BOEING 707 .99 SPAN AIRFOIL (b707e-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: BOEING 707 .99 SPAN AIRFOIL (b707e-il) Reynolds number: 50,000 Max Cl/Cd: 36.96 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-b707e-il-50000.txt Download as CSV file: xf-b707e-il-50000.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 = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.4643 0.10555 0.09868 -0.0153 1.0000 0.2242
-8.750 -0.4641 0.10273 0.09592 -0.0150 1.0000 0.2416
-8.500 -0.4691 0.10030 0.09359 -0.0149 1.0000 0.2580
-8.250 -0.4584 0.09685 0.09013 -0.0127 1.0000 0.2848
-8.000 -0.4518 0.09390 0.08723 -0.0107 1.0000 0.3125
-7.750 -0.4512 0.09154 0.08494 -0.0086 1.0000 0.3425
-7.500 -0.4568 0.08973 0.08324 -0.0061 1.0000 0.3724
-7.250 -0.4116 0.08536 0.07875 -0.0011 1.0000 0.4384
-7.000 -0.3941 0.08298 0.07638 0.0030 1.0000 0.4975
-6.750 -0.3651 0.07990 0.07324 0.0069 1.0000 0.5682
-6.500 -0.3320 0.07634 0.06964 0.0093 1.0000 0.6397
-6.250 -0.2926 0.07235 0.06559 0.0106 1.0000 0.7264
-6.000 -0.2415 0.06639 0.05956 0.0068 1.0000 0.7887
-5.750 -0.2270 0.06350 0.05667 0.0065 1.0000 0.8140
-5.500 -0.2213 0.06094 0.05416 0.0066 1.0000 0.8146
-4.750 -0.3284 0.05815 0.05209 0.0160 1.0000 0.6589
-4.500 -0.3866 0.05724 0.05153 0.0215 1.0000 0.6154
-4.250 -0.4411 0.05568 0.05028 0.0253 1.0000 0.5821
-4.000 -0.4918 0.05109 0.04576 0.0182 1.0000 0.5131
-3.750 -0.4328 0.03966 0.03198 -0.0161 1.0000 0.2739
-3.500 -0.4025 0.03715 0.02880 -0.0167 1.0000 0.2275
-3.250 -0.3760 0.03530 0.02631 -0.0161 1.0000 0.1991
-3.000 -0.3495 0.03436 0.02455 -0.0149 1.0000 0.1749
-2.750 -0.3252 0.03262 0.02245 -0.0137 1.0000 0.1594
-2.500 -0.3009 0.03164 0.02093 -0.0123 1.0000 0.1466
-2.250 -0.2773 0.02983 0.01902 -0.0114 1.0000 0.1398
-2.000 -0.2535 0.02933 0.01797 -0.0100 1.0000 0.1324
-1.750 -0.2300 0.02798 0.01657 -0.0091 1.0000 0.1291
-1.500 -0.2063 0.02703 0.01550 -0.0080 1.0000 0.1260
-1.250 -0.1823 0.02630 0.01465 -0.0070 1.0000 0.1239
-1.000 -0.1594 0.02572 0.01393 -0.0059 1.0000 0.1231
-0.750 -0.1378 0.02522 0.01330 -0.0048 1.0000 0.1236
-0.500 -0.1177 0.02480 0.01279 -0.0037 1.0000 0.1275
-0.250 -0.0978 0.02445 0.01235 -0.0027 1.0000 0.1347
0.000 -0.0772 0.02411 0.01194 -0.0020 1.0000 0.1454
0.250 -0.0555 0.02380 0.01160 -0.0015 1.0000 0.1596
0.500 -0.0344 0.02151 0.01171 -0.0005 1.0000 0.6890
0.750 0.0082 0.02128 0.01154 -0.0028 1.0000 1.0000
1.000 0.0267 0.02171 0.01155 -0.0018 1.0000 1.0000
1.250 0.0448 0.02216 0.01173 -0.0011 1.0000 1.0000
1.500 0.0629 0.02265 0.01202 -0.0005 1.0000 1.0000
1.750 0.0809 0.02317 0.01237 0.0001 1.0000 1.0000
2.000 0.0989 0.02372 0.01279 0.0006 1.0000 1.0000
2.250 0.1167 0.02432 0.01329 0.0010 1.0000 1.0000
2.500 0.1344 0.02496 0.01386 0.0013 1.0000 1.0000
2.750 0.1518 0.02564 0.01449 0.0017 1.0000 1.0000
3.000 0.1904 0.02687 0.01572 -0.0023 0.9898 1.0000
3.250 0.2546 0.02855 0.01746 -0.0109 0.9650 1.0000
3.500 0.3161 0.02983 0.01885 -0.0182 0.9394 1.0000
3.750 0.3658 0.03075 0.01994 -0.0231 0.9165 1.0000
4.000 0.4124 0.03151 0.02088 -0.0271 0.8930 1.0000
4.250 0.4652 0.03207 0.02172 -0.0315 0.8675 1.0000
4.500 0.5383 0.03168 0.02172 -0.0374 0.8320 1.0000
4.750 0.6365 0.02925 0.01994 -0.0440 0.7890 1.0000
5.000 0.6882 0.02798 0.01907 -0.0446 0.7575 1.0000
5.250 0.7293 0.02649 0.01793 -0.0429 0.7204 1.0000
5.500 0.7659 0.02464 0.01637 -0.0399 0.6772 1.0000
5.750 0.7923 0.02348 0.01547 -0.0363 0.6294 1.0000
6.000 0.8120 0.02259 0.01460 -0.0319 0.5644 1.0000
6.250 0.8257 0.02234 0.01405 -0.0271 0.4760 1.0000
6.500 0.8355 0.02330 0.01437 -0.0228 0.3833 1.0000
6.750 0.8354 0.02563 0.01580 -0.0180 0.2774 1.0000
7.000 0.8491 0.02865 0.01805 -0.0153 0.1994 1.0000
7.250 0.8734 0.03076 0.02008 -0.0142 0.1641 1.0000
7.500 0.8890 0.03242 0.02163 -0.0123 0.1341 1.0000
7.750 0.9085 0.03454 0.02368 -0.0108 0.1094 1.0000
8.000 0.9386 0.03784 0.02710 -0.0103 0.0960 1.0000
8.250 0.9653 0.04165 0.03102 -0.0099 0.0895 1.0000
8.500 0.9807 0.04498 0.03499 -0.0078 0.0861 1.0000
8.750 0.9925 0.04840 0.03887 -0.0058 0.0826 1.0000
9.000 1.0019 0.05208 0.04294 -0.0038 0.0808 1.0000
9.250 1.0024 0.05636 0.04777 -0.0012 0.0817 1.0000
9.500 0.9967 0.06087 0.05277 0.0015 0.0833 1.0000
9.750 0.9878 0.06529 0.05755 0.0038 0.0848 1.0000
10.000 0.9745 0.06973 0.06234 0.0059 0.0864 1.0000
10.250 0.9604 0.07394 0.06667 0.0077 0.0877 1.0000
10.500 0.9482 0.07827 0.07117 0.0091 0.0890 1.0000
10.750 0.9462 0.08326 0.07623 0.0096 0.0908 1.0000
11.000 0.8955 0.08808 0.08118 0.0080 0.0922 1.0000
11.250 0.8385 0.09901 0.09214 -0.0009 0.0981 1.0000
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Polar data table (+)
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