BOEING 707 .99 SPAN AIRFOIL (b707e-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: BOEING 707 .99 SPAN AIRFOIL (b707e-il) Reynolds number: 100,000 Max Cl/Cd: 48.47 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-b707e-il-100000-n5.txt Download as CSV file: xf-b707e-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: BOEING 707 .99 SPAN 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
------ -------- --------- --------- -------- -------- --------
-8.750 -0.4754 0.09330 0.08842 -0.0369 1.0000 0.0480
-8.500 -0.4848 0.09029 0.08543 -0.0384 1.0000 0.0481
-8.250 -0.4933 0.08748 0.08257 -0.0396 1.0000 0.0483
-8.000 -0.4992 0.08471 0.07971 -0.0400 1.0000 0.0484
-7.750 -0.5024 0.08190 0.07679 -0.0397 1.0000 0.0485
-7.500 -0.4906 0.07423 0.06940 -0.0388 1.0000 0.0500
-7.250 -0.4866 0.07078 0.06598 -0.0377 1.0000 0.0511
-7.000 -0.4843 0.06765 0.06284 -0.0369 1.0000 0.0523
-6.750 -0.4825 0.06458 0.05973 -0.0361 1.0000 0.0539
-6.500 -0.4801 0.06165 0.05673 -0.0351 1.0000 0.0555
-6.250 -0.4773 0.05886 0.05382 -0.0339 1.0000 0.0578
-6.000 -0.4775 0.05973 0.05401 -0.0311 1.0000 0.0620
-5.750 -0.4759 0.05497 0.04930 -0.0294 1.0000 0.0630
-5.500 -0.4584 0.05024 0.04462 -0.0305 0.9959 0.0649
-5.250 -0.4322 0.04690 0.04115 -0.0328 0.9885 0.0700
-5.000 -0.4055 0.04367 0.03763 -0.0352 0.9808 0.0815
-4.750 -0.3792 0.04084 0.03448 -0.0370 0.9723 0.0939
-4.500 -0.3372 0.03673 0.02952 -0.0365 0.9656 0.0465
-4.250 -0.3089 0.03343 0.02596 -0.0375 0.9585 0.0423
-4.000 -0.2770 0.03067 0.02257 -0.0377 0.9516 0.0378
-3.500 -0.2113 0.02748 0.01857 -0.0390 0.9393 0.0350
-3.250 -0.1815 0.02567 0.01645 -0.0395 0.9322 0.0361
-3.000 -0.1486 0.02367 0.01431 -0.0410 0.9278 0.0380
-2.750 -0.1196 0.02241 0.01282 -0.0410 0.9200 0.0379
-2.500 -0.0856 0.02119 0.01143 -0.0420 0.9151 0.0373
-2.250 -0.0553 0.02019 0.01033 -0.0423 0.9082 0.0370
-2.000 -0.0233 0.01921 0.00929 -0.0430 0.9025 0.0369
-1.750 0.0067 0.01834 0.00839 -0.0434 0.8965 0.0370
-1.500 0.0346 0.01758 0.00765 -0.0435 0.8899 0.0375
-1.250 0.0639 0.01695 0.00698 -0.0438 0.8843 0.0381
-1.000 0.0904 0.01651 0.00646 -0.0436 0.8769 0.0392
-0.750 0.1217 0.01610 0.00591 -0.0443 0.8720 0.0412
-0.500 0.1479 0.01588 0.00558 -0.0439 0.8643 0.0440
-0.250 0.1786 0.01558 0.00523 -0.0445 0.8590 0.0538
0.000 0.2032 0.01435 0.00494 -0.0445 0.8520 0.3538
0.250 0.3122 0.01276 0.00527 -0.0587 0.8580 0.9888
0.500 0.3525 0.01276 0.00518 -0.0617 0.8512 1.0000
0.750 0.3788 0.01277 0.00510 -0.0616 0.8440 1.0000
1.000 0.4007 0.01285 0.00511 -0.0606 0.8336 1.0000
