AH 93-W-145 (ah93w145-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: AH 93-W-145 (ah93w145-il) Reynolds number: 100,000 Max Cl/Cd: 49.33 at α=9.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ah93w145-il-100000-n5.txt Download as CSV file: xf-ah93w145-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: AH 93-W-145
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.3773 0.09268 0.08789 -0.0487 1.0000 0.0374
-10.000 -0.3864 0.08681 0.08211 -0.0518 1.0000 0.0378
-9.750 -0.4018 0.07985 0.07526 -0.0558 1.0000 0.0380
-9.500 -0.4354 0.06486 0.06030 -0.0695 0.9587 0.0373
-9.250 -0.4678 0.05177 0.04665 -0.0833 0.8923 0.0370
-9.000 -0.4709 0.04512 0.03934 -0.0875 0.8604 0.0380
-8.750 -0.4676 0.03999 0.03344 -0.0889 0.8367 0.0391
-8.500 -0.4580 0.03590 0.02855 -0.0891 0.8179 0.0402
-8.250 -0.4399 0.03365 0.02594 -0.0890 0.8019 0.0413
-8.000 -0.4183 0.03247 0.02459 -0.0890 0.7876 0.0429
-7.750 -0.3968 0.03112 0.02294 -0.0888 0.7748 0.0452
-7.500 -0.3750 0.02931 0.02064 -0.0885 0.7637 0.0478
-7.250 -0.3518 0.02772 0.01871 -0.0883 0.7543 0.0497
-7.000 -0.3276 0.02683 0.01775 -0.0882 0.7445 0.0523
-6.750 -0.3022 0.02588 0.01654 -0.0882 0.7368 0.0560
-6.500 -0.2767 0.02474 0.01512 -0.0880 0.7287 0.0593
-6.250 -0.2512 0.02398 0.01429 -0.0880 0.7220 0.0628
-6.000 -0.2252 0.02327 0.01341 -0.0879 0.7144 0.0678
-5.750 -0.1994 0.02246 0.01248 -0.0877 0.7084 0.0722
-5.500 -0.1733 0.02190 0.01185 -0.0877 0.7022 0.0782
-5.250 -0.1473 0.02127 0.01111 -0.0875 0.6964 0.0844
-5.000 -0.1209 0.02078 0.01055 -0.0875 0.6916 0.0920
-4.750 -0.0949 0.02027 0.01001 -0.0874 0.6861 0.1003
-4.500 -0.0684 0.01986 0.00952 -0.0873 0.6807 0.1108
-4.250 -0.0420 0.01945 0.00907 -0.0872 0.6762 0.1233
-4.000 -0.0156 0.01907 0.00870 -0.0872 0.6716 0.1385
-3.750 0.0109 0.01872 0.00839 -0.0872 0.6670 0.1575
-3.500 0.0374 0.01837 0.00809 -0.0872 0.6628 0.1826
-3.250 0.0642 0.01802 0.00781 -0.0872 0.6593 0.2161
-3.000 0.0902 0.01765 0.00762 -0.0873 0.6548 0.2639
-2.750 0.1158 0.01720 0.00748 -0.0872 0.6505 0.3383
-2.500 0.1404 0.01672 0.00742 -0.0869 0.6467 0.4502
-2.250 0.1641 0.01640 0.00747 -0.0858 0.6437 0.5643
-2.000 0.1868 0.01633 0.00764 -0.0843 0.6403 0.6493
-1.750 0.2092 0.01639 0.00784 -0.0827 0.6364 0.7119
-1.500 0.2319 0.01650 0.00798 -0.0810 0.6327 0.7590
-1.250 0.2549 0.01664 0.00807 -0.0794 0.6295 0.7961
-1.000 0.2784 0.01677 0.00812 -0.0780 0.6269 0.8266
-0.750 0.3009 0.01694 0.00827 -0.0765 0.6233 0.8537
-0.500 0.3236 0.01708 0.00839 -0.0751 0.6198 0.8785
-0.250 0.3470 0.01718 0.00844 -0.0737 0.6166 0.9056
0.000 0.3756 0.01723 0.00841 -0.0732 0.6136 0.9346
0.250 0.4128 0.01727 0.00833 -0.0748 0.6111 0.9577
0.500 0.4517 0.01740 0.00843 -0.0774 0.6074 0.9712
0.750 0.4920 0.01755 0.00853 -0.0804 0.6040 0.9825
1.000 0.5334 0.01767 0.00859 -0.0836 0.6007 0.9926
1.250 0.5690 0.01780 0.00863 -0.0856 0.5978 1.0000
1.500 0.5906 0.01796 0.00871 -0.0848 0.5954 1.0000
1.750 0.6096 0.01825 0.00901 -0.0837 0.5922 1.0000
