.4260 0.7421
4.750 0.7161 0.01563 0.00758 -0.0542 0.3983 0.7450
5.000 0.7303 0.01605 0.00794 -0.0518 0.3801 0.7486
5.250 0.7465 0.01645 0.00826 -0.0499 0.3626 0.7525
5.500 0.7637 0.01685 0.00857 -0.0483 0.3461 0.7565
5.750 0.7787 0.01724 0.00892 -0.0461 0.3300 0.7585
6.000 0.7940 0.01765 0.00929 -0.0441 0.3130 0.7609
6.250 0.8101 0.01804 0.00964 -0.0422 0.2928 0.7637
6.500 0.8261 0.01846 0.01000 -0.0405 0.2710 0.7668
6.750 0.8407 0.01897 0.01039 -0.0386 0.2385 0.7701
7.000 0.8519 0.01963 0.01086 -0.0362 0.2100 0.7730
7.250 0.8646 0.02021 0.01137 -0.0340 0.1951 0.7753
7.500 0.8800 0.02072 0.01186 -0.0323 0.1837 0.7778
7.750 0.8953 0.02125 0.01239 -0.0306 0.1749 0.7807
8.000 0.9108 0.02181 0.01294 -0.0290 0.1672 0.7841
8.250 0.9264 0.02241 0.01352 -0.0275 0.1606 0.7875
8.500 0.9411 0.02294 0.01409 -0.0258 0.1547 0.7900
8.750 0.9538 0.02362 0.01475 -0.0239 0.1490 0.7926
9.000 0.9705 0.02413 0.01534 -0.0225 0.1436 0.7951
9.250 0.9858 0.02474 0.01598 -0.0211 0.1378 0.7977
9.500 0.9994 0.02548 0.01671 -0.0195 0.1333 0.8002
9.750 1.0174 0.02600 0.01732 -0.0186 0.1282 0.8028
10.000 1.0324 0.02662 0.01799 -0.0172 0.1227 0.8052
10.250 1.0467 0.02726 0.01868 -0.0157 0.1178 0.8078
10.500 1.0619 0.02788 0.01936 -0.0144 0.1127 0.8107
10.750 1.0755 0.02864 0.02012 -0.0131 0.1081 0.8134
11.000 1.0902 0.02940 0.02093 -0.0120 0.1043 0.8159
11.250 1.1036 0.03026 0.02181 -0.0108 0.1008 0.8181
11.500 1.1145 0.03127 0.02281 -0.0094 0.0977 0.8203
11.750 1.1276 0.03216 0.02378 -0.0081 0.0948 0.8225
12.000 1.1403 0.03312 0.02484 -0.0070 0.0920 0.8247
12.250 1.1516 0.03421 0.02597 -0.0059 0.0893 0.8270
12.500 1.1610 0.03550 0.02726 -0.0047 0.0870 0.8291
12.750 1.1744 0.03654 0.02842 -0.0038 0.0847 0.8312
13.000 1.1875 0.03763 0.02962 -0.0030 0.0822 0.8332
13.500 1.2089 0.04017 0.03232 -0.0014 0.0776 0.8371
13.750 1.2190 0.04155 0.03378 -0.0006 0.0756 0.8391
14.000 1.2307 0.04284 0.03521 0.0000 0.0734 0.8412
14.250 1.2407 0.04426 0.03675 0.0006 0.0711 0.8434
14.500 1.2492 0.04584 0.03840 0.0012 0.0692 0.8459
14.750 1.2552 0.04767 0.04026 0.0017 0.0674 0.8487
15.000 1.2643 0.04932 0.04207 0.0021 0.0655 0.8517
15.250 1.2722 0.05111 0.04400 0.0024 0.0634 0.8549
15.500 1.2781 0.05313 0.04611 0.0026 0.0615 0.8583
15.750 1.2819 0.05541 0.04846 0.0027 0.0599 0.8616
16.000 1.2854 0.05782 0.05094 0.0027 0.0583 0.8649
16.250 1.2907 0.06015 0.05345 0.0025 0.0565 0.8682
16.500 1.2944 0.06273 0.05618 0.0022 0.0548 0.8715
16.750 1.2967 0.06554 0.05911 0.0016 0.0533 0.8751
17.000 1.2968 0.06868 0.06233 0.0009 0.0520 0.8790
17.500 1.2972 0.07533 0.06930 -0.0011 0.0492 0.8884
17.750 1.2970 0.07892 0.07307 -0.0024 0.0478 0.8949
18.000 1.2959 0.08283 0.07717 -0.0043 0.0464 0.9041
18.250 1.2933 0.08711 0.08162 -0.0068 0.0453 0.9320
18.500 1.2829 0.09102 0.08560 -0.0074 0.0445 1.0000
18.750 1.2769 0.09561 0.09030 -0.0094 0.0435 1.0000
19.000 1.2701 0.10048 0.09536 -0.0118 0.0423 1.0000
19.250 1.2621 0.10560 0.10064 -0.0143 0.0414 1.0000
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Polar data table (+)
Polar graphs
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