1.250 0.4239 0.01290 0.00509 -0.0597 0.8219 1.0000
1.500 0.4469 0.01295 0.00508 -0.0585 0.8090 1.0000
1.750 0.4691 0.01299 0.00506 -0.0572 0.7941 1.0000
2.000 0.4906 0.01295 0.00494 -0.0553 0.7725 1.0000
2.250 0.5084 0.01289 0.00477 -0.0526 0.7421 1.0000
2.500 0.5271 0.01284 0.00465 -0.0503 0.7118 1.0000
2.750 0.5474 0.01285 0.00460 -0.0485 0.6844 1.0000
3.000 0.5681 0.01290 0.00461 -0.0468 0.6557 1.0000
3.250 0.5902 0.01300 0.00467 -0.0454 0.6330 1.0000
3.500 0.6120 0.01313 0.00479 -0.0441 0.6072 1.0000
3.750 0.6336 0.01329 0.00493 -0.0427 0.5771 1.0000
4.000 0.6544 0.01350 0.00508 -0.0412 0.5327 1.0000
4.250 0.6700 0.01403 0.00517 -0.0386 0.4374 1.0000
4.500 0.6851 0.01475 0.00550 -0.0363 0.3632 1.0000
4.750 0.7028 0.01538 0.00594 -0.0346 0.3134 1.0000
5.000 0.7214 0.01597 0.00641 -0.0330 0.2777 1.0000
5.250 0.7400 0.01659 0.00691 -0.0315 0.2429 1.0000
5.500 0.7580 0.01728 0.00749 -0.0300 0.1972 1.0000
5.750 0.7766 0.01795 0.00803 -0.0286 0.1557 1.0000
6.000 0.7943 0.01874 0.00865 -0.0271 0.1058 1.0000
6.250 0.8101 0.01979 0.00942 -0.0253 0.0715 1.0000
6.500 0.8274 0.02072 0.01023 -0.0238 0.0544 1.0000
6.750 0.8460 0.02152 0.01111 -0.0224 0.0486 1.0000
7.000 0.8619 0.02264 0.01232 -0.0207 0.0425 1.0000
7.250 0.8781 0.02371 0.01357 -0.0189 0.0371 1.0000
7.500 0.8888 0.02533 0.01530 -0.0166 0.0310 1.0000
7.750 0.9030 0.02665 0.01683 -0.0146 0.0265 1.0000
8.000 0.9145 0.02835 0.01857 -0.0124 0.0238 1.0000
8.250 0.9298 0.03006 0.02041 -0.0106 0.0220 1.0000
8.500 0.9483 0.03178 0.02233 -0.0092 0.0206 1.0000
8.750 0.9670 0.03373 0.02455 -0.0080 0.0191 1.0000
9.000 0.9830 0.03536 0.02637 -0.0066 0.0175 1.0000
9.250 0.9953 0.03684 0.02791 -0.0052 0.0162 1.0000
9.500 1.0099 0.03918 0.03064 -0.0036 0.0152 1.0000
9.750 1.0210 0.04182 0.03363 -0.0017 0.0148 1.0000
10.000 1.0270 0.04472 0.03690 0.0006 0.0144 1.0000
10.250 1.0280 0.04756 0.04009 0.0032 0.0143 1.0000
10.500 1.0232 0.05039 0.04324 0.0062 0.0142 1.0000
10.750 1.0145 0.05336 0.04651 0.0091 0.0141 1.0000
11.000 1.0028 0.05657 0.05001 0.0115 0.0141 1.0000
11.250 0.9893 0.06004 0.05373 0.0130 0.0141 1.0000
11.500 0.9730 0.06404 0.05797 0.0135 0.0141 1.0000
11.750 0.9562 0.06842 0.06257 0.0131 0.0142 1.0000
12.000 0.9373 0.07355 0.06789 0.0116 0.0142 1.0000
12.250 0.9183 0.07930 0.07382 0.0089 0.0144 1.0000
12.500 0.8968 0.08637 0.08105 0.0047 0.0144 1.0000
12.750 0.8764 0.09445 0.08925 -0.0008 0.0146 1.0000
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Polar data table (+)
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