SM701 (sm701-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: SM701 (sm701-il) Reynolds number: 100,000 Max Cl/Cd: 50.76 at α=6.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sm701-il-100000.txt Download as CSV file: xf-sm701-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: SM701
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.4308 0.10625 0.10207 -0.0279 1.0000 0.1498
-8.500 -0.4469 0.10402 0.09991 -0.0269 1.0000 0.1542
-8.250 -0.5330 0.10014 0.09622 -0.0305 1.0000 0.1582
-8.000 -0.5064 0.09751 0.09360 -0.0265 1.0000 0.1614
-7.750 -0.4784 0.09551 0.09157 -0.0259 0.9972 0.1679
-7.250 -0.4900 0.08747 0.08360 -0.0318 0.9866 0.1836
-6.750 -0.5878 0.05339 0.04724 -0.0562 0.9705 0.0818
-6.500 -0.5731 0.04970 0.04329 -0.0563 0.9658 0.0795
-6.250 -0.5497 0.04587 0.03895 -0.0576 0.9617 0.0768
-6.000 -0.5169 0.04229 0.03428 -0.0594 0.9584 0.0720
-5.750 -0.4920 0.04066 0.03229 -0.0595 0.9540 0.0714
-5.500 -0.4658 0.03870 0.03005 -0.0598 0.9497 0.0714
-5.250 -0.4340 0.03668 0.02782 -0.0610 0.9461 0.0721
-5.000 -0.3995 0.03528 0.02641 -0.0628 0.9428 0.0750
-4.750 -0.3805 0.03440 0.02549 -0.0617 0.9374 0.0776
-4.500 -0.3503 0.03352 0.02450 -0.0622 0.9330 0.0804
-4.250 -0.3127 0.03285 0.02368 -0.0638 0.9294 0.0836
-4.000 -0.2944 0.03185 0.02286 -0.0626 0.9239 0.0876
-3.750 -0.2658 0.03133 0.02237 -0.0630 0.9189 0.0960
-3.500 -0.2280 0.03056 0.02177 -0.0652 0.9151 0.1132
-3.250 -0.2039 0.02898 0.02077 -0.0659 0.9095 0.1788
-3.000 -0.1784 0.02799 0.02180 -0.0658 0.9044 0.5943
-2.750 -0.1480 0.02938 0.02317 -0.0643 0.8996 0.6447
-2.500 -0.1429 0.03025 0.02407 -0.0590 0.8911 0.6743
-2.250 -0.1215 0.03147 0.02529 -0.0553 0.8854 0.7066
-2.000 -0.1128 0.03206 0.02586 -0.0510 0.8772 0.7241
-1.750 -0.0888 0.03260 0.02633 -0.0488 0.8709 0.7416
-1.500 -0.0753 0.03303 0.02671 -0.0455 0.8628 0.7579
-1.250 -0.0608 0.03347 0.02714 -0.0410 0.8555 0.7775
-1.000 -0.0515 0.03379 0.02744 -0.0364 0.8471 0.7959
-0.750 -0.0279 0.03385 0.02741 -0.0349 0.8396 0.8104
-0.500 -0.0012 0.03383 0.02729 -0.0351 0.8312 0.8176
-0.250 0.0362 0.03368 0.02700 -0.0374 0.8234 0.8236
0.000 0.0616 0.03360 0.02686 -0.0371 0.8145 0.8286
0.250 0.0992 0.03338 0.02654 -0.0391 0.8068 0.8338
0.500 0.1314 0.03335 0.02641 -0.0407 0.7976 0.8391
0.750 0.1674 0.03299 0.02599 -0.0418 0.7901 0.8432
1.000 0.1936 0.03293 0.02588 -0.0419 0.7800 0.8484
1.250 0.2386 0.03249 0.02536 -0.0449 0.7734 0.8536
1.500 0.2630 0.03239 0.02524 -0.0446 0.7626 0.8581
1.750 0.3068 0.03168 0.02449 -0.0465 0.7567 0.8629
2.000 0.3339 0.03158 0.02436 -0.0468 0.7455 0.8691
2.250 0.3791 0.03065 0.02340 -0.0487 0.7403 0.8738
2.500 0.4267 0.02954 0.02226 -0.0508 0.7363 0.8786
2.750 0.4536 0.02922 0.02194 -0.0507 0.7245 0.8855
3.000 0.5063 0.02769 0.02040 -0.0531 0.7221 0.8908
3.250 0.5274 0.02744 0.02017 -0.0519 0.7090 0.8986
