BOEING 707 .40 SPAN AIRFOIL (b707c-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: BOEING 707 .40 SPAN AIRFOIL (b707c-il) Reynolds number: 100,000 Max Cl/Cd: 42.39 at α=3.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-b707c-il-100000.txt Download as CSV file: xf-b707c-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: BOEING 707 .40 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.5035 0.09309 0.08798 -0.0348 1.0000 0.0666
-8.750 -0.5208 0.09038 0.08526 -0.0360 1.0000 0.0668
-8.500 -0.5358 0.08816 0.08294 -0.0366 1.0000 0.0670
-8.250 -0.5004 0.08181 0.07683 -0.0333 1.0000 0.0702
-8.000 -0.5021 0.07861 0.07365 -0.0332 1.0000 0.0720
-7.750 -0.5063 0.07541 0.07044 -0.0334 1.0000 0.0739
-7.500 -0.5125 0.07244 0.06740 -0.0336 1.0000 0.0764
-7.250 -0.5289 0.07211 0.06664 -0.0331 1.0000 0.0788
-7.000 -0.5210 0.06658 0.06126 -0.0324 1.0000 0.0803
-6.750 -0.5113 0.06294 0.05774 -0.0310 1.0000 0.0833
-6.500 -0.5067 0.06046 0.05516 -0.0297 1.0000 0.0879
-6.250 -0.5084 0.05931 0.05354 -0.0279 1.0000 0.0927
-6.000 -0.4976 0.05474 0.04921 -0.0268 1.0000 0.0959
-5.750 -0.4935 0.05641 0.05020 -0.0239 1.0000 0.1055
-5.500 -0.4832 0.04982 0.04397 -0.0235 1.0000 0.1085
-5.250 -0.4754 0.05062 0.04422 -0.0208 1.0000 0.1198
-5.000 -0.4643 0.04472 0.03869 -0.0202 1.0000 0.1243
-4.750 -0.4551 0.04255 0.03633 -0.0184 1.0000 0.1369
-4.500 -0.4453 0.04011 0.03381 -0.0168 1.0000 0.1520
-4.250 -0.4355 0.03753 0.03125 -0.0152 1.0000 0.1709
-4.000 -0.4272 0.03520 0.02888 -0.0135 1.0000 0.1989
-3.750 -0.4177 0.03316 0.02677 -0.0117 1.0000 0.2268
-3.500 -0.4076 0.03115 0.02470 -0.0099 1.0000 0.2554
-3.250 -0.3959 0.02887 0.02258 -0.0082 1.0000 0.2776
-3.000 -0.3720 0.02700 0.02069 -0.0085 0.9967 0.3036
-2.750 -0.3203 0.02499 0.01825 -0.0130 0.9870 0.3106
-2.500 -0.2469 0.02542 0.01742 -0.0175 0.9758 0.2076
-2.250 -0.1831 0.02534 0.01662 -0.0195 0.9654 0.1162
-2.000 -0.1294 0.02389 0.01480 -0.0225 0.9580 0.0890
-1.750 -0.0854 0.02272 0.01335 -0.0243 0.9463 0.0787
-1.500 -0.0424 0.02115 0.01185 -0.0269 0.9367 0.0775
-1.250 0.0032 0.01995 0.01069 -0.0297 0.9284 0.0786
-1.000 0.0403 0.01884 0.00970 -0.0311 0.9172 0.0790
-0.750 0.0831 0.01769 0.00864 -0.0338 0.9103 0.0844
-0.500 0.1166 0.01708 0.00800 -0.0346 0.8971 0.0979
-0.250 0.1507 0.01635 0.00728 -0.0353 0.8847 0.1343
0.000 0.3164 0.01331 0.00680 -0.0558 0.8749 1.0000
0.250 0.3459 0.01296 0.00625 -0.0554 0.8375 1.0000
0.500 0.3723 0.01282 0.00595 -0.0550 0.8139 1.0000
0.750 0.3946 0.01276 0.00579 -0.0539 0.7908 1.0000
1.000 0.4167 0.01270 0.00557 -0.0525 0.7651 1.0000
1.250 0.4360 0.01270 0.00546 -0.0507 0.7393 1.0000
1.500 0.4565 0.01275 0.00542 -0.0492 0.7197 1.0000
1.750 0.4768 0.01283 0.00542 -0.0477 0.7016 1.0000
2.000 0.4952 0.01294 0.00541 -0.0456 0.6755 1.0000
2.250 0.5149 0.01307 0.00546 -0.0439 0.6551 1.0000
2.500 0.5334 0.01322 0.00551 -0.0419 0.6273 1.0000
2.750 0.5510 0.01338 0.00556 -0.0396 0.5940 1.0000
3.000 0.5678 0.01353 0.00561 -0.0372 0.5515 1.0000
3.250 0.5829 0.01375 0.00557 -0.0345 0.4731 1.0000
3.500 0.5891 0.01495 0.00565 -0.0306 0.2671 1.0000
3.750 0.6011 0.01621 0.00633 -0.0282 0.1922 1.0000
4.000 0.6163 0.01714 0.00679 -0.0262 0.1148 1.0000
4.250 0.6336 0.01785 0.00744 -0.0244 0.1032 1.0000
4.500 0.6522 0.01844 0.00806 -0.0228 0.0970 1.0000
4.750 0.6695 0.01917 0.00878 -0.0210 0.0929 1.0000
5.000 0.6891 0.01971 0.00940 -0.0195 0.0906 1.0000
5.250 0.7081 0.02031 0.01011 -0.0180 0.0885 1.0000
5.500 0.7267 0.02101 0.01083 -0.0164 0.0847 1.0000
5.750 0.7441 0.02191 0.01170 -0.0148 0.0811 1.0000
6.000 0.7628 0.02301 0.01276 -0.0132 0.0789 1.0000
6.250 0.7843 0.02392 0.01377 -0.0120 0.0748 1.0000
6.500 0.8052 0.02528 0.01507 -0.0111 0.0688 1.0000
6.750 0.8307 0.02717 0.01702 -0.0104 0.0633 1.0000
7.000 0.8553 0.02892 0.01879 -0.0098 0.0590 1.0000
7.250 0.8824 0.03188 0.02173 -0.0099 0.0559 1.0000
7.500 0.9051 0.03396 0.02416 -0.0088 0.0550 1.0000
7.750 0.9263 0.03655 0.02707 -0.0076 0.0550 1.0000
8.000 0.9456 0.03954 0.03035 -0.0064 0.0554 1.0000
8.250 0.9644 0.04369 0.03472 -0.0055 0.0563 1.0000
8.500 0.9716 0.04516 0.03715 -0.0013 0.0604 1.0000
8.750 0.9795 0.04951 0.04194 0.0010 0.0646 1.0000
9.000 0.9763 0.05452 0.04771 0.0047 0.0750 1.0000
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Polar data table (+)
Polar graphs
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