MH 117 9.8% (mh117-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH 117 9.8% (mh117-il) Reynolds number: 100,000 Max Cl/Cd: 55.75 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh117-il-100000-n5.txt Download as CSV file: xf-mh117-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: MH 117 9.8%
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
------ -------- --------- --------- -------- -------- --------
-9.750 -0.4539 0.08926 0.08425 -0.0333 1.0000 0.0179
-9.500 -0.4599 0.08395 0.07901 -0.0356 1.0000 0.0178
-9.250 -0.4674 0.07858 0.07371 -0.0381 1.0000 0.0177
-9.000 -0.4787 0.07258 0.06781 -0.0411 1.0000 0.0175
-8.750 -0.4961 0.06571 0.06102 -0.0448 1.0000 0.0173
-8.500 -0.5170 0.05740 0.05279 -0.0518 1.0000 0.0169
-8.250 -0.5340 0.05100 0.04621 -0.0556 1.0000 0.0166
-8.000 -0.5466 0.04538 0.04028 -0.0571 1.0000 0.0165
-7.750 -0.5511 0.04065 0.03516 -0.0571 1.0000 0.0165
-7.500 -0.5489 0.03674 0.03080 -0.0563 1.0000 0.0167
-7.250 -0.5420 0.03342 0.02701 -0.0551 1.0000 0.0170
-7.000 -0.5313 0.03069 0.02378 -0.0536 1.0000 0.0175
-6.750 -0.5188 0.02849 0.02128 -0.0523 1.0000 0.0187
-6.500 -0.5043 0.02723 0.01992 -0.0510 1.0000 0.0205
-6.250 -0.4750 0.02549 0.01785 -0.0523 0.9956 0.0231
-6.000 -0.4414 0.02344 0.01541 -0.0539 0.9894 0.0255
-5.750 -0.4071 0.02193 0.01379 -0.0561 0.9831 0.0310
-5.500 -0.3743 0.02062 0.01235 -0.0576 0.9758 0.0404
-5.250 -0.3382 0.01960 0.01115 -0.0596 0.9697 0.0579
-5.000 -0.3055 0.01888 0.01043 -0.0610 0.9615 0.0785
-4.750 -0.2686 0.01827 0.00973 -0.0632 0.9557 0.0999
-4.500 -0.2361 0.01770 0.00912 -0.0643 0.9474 0.1175
-4.250 -0.1990 0.01715 0.00848 -0.0663 0.9419 0.1371
-4.000 -0.1676 0.01665 0.00797 -0.0672 0.9331 0.1571
-3.750 -0.1315 0.01618 0.00745 -0.0689 0.9272 0.1811
-3.500 -0.1013 0.01577 0.00708 -0.0695 0.9176 0.2080
-3.250 -0.0682 0.01537 0.00673 -0.0706 0.9103 0.2399
-3.000 -0.0368 0.01501 0.00641 -0.0713 0.9016 0.2772
-2.750 -0.0063 0.01467 0.00617 -0.0719 0.8928 0.3190
-2.500 0.0257 0.01434 0.00593 -0.0726 0.8852 0.3676
-2.250 0.0537 0.01404 0.00577 -0.0726 0.8753 0.4205
-2.000 0.0833 0.01374 0.00563 -0.0727 0.8669 0.4817
-1.750 0.1111 0.01346 0.00553 -0.0724 0.8580 0.5485
-1.500 0.1370 0.01321 0.00548 -0.0716 0.8483 0.6209
-1.250 0.1633 0.01296 0.00542 -0.0706 0.8400 0.6988
-1.000 0.1877 0.01277 0.00541 -0.0690 0.8305 0.7781
-0.750 0.2171 0.01262 0.00536 -0.0684 0.8216 0.8606
-0.500 0.2623 0.01247 0.00517 -0.0712 0.8143 0.9400
-0.250 0.3088 0.01241 0.00501 -0.0751 0.8048 1.0000
0.000 0.3344 0.01248 0.00495 -0.0746 0.7949 1.0000
0.250 0.3607 0.01255 0.00489 -0.0741 0.7854 1.0000
0.500 0.3856 0.01266 0.00491 -0.0735 0.7742 1.0000
0.750 0.4111 0.01276 0.00492 -0.0729 0.7634 1.0000
1.000 0.4371 0.01286 0.00494 -0.0724 0.7530 1.0000
1.250 0.4634 0.01295 0.00495 -0.0719 0.7427 1.0000
1.500 0.4887 0.01307 0.00502 -0.0713 0.7309 1.0000
1.750 0.5143 0.01320 0.00510 -0.0707 0.7192 1.0000
2.000 0.5401 0.01332 0.00518 -0.0701 0.7075 1.0000
