BOEING 707 .99 SPAN AIRFOIL (b707e-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: BOEING 707 .99 SPAN AIRFOIL (b707e-il) Reynolds number: 1,000,000 Max Cl/Cd: 75.79 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-b707e-il-1000000-n5.txt Download as CSV file: xf-b707e-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.4835 0.08738 0.08577 -0.0262 1.0000 0.0059
-9.000 -0.4861 0.08312 0.08153 -0.0284 1.0000 0.0061
-8.750 -0.4899 0.07892 0.07735 -0.0309 1.0000 0.0062
-8.500 -0.5021 0.07420 0.07267 -0.0347 1.0000 0.0060
-8.250 -0.5114 0.06914 0.06758 -0.0386 0.9985 0.0062
-8.000 -0.5180 0.05738 0.05561 -0.0466 0.9838 0.0073
-7.750 -0.5035 0.05249 0.05058 -0.0504 0.9732 0.0076
-7.500 -0.4766 0.04894 0.04688 -0.0547 0.9627 0.0077
-7.250 -0.4433 0.04573 0.04352 -0.0597 0.9438 0.0079
-7.000 -0.4162 0.04211 0.03958 -0.0628 0.8882 0.0081
-6.750 -0.4042 0.03982 0.03700 -0.0615 0.8500 0.0084
-6.500 -0.3916 0.03703 0.03396 -0.0601 0.8342 0.0085
-6.250 -0.3763 0.03446 0.03118 -0.0588 0.8242 0.0090
-5.750 -0.3445 0.02781 0.02397 -0.0553 0.8094 0.0099
-5.500 -0.3244 0.02502 0.02090 -0.0537 0.8033 0.0105
-5.250 -0.3029 0.02303 0.01869 -0.0525 0.7981 0.0107
-5.000 -0.2814 0.02099 0.01638 -0.0513 0.7929 0.0110
-4.750 -0.2636 0.01787 0.01289 -0.0497 0.7882 0.0113
-4.500 -0.2408 0.01643 0.01128 -0.0490 0.7840 0.0115
-4.250 -0.2168 0.01495 0.00960 -0.0483 0.7794 0.0116
-4.000 -0.1922 0.01381 0.00828 -0.0477 0.7750 0.0117
-3.750 -0.1669 0.01289 0.00725 -0.0472 0.7707 0.0118
-3.500 -0.1412 0.01229 0.00658 -0.0469 0.7658 0.0122
-3.250 -0.1154 0.01173 0.00595 -0.0466 0.7612 0.0125
-3.000 -0.0894 0.01122 0.00538 -0.0463 0.7570 0.0129
-2.750 -0.0633 0.01076 0.00489 -0.0460 0.7523 0.0134
-2.500 -0.0375 0.01031 0.00439 -0.0456 0.7476 0.0138
-2.250 -0.0118 0.00988 0.00392 -0.0452 0.7429 0.0141
-2.000 0.0137 0.00946 0.00347 -0.0448 0.7366 0.0143
-1.750 0.0389 0.00911 0.00306 -0.0443 0.7299 0.0144
-1.500 0.0646 0.00882 0.00274 -0.0439 0.7222 0.0147
-1.250 0.0902 0.00857 0.00246 -0.0435 0.7148 0.0150
-1.000 0.1150 0.00830 0.00212 -0.0429 0.6992 0.0150
-0.750 0.1388 0.00815 0.00181 -0.0420 0.6672 0.0149
-0.500 0.1637 0.00801 0.00157 -0.0414 0.6468 0.0148
-0.250 0.1887 0.00793 0.00137 -0.0408 0.6215 0.0148
0.000 0.2133 0.00793 0.00122 -0.0402 0.5869 0.0148
0.250 0.2357 0.00816 0.00112 -0.0392 0.5052 0.0149
0.500 0.2547 0.00880 0.00121 -0.0377 0.3657 0.0150
0.750 0.2747 0.00941 0.00131 -0.0365 0.2380 0.0152
1.000 0.2975 0.00977 0.00136 -0.0357 0.1603 0.0156
1.250 0.3183 0.01037 0.00154 -0.0346 0.0380 0.0161
1.500 0.3447 0.01041 0.00156 -0.0343 0.0311 0.0192
1.750 0.3704 0.01035 0.00164 -0.0340 0.0300 0.0892
2.000 0.3852 0.00900 0.00167 -0.0321 0.0294 0.6247
2.250 0.4080 0.00883 0.00178 -0.0311 0.0288 0.7048
2.500 0.4230 0.00833 0.00195 -0.0281 0.0285 0.8912
2.750 0.4626 0.00841 0.00214 -0.0308 0.0282 0.9531
3.000 0.4990 0.00858 0.00231 -0.0329 0.0278 0.9642
