BOEING 106 AIRFOIL (boe106-il) Xfoil prediction polar at RE=200,000 Ncrit=9
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Airfoil: BOEING 106 AIRFOIL (boe106-il) Reynolds number: 200,000 Max Cl/Cd: 72.1 at α=7.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-boe106-il-200000.txt Download as CSV file: xf-boe106-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.2951 0.09062 0.08733 -0.0453 1.0000 0.0762
-9.750 -0.2946 0.08868 0.08543 -0.0434 1.0000 0.0776
-9.500 -0.3951 0.08793 0.08445 -0.0477 1.0000 0.0757
-9.250 -0.3871 0.08603 0.08258 -0.0463 1.0000 0.0772
-9.000 -0.3906 0.08355 0.08016 -0.0457 1.0000 0.0789
-8.750 -0.4083 0.08130 0.07801 -0.0441 1.0000 0.0801
-8.500 -0.4422 0.08010 0.07693 -0.0398 1.0000 0.0801
-8.250 -0.4666 0.07654 0.07342 -0.0420 0.9964 0.0809
-8.000 -0.4759 0.06221 0.05864 -0.0620 0.9829 0.0874
-7.750 -0.4486 0.06003 0.05653 -0.0628 0.9781 0.0892
-7.500 -0.4738 0.04013 0.03507 -0.0684 0.9642 0.0618
-7.250 -0.4511 0.03535 0.02989 -0.0700 0.9586 0.0604
-7.000 -0.4215 0.03099 0.02496 -0.0721 0.9555 0.0596
-6.750 -0.3995 0.02869 0.02224 -0.0716 0.9472 0.0608
-6.500 -0.3658 0.02642 0.01952 -0.0732 0.9433 0.0618
-6.250 -0.3289 0.02467 0.01737 -0.0751 0.9404 0.0627
-6.000 -0.3048 0.02273 0.01526 -0.0748 0.9328 0.0645
-5.750 -0.2713 0.02156 0.01404 -0.0760 0.9280 0.0667
-5.500 -0.2352 0.02043 0.01278 -0.0775 0.9245 0.0686
-5.250 -0.2102 0.01965 0.01190 -0.0768 0.9161 0.0706
-5.000 -0.1781 0.01894 0.01104 -0.0773 0.9107 0.0733
-4.750 -0.1493 0.01782 0.00993 -0.0774 0.9051 0.0763
-4.500 -0.1239 0.01722 0.00934 -0.0767 0.8969 0.0794
-4.250 -0.0937 0.01660 0.00867 -0.0768 0.8918 0.0838
-4.000 -0.0714 0.01604 0.00814 -0.0756 0.8824 0.0890
-3.750 -0.0434 0.01555 0.00764 -0.0753 0.8764 0.0967
-3.500 -0.0206 0.01506 0.00721 -0.0742 0.8674 0.1069
-3.250 0.0056 0.01451 0.00670 -0.0735 0.8606 0.1292
-3.000 0.0271 0.01386 0.00629 -0.0723 0.8515 0.1728
-2.750 0.0510 0.01317 0.00591 -0.0714 0.8443 0.2413
-2.500 0.0707 0.01251 0.00575 -0.0700 0.8348 0.3642
-2.250 0.0902 0.01169 0.00554 -0.0681 0.8274 0.5204
-2.000 0.1067 0.01116 0.00561 -0.0653 0.8171 0.6829
-1.750 0.1317 0.01083 0.00554 -0.0635 0.8100 0.7837
-1.500 0.1598 0.01079 0.00564 -0.0623 0.7993 0.8600
-1.250 0.1978 0.01088 0.00569 -0.0630 0.7910 0.9109
-1.000 0.2365 0.01100 0.00570 -0.0643 0.7813 0.9403
-0.750 0.2790 0.01107 0.00565 -0.0668 0.7718 0.9562
-0.500 0.3299 0.01110 0.00551 -0.0710 0.7630 0.9708
-0.250 0.3819 0.01110 0.00540 -0.0758 0.7521 0.9843
0.000 0.4351 0.01101 0.00518 -0.0810 0.7422 0.9961
0.250 0.4695 0.01093 0.00499 -0.0826 0.7312 1.0000
0.500 0.4928 0.01092 0.00491 -0.0820 0.7196 1.0000
0.750 0.5166 0.01092 0.00481 -0.0813 0.7093 1.0000
1.000 0.5403 0.01094 0.00473 -0.0806 0.6986 1.0000
1.250 0.5634 0.01098 0.00472 -0.0798 0.6869 1.0000
1.500 0.5869 0.01104 0.00470 -0.0790 0.6760 1.0000
1.750 0.6109 0.01110 0.00466 -0.0783 0.6657 1.0000
2.000 0.6339 0.01119 0.00472 -0.0774 0.6540 1.0000
2.250 0.6574 0.01130 0.00477 -0.0766 0.6433 1.0000
2.500 0.6817 0.01141 0.00477 -0.0759 0.6334 1.0000
2.750 0.7043 0.01153 0.00488 -0.0749 0.6215 1.0000
3.000 0.7276 0.01168 0.00498 -0.0740 0.6104 1.0000
3.250 0.7516 0.01183 0.00505 -0.0732 0.6003 1.0000
3.500 0.7744 0.01200 0.00520 -0.0723 0.5891 1.0000
