BOEING 106 AIRFOIL (boe106-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: BOEING 106 AIRFOIL (boe106-il) Reynolds number: 100,000 Max Cl/Cd: 52.76 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-boe106-il-100000-n5.txt Download as CSV file: xf-boe106-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: BOEING 106 AIRFOIL
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 -0.4166 0.09011 0.08495 -0.0482 1.0000 0.0445
-10.000 -0.4270 0.08432 0.07922 -0.0512 1.0000 0.0444
-9.750 -0.4448 0.07749 0.07248 -0.0551 1.0000 0.0444
-9.500 -0.4770 0.06959 0.06469 -0.0601 1.0000 0.0440
-9.250 -0.5158 0.06588 0.06103 -0.0578 1.0000 0.0435
-9.000 -0.5520 0.06248 0.05760 -0.0541 1.0000 0.0432
-8.750 -0.5677 0.05439 0.04908 -0.0583 0.9906 0.0439
-8.500 -0.5705 0.04649 0.04037 -0.0618 0.9794 0.0453
-8.250 -0.5562 0.04157 0.03481 -0.0639 0.9723 0.0464
-8.000 -0.5352 0.03923 0.03227 -0.0646 0.9646 0.0474
-7.750 -0.5058 0.03742 0.03027 -0.0666 0.9599 0.0491
-7.500 -0.4833 0.03538 0.02791 -0.0670 0.9521 0.0510
-7.250 -0.4555 0.03279 0.02481 -0.0683 0.9467 0.0528
-7.000 -0.4302 0.03067 0.02220 -0.0686 0.9397 0.0541
-6.750 -0.4022 0.02896 0.02019 -0.0693 0.9331 0.0560
-6.500 -0.3687 0.02770 0.01884 -0.0709 0.9288 0.0581
-6.250 -0.3444 0.02659 0.01757 -0.0704 0.9200 0.0597
-6.000 -0.3125 0.02534 0.01612 -0.0714 0.9146 0.0615
-5.750 -0.2845 0.02436 0.01492 -0.0714 0.9076 0.0639
-5.500 -0.2559 0.02341 0.01385 -0.0716 0.9008 0.0664
-5.250 -0.2237 0.02253 0.01298 -0.0726 0.8961 0.0692
-5.000 -0.2003 0.02188 0.01228 -0.0717 0.8869 0.0716
-4.750 -0.1699 0.02113 0.01144 -0.0721 0.8813 0.0749
-4.500 -0.1458 0.02056 0.01085 -0.0714 0.8727 0.0789
-4.250 -0.1174 0.02003 0.01030 -0.0714 0.8663 0.0848
-4.000 -0.0926 0.01953 0.00978 -0.0708 0.8582 0.0912
-3.750 -0.0656 0.01903 0.00927 -0.0705 0.8510 0.1004
-3.500 -0.0403 0.01858 0.00885 -0.0699 0.8431 0.1152
-3.250 -0.0143 0.01811 0.00843 -0.0695 0.8355 0.1372
-3.000 0.0110 0.01765 0.00805 -0.0690 0.8277 0.1664
-2.750 0.0358 0.01713 0.00774 -0.0684 0.8196 0.2085
-2.500 0.0600 0.01658 0.00751 -0.0678 0.8116 0.2876
-2.250 0.0831 0.01595 0.00732 -0.0669 0.8033 0.3995
-1.750 0.1275 0.01475 0.00737 -0.0631 0.7869 0.7320
-1.500 0.1588 0.01465 0.00739 -0.0627 0.7787 0.8112
-1.250 0.1955 0.01462 0.00731 -0.0635 0.7702 0.8618
-1.000 0.2354 0.01466 0.00726 -0.0652 0.7607 0.9020
-0.750 0.2795 0.01466 0.00711 -0.0677 0.7520 0.9384
-0.500 0.3274 0.01470 0.00702 -0.0714 0.7407 0.9656
-0.250 0.3804 0.01463 0.00679 -0.0763 0.7305 0.9866
0.000 0.4283 0.01452 0.00653 -0.0805 0.7201 1.0000
0.250 0.4495 0.01455 0.00647 -0.0794 0.7085 1.0000
0.500 0.4717 0.01458 0.00639 -0.0784 0.6981 1.0000
0.750 0.4944 0.01460 0.00631 -0.0775 0.6880 1.0000
1.000 0.5160 0.01469 0.00632 -0.0764 0.6765 1.0000
1.250 0.5386 0.01476 0.00630 -0.0754 0.6662 1.0000
1.500 0.5616 0.01484 0.00628 -0.0744 0.6561 1.0000
1.750 0.5836 0.01496 0.00636 -0.0734 0.6449 1.0000
2.000 0.6066 0.01508 0.00640 -0.0724 0.6348 1.0000
2.250 0.6296 0.01520 0.00644 -0.0715 0.6247 1.0000
2.500 0.6519 0.01536 0.00657 -0.0704 0.6138 1.0000
2.750 0.6751 0.01551 0.00665 -0.0695 0.6039 1.0000
3.000 0.6980 0.01568 0.00677 -0.0685 0.5938 1.0000
3.250 0.7205 0.01588 0.00695 -0.0675 0.5837 1.0000
3.500 0.7442 0.01606 0.00705 -0.0667 0.5747 1.0000
3.750 0.7664 0.01628 0.00729 -0.0657 0.5641 1.0000
