AH 93-W-174 (ah93w174-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: AH 93-W-174 (ah93w174-il) Reynolds number: 200,000 Max Cl/Cd: 71.11 at α=9.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ah93w174-il-200000-n5.txt Download as CSV file: xf-ah93w174-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: AH 93-W-174
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
------ -------- --------- --------- -------- -------- --------
-14.750 -0.7045 0.07085 0.06634 -0.0720 1.0000 0.0327
-14.500 -0.7349 0.06245 0.05773 -0.0779 1.0000 0.0327
-14.250 -0.7551 0.05622 0.05131 -0.0821 1.0000 0.0330
-14.000 -0.7708 0.05115 0.04603 -0.0853 1.0000 0.0333
-13.750 -0.7821 0.04705 0.04175 -0.0873 1.0000 0.0337
-13.500 -0.7612 0.04242 0.03681 -0.0958 0.9030 0.0345
-13.250 -0.7182 0.03940 0.03345 -0.1053 0.8381 0.0354
-13.000 -0.7063 0.03735 0.03114 -0.1075 0.8017 0.0361
-12.750 -0.6982 0.03555 0.02912 -0.1083 0.7778 0.0368
-12.500 -0.6919 0.03392 0.02727 -0.1083 0.7589 0.0376
-12.250 -0.6874 0.03245 0.02557 -0.1075 0.7436 0.0385
-12.000 -0.6820 0.03109 0.02397 -0.1064 0.7309 0.0394
-11.750 -0.6751 0.02990 0.02262 -0.1052 0.7196 0.0401
-11.500 -0.6670 0.02891 0.02156 -0.1038 0.7100 0.0409
-11.250 -0.6589 0.02805 0.02058 -0.1021 0.7015 0.0417
-11.000 -0.6500 0.02729 0.01972 -0.1002 0.6937 0.0426
-10.750 -0.6377 0.02653 0.01881 -0.0987 0.6863 0.0438
-10.500 -0.6231 0.02576 0.01787 -0.0974 0.6797 0.0451
-10.250 -0.6074 0.02498 0.01696 -0.0963 0.6730 0.0464
-10.000 -0.5911 0.02433 0.01625 -0.0952 0.6672 0.0477
-9.750 -0.5730 0.02373 0.01556 -0.0942 0.6620 0.0492
-9.500 -0.5538 0.02311 0.01484 -0.0933 0.6568 0.0509
-9.250 -0.5335 0.02254 0.01412 -0.0925 0.6521 0.0528
-9.000 -0.5142 0.02195 0.01345 -0.0917 0.6479 0.0547
-8.750 -0.4931 0.02144 0.01291 -0.0910 0.6432 0.0568
-8.500 -0.4711 0.02095 0.01233 -0.0904 0.6385 0.0592
-8.250 -0.4488 0.02048 0.01173 -0.0898 0.6343 0.0616
-8.000 -0.4272 0.01999 0.01120 -0.0892 0.6307 0.0642
-7.750 -0.4038 0.01959 0.01074 -0.0887 0.6270 0.0674
-7.250 -0.3569 0.01874 0.00981 -0.0878 0.6196 0.0741
-7.000 -0.3326 0.01841 0.00940 -0.0874 0.6163 0.0783
-6.750 -0.3083 0.01807 0.00897 -0.0870 0.6132 0.0825
-6.500 -0.2838 0.01771 0.00862 -0.0867 0.6097 0.0873
-6.250 -0.2583 0.01744 0.00827 -0.0864 0.6061 0.0927
-6.000 -0.2336 0.01708 0.00794 -0.0861 0.6029 0.0985
-5.750 -0.2078 0.01685 0.00763 -0.0859 0.6000 0.1052
-5.500 -0.1825 0.01655 0.00733 -0.0857 0.5974 0.1127
-5.250 -0.1564 0.01634 0.00705 -0.0855 0.5950 0.1210
-5.000 -0.1304 0.01608 0.00683 -0.0854 0.5919 0.1309
-4.750 -0.1044 0.01583 0.00661 -0.0853 0.5887 0.1415
-4.500 -0.0781 0.01561 0.00640 -0.0851 0.5856 0.1538
-4.250 -0.0516 0.01540 0.00619 -0.0850 0.5829 0.1678
-4.000 -0.0250 0.01521 0.00600 -0.0850 0.5805 0.1840
-3.750 0.0018 0.01503 0.00583 -0.0850 0.5784 0.2022
-3.500 0.0285 0.01483 0.00571 -0.0849 0.5759 0.2234
-3.250 0.0552 0.01464 0.00560 -0.0849 0.5731 0.2476
-3.000 0.0818 0.01442 0.00549 -0.0849 0.5702 0.2757
-2.750 0.1085 0.01421 0.00538 -0.0849 0.5675 0.3090
-2.500 0.1352 0.01400 0.00528 -0.0849 0.5651 0.3492
-2.250 0.1620 0.01380 0.00521 -0.0848 0.5630 0.3945
-2.000 0.1890 0.01365 0.00518 -0.0848 0.5611 0.4435
-1.750 0.2156 0.01353 0.00524 -0.0846 0.5587 0.4909
-1.500 0.2422 0.01345 0.00532 -0.0844 0.5560 0.5336
-1.250 0.2691 0.01341 0.00539 -0.0842 0.5533 0.5708
-1.000 0.2963 0.01341 0.00546 -0.0840 0.5507 0.6017
-0.750 0.3235 0.01344 0.00552 -0.0838 0.5485 0.6281
-0.500 0.3512 0.01350 0.00558 -0.0836 0.5465 0.6515
-0.250 0.3788 0.01358 0.00565 -0.0835 0.5448 0.6716