3.250 0.5336 0.00876 0.00248 -0.0346 0.0275 0.9721
3.500 0.5674 0.00895 0.00267 -0.0361 0.0268 0.9780
3.750 0.5982 0.00917 0.00287 -0.0370 0.0254 0.9835
4.000 0.6298 0.00939 0.00310 -0.0381 0.0247 0.9880
4.250 0.6592 0.00969 0.00343 -0.0387 0.0231 0.9927
4.500 0.6905 0.00973 0.00342 -0.0397 0.0225 0.9962
4.750 0.7224 0.00982 0.00347 -0.0408 0.0211 0.9987
5.000 0.7521 0.00997 0.00354 -0.0415 0.0113 1.0000
5.250 0.7738 0.01024 0.00375 -0.0404 0.0079 1.0000
5.500 0.7958 0.01050 0.00405 -0.0393 0.0071 1.0000
5.750 0.8174 0.01080 0.00439 -0.0382 0.0062 1.0000
6.000 0.8387 0.01115 0.00477 -0.0370 0.0055 1.0000
6.250 0.8602 0.01149 0.00515 -0.0359 0.0051 1.0000
6.500 0.8821 0.01179 0.00548 -0.0348 0.0049 1.0000
6.750 0.9038 0.01212 0.00586 -0.0338 0.0046 1.0000
7.000 0.9249 0.01250 0.00628 -0.0326 0.0043 1.0000
7.250 0.9459 0.01290 0.00672 -0.0314 0.0040 1.0000
7.500 0.9663 0.01335 0.00722 -0.0302 0.0038 1.0000
7.750 0.9863 0.01384 0.00775 -0.0289 0.0036 1.0000
8.000 1.0059 0.01438 0.00835 -0.0276 0.0034 1.0000
8.250 1.0233 0.01511 0.00915 -0.0259 0.0032 1.0000
8.500 1.0380 0.01608 0.01022 -0.0238 0.0030 1.0000
8.750 1.0586 0.01649 0.01068 -0.0227 0.0029 1.0000
9.000 1.0761 0.01719 0.01145 -0.0212 0.0029 1.0000
9.250 1.0931 0.01792 0.01227 -0.0195 0.0028 1.0000
9.500 1.1109 0.01854 0.01297 -0.0181 0.0028 1.0000
9.750 1.1253 0.01946 0.01400 -0.0161 0.0027 1.0000
10.000 1.1407 0.02026 0.01489 -0.0144 0.0026 1.0000
10.250 1.1538 0.02122 0.01597 -0.0123 0.0026 1.0000
10.500 1.1661 0.02209 0.01694 -0.0101 0.0025 1.0000
10.750 1.1741 0.02315 0.01811 -0.0072 0.0025 1.0000
11.000 1.1819 0.02420 0.01929 -0.0044 0.0024 1.0000
11.250 1.1889 0.02535 0.02057 -0.0017 0.0024 1.0000
11.500 1.1955 0.02655 0.02190 0.0008 0.0023 1.0000
11.750 1.2012 0.02784 0.02331 0.0032 0.0023 1.0000
12.000 1.2035 0.02948 0.02513 0.0057 0.0022 1.0000
12.250 1.2068 0.03104 0.02683 0.0078 0.0022 1.0000
12.500 1.2054 0.03312 0.02908 0.0099 0.0022 1.0000
12.750 1.2035 0.03534 0.03146 0.0116 0.0021 1.0000
13.000 1.2098 0.03677 0.03298 0.0124 0.0020 1.0000
13.250 1.2097 0.03897 0.03530 0.0134 0.0020 1.0000
13.500 1.2053 0.04174 0.03822 0.0141 0.0019 1.0000
13.750 1.1870 0.04640 0.04312 0.0145 0.0020 1.0000
14.000 1.1869 0.04902 0.04584 0.0142 0.0019 1.0000
14.250 1.1709 0.05399 0.05100 0.0132 0.0019 1.0000
14.500 1.1779 0.05603 0.05307 0.0123 0.0018 1.0000
14.750 1.1521 0.06312 0.06039 0.0096 0.0019 1.0000
15.000 1.1458 0.06776 0.06512 0.0072 0.0018 1.0000
15.250 1.1102 0.07841 0.07602 0.0014 0.0019 1.0000
15.500 1.0896 0.08731 0.08507 -0.0040 0.0019 1.0000
15.750 1.0358 0.10434 0.10236 -0.0135 0.0020 1.0000
16.000 1.0358 0.10904 0.10707 -0.0160 0.0019 1.0000
16.250 1.0022 0.12176 0.11991 -0.0226 0.0019 1.0000
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Polar data table (+)
Polar graphs
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