BOEING 106 AIRFOIL (boe106-il) Xfoil prediction polar at RE=500,000 Ncrit=9
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Airfoil: BOEING 106 AIRFOIL (boe106-il) Reynolds number: 500,000 Max Cl/Cd: 98.8 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-boe106-il-500000.txt Download as CSV file: xf-boe106-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 -0.7283 0.04296 0.04005 -0.0699 1.0000 0.0242
-10.750 -0.7433 0.03967 0.03652 -0.0678 0.9971 0.0245
-10.500 -0.7308 0.03531 0.03174 -0.0705 0.9918 0.0254
-10.250 -0.7166 0.03115 0.02699 -0.0723 0.9859 0.0265
-10.000 -0.6949 0.02764 0.02300 -0.0743 0.9828 0.0275
-9.750 -0.6672 0.02650 0.02181 -0.0754 0.9781 0.0282
-9.500 -0.6363 0.02566 0.02093 -0.0769 0.9743 0.0289
-9.250 -0.6054 0.02452 0.01964 -0.0784 0.9709 0.0298
-9.000 -0.5803 0.02337 0.01827 -0.0785 0.9637 0.0310
-8.750 -0.5532 0.02256 0.01719 -0.0787 0.9571 0.0319
-8.500 -0.5332 0.02052 0.01495 -0.0780 0.9483 0.0329
-8.250 -0.5085 0.01971 0.01410 -0.0776 0.9410 0.0337
-8.000 -0.4854 0.01910 0.01341 -0.0769 0.9324 0.0346
-7.750 -0.4610 0.01854 0.01275 -0.0762 0.9251 0.0357
-7.500 -0.4373 0.01795 0.01204 -0.0754 0.9166 0.0368
-7.250 -0.4127 0.01742 0.01135 -0.0747 0.9092 0.0376
-7.000 -0.3890 0.01646 0.01025 -0.0740 0.9011 0.0384
-6.750 -0.3654 0.01547 0.00922 -0.0733 0.8937 0.0396
-6.500 -0.3403 0.01501 0.00874 -0.0728 0.8861 0.0408
-6.250 -0.3150 0.01456 0.00822 -0.0723 0.8785 0.0420
-6.000 -0.2894 0.01408 0.00767 -0.0717 0.8713 0.0431
-5.750 -0.2637 0.01367 0.00718 -0.0712 0.8635 0.0441
-5.500 -0.2371 0.01344 0.00685 -0.0708 0.8565 0.0450
-5.250 -0.2139 0.01252 0.00592 -0.0700 0.8485 0.0469
-5.000 -0.1882 0.01213 0.00548 -0.0696 0.8418 0.0484
-4.750 -0.1625 0.01179 0.00513 -0.0691 0.8337 0.0500
-4.500 -0.1363 0.01151 0.00476 -0.0686 0.8268 0.0518
-4.250 -0.1098 0.01128 0.00450 -0.0683 0.8188 0.0534
-4.000 -0.0850 0.01080 0.00398 -0.0677 0.8115 0.0569
-3.750 -0.0588 0.01055 0.00371 -0.0673 0.8035 0.0601
-3.500 -0.0323 0.01031 0.00342 -0.0668 0.7959 0.0642
-3.250 -0.0063 0.01003 0.00317 -0.0664 0.7876 0.0725
-3.000 0.0195 0.00973 0.00295 -0.0659 0.7790 0.0961
-2.750 0.0453 0.00946 0.00280 -0.0655 0.7691 0.1331
-2.500 0.0716 0.00927 0.00264 -0.0651 0.7601 0.1591
-2.250 0.0974 0.00902 0.00250 -0.0647 0.7504 0.1928
-2.000 0.1219 0.00863 0.00239 -0.0642 0.7418 0.2779
-1.750 0.1462 0.00826 0.00230 -0.0636 0.7327 0.3685
-1.500 0.1699 0.00786 0.00222 -0.0629 0.7238 0.4677
-1.250 0.1907 0.00737 0.00217 -0.0614 0.7146 0.6075
-1.000 0.2127 0.00707 0.00219 -0.0600 0.7048 0.7113
-0.750 0.2361 0.00690 0.00220 -0.0588 0.6955 0.7787
-0.500 0.2607 0.00678 0.00224 -0.0577 0.6855 0.8389
-0.250 0.2881 0.00677 0.00232 -0.0571 0.6756 0.8924
0.250 0.3517 0.00696 0.00244 -0.0581 0.6538 0.9423
0.500 0.3848 0.00707 0.00249 -0.0589 0.6428 0.9565
0.750 0.4197 0.00721 0.00254 -0.0603 0.6320 0.9677
1.000 0.4614 0.00732 0.00258 -0.0631 0.6202 0.9741
1.250 0.4999 0.00745 0.00263 -0.0654 0.6085 0.9825
1.500 0.5456 0.00755 0.00265 -0.0692 0.5965 0.9877
1.750 0.5890 0.00767 0.00268 -0.0726 0.5845 0.9943
2.000 0.6345 0.00774 0.00269 -0.0765 0.5725 0.9993
2.250 0.6622 0.00782 0.00272 -0.0767 0.5622 1.0000
2.500 0.6860 0.00793 0.00276 -0.0760 0.5525 1.0000
2.750 0.7098 0.00802 0.00282 -0.0753 0.5415 1.0000
3.000 0.7333 0.00814 0.00289 -0.0745 0.5297 1.0000