0.000 0.4058 0.01368 0.00578 -0.0832 0.5425 0.6900
0.250 0.4326 0.01377 0.00593 -0.0829 0.5398 0.7067
0.500 0.4595 0.01386 0.00605 -0.0827 0.5371 0.7225
0.750 0.4861 0.01396 0.00617 -0.0823 0.5347 0.7366
1.000 0.5129 0.01406 0.00628 -0.0820 0.5326 0.7501
1.250 0.5399 0.01417 0.00639 -0.0817 0.5306 0.7639
1.500 0.5671 0.01429 0.00648 -0.0815 0.5288 0.7776
1.750 0.5935 0.01441 0.00661 -0.0811 0.5268 0.7886
2.000 0.6190 0.01454 0.00681 -0.0807 0.5240 0.7987
2.250 0.6451 0.01467 0.00697 -0.0803 0.5214 0.8086
2.500 0.6709 0.01479 0.00713 -0.0799 0.5191 0.8170
2.750 0.6975 0.01490 0.00725 -0.0797 0.5169 0.8264
3.000 0.7234 0.01500 0.00735 -0.0793 0.5148 0.8344
3.250 0.7503 0.01510 0.00744 -0.0791 0.5128 0.8432
3.500 0.7768 0.01521 0.00754 -0.0788 0.5109 0.8508
3.750 0.8009 0.01538 0.00781 -0.0782 0.5083 0.8597
4.000 0.8249 0.01553 0.00804 -0.0776 0.5057 0.8678
4.250 0.8498 0.01567 0.00822 -0.0771 0.5031 0.8769
4.500 0.8741 0.01576 0.00836 -0.0764 0.5006 0.8853
4.750 0.8996 0.01587 0.00848 -0.0760 0.4984 0.8949
5.000 0.9246 0.01595 0.00859 -0.0755 0.4966 0.9039
5.250 0.9508 0.01606 0.00870 -0.0752 0.4947 0.9138
5.500 0.9725 0.01626 0.00903 -0.0743 0.4915 0.9257
5.750 0.9969 0.01642 0.00929 -0.0738 0.4886 0.9385
6.000 1.0253 0.01656 0.00950 -0.0742 0.4858 0.9526
6.500 1.0922 0.01682 0.00983 -0.0770 0.4809 1.0000
6.750 1.1216 0.01699 0.00998 -0.0776 0.4788 1.0000
7.000 1.1441 0.01736 0.01048 -0.0773 0.4752 1.0000
7.250 1.1686 0.01765 0.01086 -0.0771 0.4717 1.0000
7.500 1.1943 0.01786 0.01113 -0.0771 0.4686 1.0000
7.750 1.2213 0.01800 0.01128 -0.0772 0.4656 1.0000
8.000 1.2486 0.01813 0.01142 -0.0773 0.4624 1.0000
8.250 1.2677 0.01850 0.01193 -0.0763 0.4572 1.0000
8.500 1.2906 0.01869 0.01219 -0.0758 0.4525 1.0000
8.750 1.3168 0.01874 0.01224 -0.0756 0.4484 1.0000
9.000 1.3351 0.01907 0.01269 -0.0744 0.4428 1.0000
9.250 1.3542 0.01931 0.01303 -0.0733 0.4368 1.0000
9.500 1.3774 0.01937 0.01307 -0.0727 0.4312 1.0000
9.750 1.3891 0.01981 0.01365 -0.0705 0.4231 1.0000
10.000 1.4063 0.01993 0.01377 -0.0689 0.4156 1.0000
10.250 1.4122 0.02044 0.01439 -0.0658 0.4066 1.0000
10.500 1.4214 0.02089 0.01486 -0.0633 0.3978 1.0000
10.750 1.4271 0.02153 0.01553 -0.0606 0.3877 1.0000
11.000 1.4303 0.02243 0.01651 -0.0580 0.3776 1.0000
11.250 1.4327 0.02349 0.01758 -0.0556 0.3667 1.0000
11.500 1.4322 0.02487 0.01897 -0.0533 0.3545 1.0000
11.750 1.4286 0.02665 0.02076 -0.0511 0.3406 1.0000
12.000 1.4225 0.02880 0.02289 -0.0492 0.3251 1.0000
12.250 1.4141 0.03132 0.02538 -0.0474 0.3083 1.0000
12.500 1.4032 0.03419 0.02820 -0.0459 0.2900 1.0000
12.750 1.3908 0.03733 0.03128 -0.0444 0.2718 1.0000
13.000 1.3764 0.04076 0.03463 -0.0432 0.2531 1.0000
13.250 1.3617 0.04434 0.03813 -0.0421 0.2355 1.0000
13.500 1.3489 0.04797 0.04169 -0.0413 0.2191 1.0000
13.750 1.3376 0.05163 0.04528 -0.0408 0.2024 1.0000
14.000 1.3280 0.05526 0.04886 -0.0405 0.1870 1.0000
14.250 1.3195 0.05891 0.05247 -0.0403 0.1719 1.0000
14.500 1.3120 0.06258 0.05609 -0.0403 0.1576 1.0000
14.750 1.3055 0.06625 0.05972 -0.0405 0.1445 1.0000
15.000 1.3002 0.06987 0.06330 -0.0407 0.1323 1.0000
15.250 1.2952 0.07354 0.06694 -0.0411 0.1202 1.0000
15.500 1.2919 0.07709 0.07047 -0.0415 0.1090 1.0000
15.750 1.2897 0.08056 0.07393 -0.0420 0.0991 1.0000
16.000 1.2870 0.08416 0.07752 -0.0426 0.0902 1.0000
16.250 1.2844 0.08780 0.08115 -0.0433 0.0819 1.0000
16.500 1.2832 0.09133 0.08470 -0.0440 0.0747 1.0000
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Polar data table (+)
Polar graphs
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