3.500 0.5873 0.02582 0.01853 -0.0558 0.7060 0.9037
3.750 0.6084 0.02541 0.01815 -0.0542 0.6929 0.9121
4.000 0.6756 0.02378 0.01650 -0.0594 0.6889 0.9180
4.250 0.6971 0.02325 0.01600 -0.0578 0.6748 0.9283
4.500 0.7277 0.02257 0.01535 -0.0577 0.6612 0.9384
4.750 0.7664 0.02179 0.01457 -0.0590 0.6473 0.9485
5.000 0.8077 0.02106 0.01385 -0.0608 0.6312 0.9598
5.250 0.8528 0.02043 0.01320 -0.0636 0.6122 0.9718
5.750 0.9361 0.01970 0.01234 -0.0689 0.5650 1.0000
6.000 0.9681 0.01961 0.01207 -0.0700 0.5418 1.0000
6.250 0.9946 0.01987 0.01220 -0.0705 0.5164 1.0000
6.500 1.0278 0.02025 0.01235 -0.0721 0.4924 1.0000
6.750 1.0555 0.02082 0.01279 -0.0729 0.4689 1.0000
7.000 1.0863 0.02144 0.01324 -0.0743 0.4478 1.0000
7.250 1.1173 0.02215 0.01375 -0.0756 0.4285 1.0000
7.500 1.1436 0.02290 0.01441 -0.0761 0.4106 1.0000
7.750 1.1704 0.02368 0.01509 -0.0767 0.3942 1.0000
8.000 1.1982 0.02447 0.01576 -0.0774 0.3793 1.0000
8.250 1.2210 0.02526 0.01652 -0.0772 0.3653 1.0000
8.500 1.2427 0.02608 0.01736 -0.0769 0.3524 1.0000
8.750 1.2667 0.02696 0.01821 -0.0768 0.3408 1.0000
9.000 1.2957 0.02783 0.01895 -0.0776 0.3297 1.0000
9.250 1.3125 0.02867 0.01988 -0.0764 0.3192 1.0000
9.500 1.3351 0.02962 0.02085 -0.0761 0.3097 1.0000
9.750 1.3605 0.03050 0.02167 -0.0763 0.3003 1.0000
10.000 1.3754 0.03150 0.02280 -0.0748 0.2918 1.0000
10.250 1.4063 0.03244 0.02362 -0.0759 0.2830 1.0000
10.500 1.4142 0.03349 0.02490 -0.0733 0.2757 1.0000
10.750 1.4425 0.03442 0.02575 -0.0739 0.2677 1.0000
11.000 1.4510 0.03559 0.02711 -0.0715 0.2610 1.0000
11.250 1.4696 0.03657 0.02814 -0.0707 0.2540 1.0000
11.500 1.4890 0.03782 0.02945 -0.0701 0.2474 1.0000
11.750 1.4946 0.03901 0.03083 -0.0674 0.2413 1.0000
12.000 1.5296 0.04010 0.03178 -0.0691 0.2341 1.0000
12.250 1.5225 0.04154 0.03354 -0.0648 0.2293 1.0000
12.500 1.5341 0.04271 0.03482 -0.0631 0.2235 1.0000
12.750 1.5574 0.04403 0.03613 -0.0632 0.2175 1.0000
13.000 1.5487 0.04574 0.03814 -0.0592 0.2129 1.0000
13.250 1.5600 0.04696 0.03943 -0.0578 0.2076 1.0000
13.500 1.5789 0.04845 0.04094 -0.0574 0.2021 1.0000
13.750 1.5639 0.05063 0.04344 -0.0534 0.1983 1.0000
14.000 1.5654 0.05230 0.04526 -0.0513 0.1936 1.0000
14.250 1.5941 0.05338 0.04625 -0.0519 0.1878 1.0000
14.500 1.5685 0.05641 0.04964 -0.0478 0.1850 1.0000
14.750 1.5529 0.05929 0.05279 -0.0451 0.1814 1.0000
15.000 1.5833 0.05959 0.05296 -0.0455 0.1755 1.0000
15.250 1.5703 0.06283 0.05643 -0.0434 0.1723 1.0000
15.500 1.5341 0.06766 0.06162 -0.0409 0.1703 1.0000
15.750 1.4977 0.07320 0.06748 -0.0394 0.1683 1.0000
16.000 1.4605 0.07953 0.07408 -0.0390 0.1663 1.0000
16.250 1.4318 0.08551 0.08026 -0.0395 0.1638 1.0000
16.500 1.3882 0.09407 0.08903 -0.0415 0.1622 1.0000
16.750 1.3420 0.10419 0.09932 -0.0449 0.1605 1.0000
17.000 0.9839 0.20310 0.19808 -0.0978 0.2040 1.0000
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