3.250 0.7563 0.00827 0.00296 -0.0736 0.5179 1.0000
3.500 0.7791 0.00843 0.00305 -0.0727 0.5063 1.0000
3.750 0.8023 0.00854 0.00315 -0.0718 0.4947 1.0000
4.000 0.8252 0.00868 0.00326 -0.0709 0.4842 1.0000
4.500 0.8706 0.00899 0.00350 -0.0690 0.4627 1.0000
4.750 0.8930 0.00915 0.00363 -0.0680 0.4513 1.0000
5.000 0.9150 0.00934 0.00377 -0.0668 0.4395 1.0000
5.250 0.9364 0.00954 0.00392 -0.0657 0.4258 1.0000
5.500 0.9580 0.00974 0.00408 -0.0645 0.4116 1.0000
5.750 0.9800 0.00993 0.00425 -0.0634 0.3993 1.0000
6.000 1.0018 0.01014 0.00444 -0.0623 0.3883 1.0000
6.250 1.0230 0.01038 0.00464 -0.0611 0.3771 1.0000
6.500 1.0444 0.01061 0.00485 -0.0600 0.3658 1.0000
6.750 1.0665 0.01083 0.00507 -0.0590 0.3552 1.0000
7.000 1.0880 0.01109 0.00531 -0.0579 0.3443 1.0000
7.250 1.1089 0.01139 0.00557 -0.0567 0.3319 1.0000
7.500 1.1300 0.01168 0.00584 -0.0556 0.3181 1.0000
7.750 1.1510 0.01199 0.00612 -0.0545 0.3031 1.0000
8.000 1.1713 0.01235 0.00644 -0.0533 0.2856 1.0000
8.250 1.1906 0.01277 0.00679 -0.0520 0.2609 1.0000
8.500 1.2053 0.01345 0.00727 -0.0501 0.2215 1.0000
8.750 1.2156 0.01440 0.00795 -0.0475 0.1805 1.0000
9.000 1.2279 0.01517 0.00861 -0.0452 0.1601 1.0000
9.250 1.2411 0.01584 0.00922 -0.0431 0.1465 1.0000
9.500 1.2549 0.01649 0.00984 -0.0411 0.1347 1.0000
9.750 1.2683 0.01718 0.01050 -0.0392 0.1238 1.0000
10.250 1.2960 0.01859 0.01187 -0.0357 0.1049 1.0000
10.500 1.3090 0.01938 0.01265 -0.0340 0.0975 1.0000
10.750 1.3222 0.02018 0.01345 -0.0325 0.0911 1.0000
11.000 1.3346 0.02106 0.01435 -0.0309 0.0857 1.0000
11.250 1.3478 0.02190 0.01522 -0.0295 0.0809 1.0000
11.500 1.3568 0.02307 0.01638 -0.0279 0.0766 1.0000
11.750 1.3705 0.02394 0.01733 -0.0267 0.0737 1.0000
12.000 1.3824 0.02498 0.01840 -0.0255 0.0704 1.0000
12.250 1.3907 0.02630 0.01974 -0.0242 0.0671 1.0000
12.500 1.4003 0.02758 0.02108 -0.0230 0.0644 1.0000
12.750 1.4122 0.02871 0.02229 -0.0221 0.0618 1.0000
13.000 1.4210 0.03012 0.02373 -0.0211 0.0591 1.0000
13.250 1.4247 0.03201 0.02564 -0.0199 0.0563 1.0000
13.500 1.4358 0.03330 0.02703 -0.0192 0.0540 1.0000
13.750 1.4448 0.03480 0.02860 -0.0185 0.0511 1.0000
14.000 1.4483 0.03685 0.03067 -0.0177 0.0481 1.0000
14.250 1.4567 0.03848 0.03239 -0.0172 0.0450 1.0000
14.500 1.4611 0.04054 0.03447 -0.0166 0.0413 1.0000
14.750 1.4652 0.04268 0.03666 -0.0161 0.0372 1.0000
15.000 1.4644 0.04539 0.03939 -0.0157 0.0331 1.0000
15.250 1.4643 0.04812 0.04217 -0.0154 0.0294 1.0000
15.500 1.4612 0.05127 0.04538 -0.0152 0.0268 1.0000
15.750 1.4575 0.05457 0.04874 -0.0152 0.0247 1.0000
16.000 1.4505 0.05840 0.05261 -0.0154 0.0233 1.0000
16.250 1.4477 0.06178 0.05611 -0.0157 0.0221 1.0000
16.500 1.4428 0.06551 0.05992 -0.0162 0.0211 1.0000
16.750 1.4355 0.06963 0.06412 -0.0169 0.0203 1.0000
17.000 1.4248 0.07431 0.06888 -0.0177 0.0196 1.0000
17.250 1.4174 0.07858 0.07325 -0.0186 0.0191 1.0000
17.500 1.4113 0.08273 0.07752 -0.0196 0.0185 1.0000
17.750 1.4043 0.08711 0.08201 -0.0207 0.0180 1.0000
18.000 1.3964 0.09167 0.08666 -0.0219 0.0176 1.0000
18.250 1.3875 0.09641 0.09151 -0.0233 0.0172 1.0000
18.500 1.3774 0.10141 0.09660 -0.0249 0.0169 1.0000
18.750 1.3661 0.10669 0.10195 -0.0267 0.0165 1.0000
19.000 1.3540 0.11213 0.10748 -0.0287 0.0162 1.0000
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