AH 93-W-300 (ah93w300-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: AH 93-W-300 (ah93w300-il) Reynolds number: 100,000 Max Cl/Cd: 27.33 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ah93w300-il-100000-n5.txt Download as CSV file: xf-ah93w300-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: AH 93-W-300
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
------ -------- --------- --------- -------- -------- --------
-15.000 -0.4649 0.11657 0.10902 -0.0464 1.0000 0.1970
-14.750 -0.4518 0.11545 0.10794 -0.0466 1.0000 0.2005
-14.250 -0.4865 0.10437 0.09680 -0.0492 1.0000 0.2193
-14.000 -0.4625 0.10508 0.09757 -0.0487 1.0000 0.2204
-13.750 -0.4410 0.10551 0.09807 -0.0481 1.0000 0.2219
-13.500 -0.4248 0.10529 0.09791 -0.0476 1.0000 0.2244
-13.000 -0.4808 0.09316 0.08573 -0.0490 1.0000 0.2461
-12.750 -0.4609 0.09418 0.08685 -0.0476 1.0000 0.2470
-12.250 -0.4537 0.08726 0.07992 -0.0515 0.9842 0.2605
-12.000 -0.3739 0.09206 0.08480 -0.0535 0.9704 0.2549
-11.250 -0.3468 0.08045 0.07300 -0.0633 0.9312 0.2765
-7.250 -0.2732 0.04229 0.03362 -0.0689 0.7321 0.3741
-7.000 -0.2384 0.04317 0.03455 -0.0686 0.7215 0.3749
-6.750 -0.2060 0.04385 0.03523 -0.0682 0.7113 0.3760
-6.500 -0.1754 0.04433 0.03564 -0.0677 0.7025 0.3773
-6.250 -0.1489 0.04455 0.03586 -0.0673 0.6930 0.3792
-5.500 -0.2602 0.03182 0.02263 -0.0609 0.6721 0.4122
-5.250 -0.2281 0.03227 0.02313 -0.0607 0.6635 0.4141
-5.000 -0.1992 0.03254 0.02345 -0.0603 0.6543 0.4163
-4.750 -0.1745 0.03244 0.02330 -0.0599 0.6464 0.4194
-4.500 -0.1620 0.03138 0.02208 -0.0595 0.6399 0.4253
-4.250 -0.1556 0.02994 0.02051 -0.0590 0.6318 0.4321
-4.000 -0.1265 0.03019 0.02080 -0.0586 0.6234 0.4342
-3.750 -0.0974 0.03032 0.02091 -0.0584 0.6162 0.4367
-3.500 -0.0713 0.03029 0.02085 -0.0582 0.6092 0.4399
-3.250 -0.0506 0.02990 0.02044 -0.0580 0.6011 0.4446
-3.000 -0.0340 0.02863 0.01894 -0.0587 0.5940 0.4520
-2.750 -0.0042 0.02879 0.01909 -0.0584 0.5875 0.4540
-2.500 0.0232 0.02899 0.01933 -0.0581 0.5805 0.4564
-2.250 0.0489 0.02910 0.01949 -0.0576 0.5727 0.4594
-2.000 0.0750 0.02899 0.01935 -0.0576 0.5659 0.4631
-1.750 0.1018 0.02859 0.01879 -0.0582 0.5600 0.4680
-1.500 0.1262 0.02796 0.01802 -0.0591 0.5533 0.4740
-1.250 0.1520 0.02815 0.01830 -0.0585 0.5459 0.4763
-1.000 0.1790 0.02829 0.01846 -0.0581 0.5394 0.4789
-0.750 0.2079 0.02833 0.01845 -0.0581 0.5339 0.4819
-0.500 0.2333 0.02835 0.01848 -0.0580 0.5273 0.4855
-0.250 0.2588 0.02822 0.01834 -0.0581 0.5204 0.4901
0.000 0.2871 0.02783 0.01779 -0.0593 0.5142 0.4960
0.250 0.3160 0.02782 0.01772 -0.0594 0.5090 0.4990
0.500 0.3411 0.02801 0.01799 -0.0589 0.5030 0.5015
0.750 0.3654 0.02818 0.01824 -0.0583 0.4964 0.5044
1.000 0.3917 0.02827 0.01834 -0.0580 0.4905 0.5079
1.250 0.4207 0.02826 0.01824 -0.0584 0.4853 0.5121
1.500 0.4484 0.02823 0.01815 -0.0589 0.4798 0.5169