4.000 0.7894 0.01651 0.00749 -0.0647 0.5545 1.0000
4.250 0.8129 0.01674 0.00768 -0.0639 0.5454 1.0000
4.500 0.8354 0.01701 0.00798 -0.0630 0.5359 1.0000
4.750 0.8597 0.01726 0.00817 -0.0622 0.5276 1.0000
5.000 0.8812 0.01755 0.00850 -0.0611 0.5162 1.0000
5.250 0.9034 0.01782 0.00877 -0.0601 0.5049 1.0000
5.500 0.9259 0.01808 0.00900 -0.0591 0.4935 1.0000
5.750 0.9472 0.01836 0.00928 -0.0579 0.4811 1.0000
6.000 0.9681 0.01866 0.00961 -0.0567 0.4684 1.0000
6.250 0.9892 0.01896 0.00995 -0.0556 0.4563 1.0000
6.500 1.0101 0.01927 0.01026 -0.0544 0.4439 1.0000
6.750 1.0310 0.01958 0.01057 -0.0532 0.4320 1.0000
7.000 1.0509 0.01993 0.01100 -0.0519 0.4194 1.0000
7.250 1.0704 0.02029 0.01141 -0.0506 0.4063 1.0000
7.500 1.0891 0.02067 0.01181 -0.0492 0.3921 1.0000
7.750 1.1069 0.02108 0.01223 -0.0476 0.3771 1.0000
8.000 1.1237 0.02152 0.01271 -0.0459 0.3613 1.0000
8.250 1.1396 0.02201 0.01322 -0.0441 0.3450 1.0000
8.500 1.1546 0.02255 0.01378 -0.0423 0.3282 1.0000
8.750 1.1679 0.02316 0.01439 -0.0402 0.3102 1.0000
9.000 1.1791 0.02384 0.01507 -0.0379 0.2907 1.0000
9.250 1.1882 0.02457 0.01583 -0.0353 0.2681 1.0000
9.500 1.1944 0.02550 0.01671 -0.0326 0.2430 1.0000
9.750 1.1983 0.02666 0.01776 -0.0298 0.2172 1.0000
10.000 1.2013 0.02802 0.01900 -0.0272 0.1957 1.0000
10.250 1.2038 0.02952 0.02042 -0.0249 0.1803 1.0000
10.500 1.2069 0.03110 0.02198 -0.0228 0.1685 1.0000
10.750 1.2090 0.03283 0.02367 -0.0208 0.1591 1.0000
11.000 1.2137 0.03446 0.02536 -0.0192 0.1501 1.0000
11.250 1.2169 0.03627 0.02718 -0.0176 0.1430 1.0000
11.500 1.2221 0.03799 0.02899 -0.0163 0.1360 1.0000
11.750 1.2242 0.03998 0.03095 -0.0149 0.1307 1.0000
12.000 1.2314 0.04165 0.03279 -0.0138 0.1251 1.0000
12.250 1.2360 0.04355 0.03475 -0.0128 0.1202 1.0000
12.500 1.2399 0.04553 0.03671 -0.0118 0.1161 1.0000
12.750 1.2469 0.04733 0.03868 -0.0109 0.1115 1.0000
13.000 1.2523 0.04928 0.04071 -0.0101 0.1075 1.0000
13.250 1.2572 0.05125 0.04269 -0.0093 0.1042 1.0000
13.500 1.2641 0.05313 0.04470 -0.0086 0.1009 1.0000
13.750 1.2690 0.05526 0.04698 -0.0080 0.0971 1.0000
14.000 1.2712 0.05762 0.04942 -0.0077 0.0934 1.0000
14.250 1.2728 0.06006 0.05187 -0.0074 0.0899 1.0000
14.500 1.2728 0.06292 0.05496 -0.0075 0.0858 1.0000
14.750 1.2712 0.06597 0.05812 -0.0079 0.0820 1.0000
15.000 1.2694 0.06901 0.06113 -0.0082 0.0787 1.0000
15.250 1.2675 0.07240 0.06477 -0.0088 0.0751 1.0000
15.500 1.2657 0.07576 0.06830 -0.0094 0.0720 1.0000
15.750 1.2629 0.07928 0.07189 -0.0102 0.0693 1.0000
16.000 1.2605 0.08277 0.07546 -0.0109 0.0668 1.0000
16.250 1.2566 0.08672 0.07964 -0.0119 0.0639 1.0000
16.500 1.2517 0.09083 0.08390 -0.0132 0.0612 1.0000
16.750 1.2464 0.09504 0.08819 -0.0147 0.0589 1.0000
17.000 1.2408 0.09934 0.09258 -0.0161 0.0565 1.0000
17.250 1.2324 0.10437 0.09785 -0.0180 0.0540 1.0000
17.500 1.2242 0.10939 0.10302 -0.0201 0.0516 1.0000
17.750 1.2170 0.11430 0.10800 -0.0223 0.0496 1.0000
18.000 1.2090 0.11941 0.11319 -0.0246 0.0476 1.0000
18.250 1.1958 0.12583 0.11986 -0.0278 0.0455 1.0000
18.500 1.1837 0.13212 0.12631 -0.0310 0.0437 1.0000
18.750 1.1747 0.13791 0.13217 -0.0342 0.0419 1.0000
19.000 1.1683 0.14313 0.13741 -0.0371 0.0404 1.0000
19.250 1.1475 0.15207 0.14660 -0.0422 0.0392 1.0000
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Polar data table (+)
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