2.250 0.5660 0.01344 0.00528 -0.0696 0.6957 1.0000
2.500 0.5919 0.01356 0.00537 -0.0690 0.6835 1.0000
2.750 0.6177 0.01368 0.00546 -0.0684 0.6706 1.0000
3.000 0.6433 0.01381 0.00560 -0.0677 0.6570 1.0000
3.250 0.6687 0.01395 0.00574 -0.0670 0.6424 1.0000
3.500 0.6938 0.01410 0.00590 -0.0663 0.6269 1.0000
3.750 0.7189 0.01426 0.00608 -0.0656 0.6103 1.0000
4.000 0.7438 0.01442 0.00627 -0.0649 0.5926 1.0000
4.250 0.7687 0.01459 0.00644 -0.0641 0.5740 1.0000
4.500 0.7930 0.01478 0.00666 -0.0632 0.5531 1.0000
4.750 0.8171 0.01499 0.00685 -0.0623 0.5305 1.0000
5.000 0.8406 0.01524 0.00713 -0.0614 0.5044 1.0000
5.250 0.8636 0.01553 0.00738 -0.0603 0.4752 1.0000
5.500 0.8859 0.01589 0.00768 -0.0592 0.4423 1.0000
5.750 0.9072 0.01633 0.00802 -0.0580 0.4058 1.0000
6.000 0.9277 0.01687 0.00847 -0.0567 0.3679 1.0000
6.250 0.9474 0.01751 0.00896 -0.0554 0.3308 1.0000
6.500 0.9668 0.01820 0.00954 -0.0541 0.2955 1.0000
6.750 0.9854 0.01897 0.01018 -0.0528 0.2624 1.0000
7.000 1.0042 0.01974 0.01088 -0.0516 0.2319 1.0000
7.250 1.0225 0.02056 0.01162 -0.0503 0.2045 1.0000
7.500 1.0403 0.02142 0.01247 -0.0490 0.1803 1.0000
7.750 1.0579 0.02230 0.01332 -0.0477 0.1578 1.0000
8.000 1.0743 0.02327 0.01424 -0.0462 0.1391 1.0000
8.250 1.0904 0.02426 0.01522 -0.0448 0.1236 1.0000
8.500 1.1058 0.02528 0.01626 -0.0432 0.1097 1.0000
9.000 1.1347 0.02745 0.01854 -0.0400 0.0885 1.0000
9.250 1.1476 0.02862 0.01981 -0.0382 0.0801 1.0000
9.500 1.1573 0.02988 0.02109 -0.0362 0.0732 1.0000
9.750 1.1687 0.03109 0.02246 -0.0341 0.0669 1.0000
10.000 1.1762 0.03247 0.02387 -0.0320 0.0615 1.0000
10.250 1.1858 0.03387 0.02544 -0.0301 0.0560 1.0000
10.500 1.1935 0.03538 0.02705 -0.0282 0.0516 1.0000
10.750 1.1984 0.03721 0.02893 -0.0263 0.0477 1.0000
11.000 1.2060 0.03884 0.03080 -0.0248 0.0430 1.0000
11.250 1.2095 0.04071 0.03276 -0.0233 0.0395 1.0000
11.500 1.2122 0.04295 0.03512 -0.0219 0.0364 1.0000
11.750 1.2158 0.04509 0.03751 -0.0208 0.0327 1.0000
12.000 1.2163 0.04747 0.04006 -0.0200 0.0302 1.0000
12.250 1.2125 0.05045 0.04307 -0.0193 0.0280 1.0000
12.500 1.2128 0.05335 0.04631 -0.0188 0.0257 1.0000
12.750 1.2103 0.05660 0.04978 -0.0186 0.0239 1.0000
13.000 1.2060 0.06010 0.05346 -0.0188 0.0226 1.0000
13.250 1.1994 0.06389 0.05737 -0.0196 0.0213 1.0000
13.500 1.1911 0.06814 0.06172 -0.0207 0.0205 1.0000
13.750 1.1815 0.07299 0.06676 -0.0220 0.0197 1.0000
14.000 1.1703 0.07834 0.07241 -0.0240 0.0190 1.0000
14.250 1.1569 0.08434 0.07866 -0.0266 0.0185 1.0000
14.500 1.1425 0.09087 0.08543 -0.0298 0.0182 1.0000
14.750 1.1261 0.09821 0.09300 -0.0338 0.0179 1.0000
15.000 1.1088 0.10621 0.10119 -0.0384 0.0180 1.0000
15.250 1.0886 0.11544 0.11062 -0.0439 0.0182 1.0000
15.500 1.0686 0.12517 0.12051 -0.0498 0.0187 1.0000
15.750 1.0477 0.13576 0.13122 -0.0562 0.0192 1.0000
16.000 1.0279 0.14657 0.14210 -0.0626 0.0197 1.0000
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Polar data table (+)
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