1.750 0.4749 0.02814 0.01801 -0.0597 0.4734 0.5220
2.000 0.4994 0.02828 0.01821 -0.0590 0.4675 0.5246
2.250 0.5261 0.02841 0.01834 -0.0586 0.4624 0.5275
2.500 0.5527 0.02861 0.01853 -0.0584 0.4574 0.5308
2.750 0.5738 0.02886 0.01888 -0.0575 0.4510 0.5343
3.000 0.5982 0.02898 0.01901 -0.0572 0.4451 0.5383
3.250 0.6265 0.02901 0.01896 -0.0576 0.4399 0.5429
3.500 0.6571 0.02904 0.01885 -0.0586 0.4349 0.5480
3.750 0.6754 0.02932 0.01927 -0.0574 0.4286 0.5512
4.000 0.6961 0.02958 0.01960 -0.0562 0.4229 0.5541
4.250 0.7203 0.02976 0.01977 -0.0556 0.4178 0.5573
4.500 0.7471 0.02994 0.01991 -0.0555 0.4131 0.5609
4.750 0.7618 0.03036 0.02046 -0.0538 0.4070 0.5649
5.000 0.7818 0.03064 0.02076 -0.0530 0.4012 0.5694
5.250 0.8071 0.03079 0.02084 -0.0530 0.3962 0.5743
5.500 0.8337 0.03098 0.02094 -0.0533 0.3914 0.5785
5.750 0.8403 0.03150 0.02163 -0.0503 0.3855 0.5813
6.000 0.8519 0.03190 0.02212 -0.0480 0.3801 0.5844
6.250 0.8705 0.03219 0.02241 -0.0467 0.3754 0.5881
6.500 0.8900 0.03256 0.02276 -0.0457 0.3707 0.5923
6.750 0.8964 0.03345 0.02379 -0.0435 0.3649 0.5965
7.000 0.9121 0.03408 0.02445 -0.0425 0.3594 0.6010
7.250 0.9360 0.03440 0.02469 -0.0425 0.3547 0.6057
7.500 0.9502 0.03520 0.02552 -0.0416 0.3496 0.6096
7.750 0.9547 0.03635 0.02682 -0.0395 0.3439 0.6129
8.000 0.9677 0.03713 0.02766 -0.0383 0.3388 0.6166
8.250 0.9910 0.03742 0.02790 -0.0379 0.3345 0.6211
8.500 0.9909 0.03909 0.02973 -0.0361 0.3289 0.6251
8.750 0.9968 0.04052 0.03124 -0.0349 0.3233 0.6295
9.000 1.0140 0.04128 0.03196 -0.0346 0.3186 0.6342
9.250 1.0301 0.04224 0.03289 -0.0344 0.3140 0.6390
9.500 1.0248 0.04460 0.03544 -0.0331 0.3081 0.6425
9.750 1.0322 0.04601 0.03692 -0.0321 0.3031 0.6464
10.000 1.0543 0.04636 0.03722 -0.0317 0.2991 0.6512
10.250 1.0431 0.04948 0.04055 -0.0307 0.2933 0.6550
10.500 1.0426 0.05187 0.04303 -0.0302 0.2878 0.6595
10.750 1.0606 0.05269 0.04380 -0.0301 0.2835 0.6649
11.000 1.0593 0.05538 0.04657 -0.0300 0.2784 0.6694
11.250 1.0483 0.05910 0.05042 -0.0299 0.2725 0.6732
11.500 1.0611 0.06025 0.05161 -0.0295 0.2682 0.6778
11.750 1.0700 0.06192 0.05330 -0.0292 0.2640 0.6827
12.000 1.0403 0.06795 0.05958 -0.0296 0.2573 0.6858
12.250 1.0533 0.06936 0.06098 -0.0296 0.2531 0.6917
12.500 1.0805 0.06926 0.06077 -0.0296 0.2499 0.6987
12.750 1.0233 0.07915 0.07101 -0.0313 0.2416 0.7000
13.000 1.0412 0.08003 0.07187 -0.0314 0.2380 0.7058
13.250 1.0732 0.07894 0.07072 -0.0307 0.2356 0.7128
13.500 0.9932 0.09256 0.08473 -0.0340 0.2256 0.7121
13.750 1.0214 0.09197 0.08409 -0.0336 0.2232 0.7201
14.250 0.9706 0.10594 0.09833 -0.0378 0.2103 0.7276
14.500 1.0054 0.10432 0.09665 -0.0371 0.2089 0.7364
15.000 0.9572 0.11832 0.11092 -0.0418 0.1961 0.7436
15.250 0.9919 0.11655 0.10910 -0.0410 0.1952 0.7539
15.750 0.9518 0.13011 0.12288 -0.0466 0.1830 0.7632
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