3.750 0.7975 0.01219 0.00536 -0.0713 0.5782 1.0000
4.000 0.8208 0.01238 0.00548 -0.0704 0.5670 1.0000
4.250 0.8435 0.01256 0.00559 -0.0694 0.5546 1.0000
4.500 0.8653 0.01274 0.00577 -0.0682 0.5415 1.0000
4.750 0.8876 0.01296 0.00597 -0.0671 0.5296 1.0000
5.000 0.9105 0.01320 0.00615 -0.0662 0.5191 1.0000
5.250 0.9327 0.01342 0.00634 -0.0651 0.5075 1.0000
5.500 0.9542 0.01364 0.00659 -0.0639 0.4956 1.0000
5.750 0.9764 0.01389 0.00681 -0.0628 0.4846 1.0000
6.000 0.9986 0.01413 0.00699 -0.0618 0.4734 1.0000
6.250 1.0194 0.01433 0.00725 -0.0605 0.4609 1.0000
6.500 1.0403 0.01456 0.00749 -0.0592 0.4484 1.0000
6.750 1.0615 0.01480 0.00773 -0.0580 0.4364 1.0000
7.000 1.0829 0.01507 0.00798 -0.0569 0.4253 1.0000
7.250 1.1036 0.01532 0.00828 -0.0556 0.4130 1.0000
7.500 1.1240 0.01559 0.00859 -0.0544 0.4004 1.0000
7.750 1.1439 0.01588 0.00890 -0.0530 0.3870 1.0000
8.000 1.1631 0.01620 0.00924 -0.0516 0.3729 1.0000
8.250 1.1814 0.01655 0.00961 -0.0501 0.3576 1.0000
8.500 1.1984 0.01694 0.01000 -0.0483 0.3401 1.0000
8.750 1.2132 0.01741 0.01044 -0.0463 0.3197 1.0000
9.000 1.2260 0.01795 0.01097 -0.0440 0.2938 1.0000
9.250 1.2342 0.01866 0.01158 -0.0410 0.2604 1.0000
9.500 1.2367 0.01965 0.01237 -0.0373 0.2236 1.0000
9.750 1.2377 0.02091 0.01343 -0.0338 0.1955 1.0000
10.000 1.2403 0.02226 0.01464 -0.0308 0.1771 1.0000
10.250 1.2439 0.02366 0.01598 -0.0281 0.1636 1.0000
10.500 1.2473 0.02516 0.01740 -0.0257 0.1531 1.0000
10.750 1.2540 0.02653 0.01877 -0.0237 0.1437 1.0000
11.000 1.2611 0.02794 0.02020 -0.0218 0.1360 1.0000
11.250 1.2684 0.02937 0.02162 -0.0202 0.1292 1.0000
11.500 1.2766 0.03079 0.02308 -0.0186 0.1228 1.0000
11.750 1.2849 0.03217 0.02451 -0.0173 0.1168 1.0000
12.000 1.2918 0.03375 0.02607 -0.0159 0.1113 1.0000
12.250 1.3002 0.03516 0.02760 -0.0150 0.1057 1.0000
12.500 1.3056 0.03688 0.02927 -0.0138 0.1009 1.0000
12.750 1.3137 0.03844 0.03096 -0.0128 0.0968 1.0000
13.000 1.3208 0.04009 0.03272 -0.0120 0.0927 1.0000
13.250 1.3259 0.04194 0.03456 -0.0111 0.0891 1.0000
13.500 1.3319 0.04377 0.03648 -0.0102 0.0856 1.0000
13.750 1.3372 0.04570 0.03855 -0.0096 0.0819 1.0000
14.000 1.3405 0.04782 0.04072 -0.0091 0.0786 1.0000
14.250 1.3438 0.04998 0.04289 -0.0084 0.0751 1.0000
14.500 1.3461 0.05239 0.04549 -0.0082 0.0716 1.0000
14.750 1.3471 0.05497 0.04815 -0.0081 0.0682 1.0000
15.000 1.3475 0.05758 0.05076 -0.0077 0.0646 1.0000
15.250 1.3463 0.06065 0.05403 -0.0080 0.0609 1.0000
15.500 1.3443 0.06381 0.05721 -0.0084 0.0576 1.0000
15.750 1.3412 0.06713 0.06062 -0.0085 0.0540 1.0000
16.000 1.3378 0.07071 0.06432 -0.0092 0.0505 1.0000
16.250 1.3350 0.07397 0.06752 -0.0094 0.0476 1.0000
16.500 1.3303 0.07792 0.07168 -0.0102 0.0450 1.0000
16.750 1.3272 0.08162 0.07548 -0.0110 0.0426 1.0000
17.000 1.3250 0.08506 0.07892 -0.0117 0.0407 1.0000
17.250 1.3221 0.08861 0.08258 -0.0121 0.0390 1.0000
17.500 1.3174 0.09275 0.08689 -0.0133 0.0374 1.0000
17.750 1.3139 0.09668 0.09093 -0.0145 0.0360 1.0000
18.000 1.3122 0.10028 0.09456 -0.0156 0.0347 1.0000
18.250 1.3131 0.10312 0.09736 -0.0158 0.0334 1.0000
18.500 1.3048 0.10811 0.10259 -0.0178 0.0326 1.0000
18.750 1.2969 0.11307 0.10774 -0.0198 0.0318 1.0000
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