2.000 0.6299 0.01857 0.00935 -0.0828 0.5888 1.0000
2.250 0.6529 0.01885 0.00961 -0.0824 0.5856 1.0000
2.500 0.6779 0.01909 0.00982 -0.0822 0.5827 1.0000
2.750 0.7045 0.01932 0.01000 -0.0822 0.5803 1.0000
3.000 0.7303 0.01965 0.01032 -0.0823 0.5778 1.0000
3.250 0.7534 0.02011 0.01086 -0.0820 0.5738 1.0000
3.500 0.7786 0.02048 0.01128 -0.0820 0.5703 1.0000
3.750 0.8053 0.02079 0.01159 -0.0821 0.5674 1.0000
4.000 0.8330 0.02107 0.01186 -0.0823 0.5650 1.0000
4.250 0.8605 0.02137 0.01218 -0.0825 0.5625 1.0000
4.500 0.8819 0.02201 0.01296 -0.0821 0.5579 1.0000
4.750 0.9066 0.02246 0.01348 -0.0820 0.5542 1.0000
5.000 0.9334 0.02278 0.01385 -0.0821 0.5512 1.0000
5.250 0.9617 0.02302 0.01411 -0.0824 0.5486 1.0000
5.500 0.9848 0.02358 0.01479 -0.0821 0.5448 1.0000
5.750 1.0060 0.02423 0.01558 -0.0816 0.5398 1.0000
6.000 1.0318 0.02457 0.01601 -0.0815 0.5362 1.0000
6.250 1.0607 0.02470 0.01617 -0.0818 0.5332 1.0000
6.500 1.0809 0.02535 0.01698 -0.0811 0.5279 1.0000
6.750 1.1028 0.02582 0.01760 -0.0805 0.5223 1.0000
7.000 1.1324 0.02574 0.01757 -0.0806 0.5182 1.0000
7.250 1.1516 0.02625 0.01823 -0.0797 0.5112 1.0000
7.500 1.1768 0.02627 0.01835 -0.0792 0.5047 1.0000
7.750 1.2024 0.02625 0.01844 -0.0788 0.4985 1.0000
8.000 1.2219 0.02655 0.01890 -0.0778 0.4903 1.0000
8.250 1.2464 0.02647 0.01892 -0.0771 0.4829 1.0000
8.500 1.2669 0.02655 0.01915 -0.0760 0.4736 1.0000
8.750 1.2832 0.02685 0.01962 -0.0745 0.4633 1.0000
9.000 1.3038 0.02680 0.01968 -0.0732 0.4527 1.0000
9.250 1.3225 0.02681 0.01979 -0.0718 0.4406 1.0000
9.500 1.3344 0.02724 0.02038 -0.0697 0.4265 1.0000
9.750 1.3407 0.02790 0.02117 -0.0670 0.4109 1.0000
10.000 1.3417 0.02899 0.02238 -0.0640 0.3932 1.0000
10.250 1.3436 0.03017 0.02360 -0.0615 0.3713 1.0000
10.500 1.3442 0.03163 0.02502 -0.0594 0.3440 1.0000
10.750 1.3417 0.03356 0.02679 -0.0574 0.3122 1.0000
11.000 1.3335 0.03632 0.02935 -0.0557 0.2812 1.0000
11.250 1.3222 0.03965 0.03252 -0.0543 0.2534 1.0000
11.500 1.3106 0.04320 0.03594 -0.0532 0.2287 1.0000
11.750 1.2991 0.04685 0.03948 -0.0522 0.2068 1.0000
12.000 1.2894 0.05040 0.04295 -0.0514 0.1863 1.0000
12.250 1.2804 0.05394 0.04641 -0.0507 0.1679 1.0000
12.500 1.2722 0.05742 0.04984 -0.0501 0.1512 1.0000
12.750 1.2650 0.06090 0.05325 -0.0496 0.1359 1.0000
13.000 1.2595 0.06431 0.05662 -0.0493 0.1216 1.0000
13.250 1.2548 0.06772 0.05999 -0.0491 0.1086 1.0000
13.500 1.2511 0.07109 0.06334 -0.0489 0.0968 1.0000
13.750 1.2486 0.07439 0.06665 -0.0488 0.0863 1.0000
14.000 1.2463 0.07771 0.06998 -0.0488 0.0773 1.0000
14.250 1.2431 0.08121 0.07347 -0.0489 0.0700 1.0000
14.500 1.2413 0.08460 0.07691 -0.0490 0.0634 1.0000
14.750 1.2395 0.08801 0.08035 -0.0492 0.0580 1.0000
15.000 1.2378 0.09147 0.08386 -0.0495 0.0533 1.0000
15.250 1.2358 0.09497 0.08738 -0.0498 0.0496 1.0000
15.500 1.2362 0.09821 0.09073 -0.0502 0.0458 1.0000
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Polar data table (+)
Polar graphs
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