BOEING 707 .40 SPAN AIRFOIL (b707c-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: BOEING 707 .40 SPAN AIRFOIL (b707c-il) Reynolds number: 50,000 Max Cl/Cd: 30.06 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-b707c-il-50000-n5.txt Download as CSV file: xf-b707c-il-50000-n5.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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.4797 0.09923 0.09200 -0.0234 1.0000 0.1272
-8.750 -0.4932 0.09618 0.08906 -0.0266 1.0000 0.1322
-8.500 -0.5239 0.09366 0.08665 -0.0308 1.0000 0.1340
-8.250 -0.4932 0.08892 0.08196 -0.0269 1.0000 0.1417
-8.000 -0.5053 0.08586 0.07898 -0.0281 1.0000 0.1474
-7.750 -0.5156 0.08227 0.07547 -0.0288 1.0000 0.1546
-7.500 -0.5133 0.07932 0.07256 -0.0280 1.0000 0.1635
-6.500 -0.4195 0.05881 0.05298 -0.0137 1.0000 0.3015
-6.250 -0.4318 0.05516 0.04943 -0.0128 1.0000 0.3096
-6.000 -0.4437 0.05069 0.04501 -0.0136 1.0000 0.2992
-5.750 -0.4585 0.04588 0.04017 -0.0153 1.0000 0.2840
-5.250 -0.4545 0.05232 0.04345 -0.0234 1.0000 0.0879
-5.000 -0.4398 0.04755 0.03891 -0.0226 1.0000 0.0796
-4.750 -0.4230 0.04509 0.03613 -0.0208 1.0000 0.0696
-4.500 -0.4051 0.04311 0.03370 -0.0188 1.0000 0.0620
-4.250 -0.3894 0.04086 0.03128 -0.0173 1.0000 0.0591
-4.000 -0.3717 0.03894 0.02901 -0.0155 1.0000 0.0557
-3.750 -0.3522 0.03823 0.02771 -0.0132 1.0000 0.0532
-3.500 -0.3358 0.03601 0.02544 -0.0119 1.0000 0.0539
-3.250 -0.3182 0.03457 0.02378 -0.0104 1.0000 0.0540
-3.000 -0.3004 0.03323 0.02226 -0.0089 1.0000 0.0540
-2.750 -0.2645 0.03203 0.02070 -0.0104 0.9927 0.0533
-2.500 -0.2244 0.03026 0.01877 -0.0129 0.9831 0.0526
-2.250 -0.1832 0.02874 0.01711 -0.0153 0.9728 0.0523
-2.000 -0.1413 0.02742 0.01570 -0.0176 0.9625 0.0524
-1.750 -0.0990 0.02629 0.01449 -0.0198 0.9520 0.0529
-1.500 -0.0602 0.02520 0.01340 -0.0216 0.9393 0.0539
-1.250 -0.0219 0.02415 0.01231 -0.0236 0.9262 0.0573
-1.000 0.0165 0.02338 0.01140 -0.0256 0.9132 0.0630
-0.750 0.0509 0.02262 0.01063 -0.0270 0.8981 0.0712
-0.500 0.0866 0.02199 0.00998 -0.0284 0.8839 0.0840
-0.250 0.1210 0.02128 0.00931 -0.0295 0.8703 0.1164
0.000 0.2246 0.01843 0.00938 -0.0407 0.8716 0.9908
0.250 0.2664 0.01836 0.00908 -0.0436 0.8573 1.0000
0.500 0.2967 0.01833 0.00890 -0.0442 0.8427 1.0000
0.750 0.3240 0.01835 0.00882 -0.0442 0.8281 1.0000
1.000 0.3504 0.01828 0.00863 -0.0436 0.8060 1.0000
1.250 0.3784 0.01806 0.00822 -0.0426 0.7738 1.0000
1.500 0.4029 0.01796 0.00793 -0.0411 0.7417 1.0000
1.750 0.4268 0.01799 0.00781 -0.0399 0.7188 1.0000
2.000 0.4483 0.01811 0.00786 -0.0384 0.6972 1.0000
2.250 0.4696 0.01824 0.00787 -0.0367 0.6733 1.0000
2.500 0.4912 0.01839 0.00786 -0.0350 0.6479 1.0000
2.750 0.5117 0.01859 0.00802 -0.0335 0.6280 1.0000
3.000 0.5323 0.01881 0.00824 -0.0319 0.6088 1.0000
3.250 0.5511 0.01903 0.00845 -0.0300 0.5818 1.0000
3.500 0.5688 0.01924 0.00868 -0.0279 0.5460 1.0000
3.750 0.5850 0.01946 0.00879 -0.0254 0.4860 1.0000
4.000 0.5991 0.01998 0.00872 -0.0226 0.3773 1.0000
4.250 0.6044 0.02181 0.00925 -0.0194 0.2198 1.0000
4.500 0.6253 0.02234 0.00989 -0.0183 0.1441 1.0000
4.750 0.6368 0.02398 0.01087 -0.0165 0.1042 1.0000
5.000 0.6538 0.02492 0.01180 -0.0151 0.0939 1.0000
5.250 0.6716 0.02572 0.01268 -0.0137 0.0872 1.0000
5.500 0.6880 0.02667 0.01363 -0.0122 0.0823 1.0000
5.750 0.7056 0.02747 0.01457 -0.0107 0.0788 1.0000
6.000 0.7223 0.02836 0.01557 -0.0092 0.0760 1.0000
6.250 0.7384 0.02933 0.01668 -0.0076 0.0734 1.0000
6.500 0.7536 0.03041 0.01782 -0.0060 0.0705 1.0000
6.750 0.7697 0.03152 0.01902 -0.0044 0.0681 1.0000
7.000 0.7877 0.03264 0.02031 -0.0030 0.0657 1.0000
7.250 0.8070 0.03387 0.02169 -0.0018 0.0624 1.0000
7.500 0.8274 0.03529 0.02312 -0.0008 0.0589 1.0000
7.750 0.8528 0.03696 0.02497 -0.0003 0.0551 1.0000
8.000 0.8759 0.03865 0.02685 0.0003 0.0504 1.0000
8.250 0.8997 0.04072 0.02899 0.0006 0.0477 1.0000
8.500 0.9231 0.04338 0.03179 0.0009 0.0455 1.0000
8.750 0.9408 0.04591 0.03480 0.0020 0.0441 1.0000
9.000 0.9553 0.04871 0.03800 0.0034 0.0432 1.0000
9.250 0.9655 0.05165 0.04133 0.0050 0.0427 1.0000
9.500 0.9708 0.05475 0.04482 0.0069 0.0423 1.0000
9.750 0.9715 0.05796 0.04839 0.0089 0.0420 1.0000
10.000 0.9680 0.06122 0.05198 0.0110 0.0419 1.0000
10.250 0.9594 0.06447 0.05552 0.0132 0.0419 1.0000
10.500 0.9462 0.06780 0.05909 0.0154 0.0420 1.0000
10.750 0.9301 0.07146 0.06298 0.0167 0.0421 1.0000
11.000 0.9123 0.07561 0.06731 0.0168 0.0423 1.0000
11.250 0.8917 0.08051 0.07239 0.0156 0.0425 1.0000
11.500 0.8703 0.08623 0.07825 0.0130 0.0428 1.0000
11.750 0.8490 0.09280 0.08494 0.0093 0.0432 1.0000
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Polar data table (+)
Polar graphs
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