BOEING 707 .19 SPAN AIRFOIL (b707b-il) Xfoil prediction polar at RE=50,000 Ncrit=9
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Airfoil: BOEING 707 .19 SPAN AIRFOIL (b707b-il) Reynolds number: 50,000 Max Cl/Cd: 24.73 at α=3.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-b707b-il-50000.txt Download as CSV file: xf-b707b-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: BOEING 707 .19 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
------ -------- --------- --------- -------- -------- --------
-9.500 -0.6550 0.08582 0.07952 -0.0062 1.0000 0.2047
-9.250 -0.7292 0.07555 0.06929 -0.0125 1.0000 0.1866
-9.000 -0.7643 0.06968 0.06325 -0.0124 1.0000 0.1728
-8.750 -0.7861 0.06454 0.05777 -0.0114 1.0000 0.1603
-8.500 -0.8059 0.06044 0.05304 -0.0090 1.0000 0.1491
-8.250 -0.7938 0.05611 0.04857 -0.0085 1.0000 0.1433
-8.000 -0.8021 0.05360 0.04512 -0.0049 1.0000 0.1352
-7.750 -0.7821 0.04972 0.04118 -0.0048 1.0000 0.1327
-7.500 -0.7674 0.04676 0.03798 -0.0037 1.0000 0.1308
-7.250 -0.7538 0.04424 0.03516 -0.0023 1.0000 0.1298
-7.000 -0.7418 0.04210 0.03277 -0.0005 1.0000 0.1290
-6.750 -0.7375 0.04053 0.03099 0.0027 1.0000 0.1285
-6.500 -0.7344 0.03916 0.02938 0.0062 1.0000 0.1280
-6.250 -0.7268 0.03773 0.02767 0.0092 1.0000 0.1277
-6.000 -0.7143 0.03624 0.02594 0.0116 1.0000 0.1274
-5.750 -0.6976 0.03478 0.02426 0.0134 1.0000 0.1275
-5.500 -0.6774 0.03339 0.02269 0.0148 1.0000 0.1284
-5.250 -0.6539 0.03208 0.02126 0.0158 1.0000 0.1302
-5.000 -0.6279 0.03094 0.01998 0.0165 1.0000 0.1331
-4.750 -0.5994 0.02973 0.01880 0.0169 1.0000 0.1378
-4.500 -0.5777 0.02871 0.01783 0.0182 1.0000 0.1453
-4.250 -0.5625 0.02773 0.01685 0.0204 1.0000 0.1543
-4.000 -0.5528 0.02656 0.01572 0.0233 1.0000 0.1696
-3.750 -0.5479 0.02479 0.01432 0.0267 1.0000 0.2058
-3.500 -0.5651 0.02185 0.01413 0.0353 1.0000 0.5820
-3.250 -0.5625 0.02331 0.01609 0.0461 1.0000 0.7611
-3.000 -0.2807 0.03300 0.02477 0.0222 1.0000 0.9071
-2.750 -0.2052 0.03269 0.02417 0.0133 1.0000 0.9330
-2.500 -0.1642 0.03213 0.02342 0.0091 1.0000 0.9518
-2.250 -0.1235 0.03144 0.02258 0.0046 1.0000 0.9673
-2.000 -0.0757 0.03064 0.02163 -0.0014 1.0000 0.9825
-1.750 -0.0195 0.02971 0.02057 -0.0092 1.0000 0.9983
-1.500 -0.0146 0.02942 0.02021 -0.0078 1.0000 1.0000
-1.250 -0.0161 0.02919 0.01992 -0.0051 1.0000 1.0000
-1.000 -0.0170 0.02895 0.01963 -0.0025 1.0000 1.0000
-0.750 -0.0176 0.02871 0.01934 0.0002 1.0000 1.0000
-0.500 -0.0179 0.02846 0.01904 0.0030 1.0000 1.0000
-0.250 -0.0183 0.02820 0.01874 0.0058 1.0000 1.0000
0.000 -0.0188 0.02793 0.01843 0.0087 1.0000 1.0000
0.250 -0.0099 0.02771 0.01818 0.0100 0.9978 1.0000
0.500 0.0251 0.02774 0.01820 0.0067 0.9887 1.0000
0.750 0.0640 0.02788 0.01836 0.0029 0.9784 1.0000
1.000 0.1104 0.02810 0.01862 -0.0020 0.9656 1.0000
1.250 0.2214 0.02815 0.01886 -0.0171 0.9328 1.0000
1.500 0.4121 0.02604 0.01716 -0.0414 0.8751 1.0000
1.750 0.4457 0.02538 0.01658 -0.0400 0.8404 1.0000
2.000 0.4614 0.02498 0.01623 -0.0357 0.8076 1.0000
2.250 0.4724 0.02465 0.01593 -0.0306 0.7760 1.0000
2.500 0.4820 0.02430 0.01561 -0.0255 0.7440 1.0000
2.750 0.4913 0.02391 0.01523 -0.0205 0.7097 1.0000
3.000 0.5011 0.02336 0.01468 -0.0154 0.6719 1.0000
3.250 0.5113 0.02281 0.01415 -0.0109 0.6277 1.0000
3.500 0.5210 0.02237 0.01383 -0.0072 0.5569 1.0000
3.750 0.5306 0.02146 0.01239 -0.0018 0.4660 1.0000
4.000 0.5392 0.02250 0.01224 0.0025 0.4000 1.0000
4.250 0.5506 0.02450 0.01372 0.0052 0.3325 1.0000
4.500 0.5651 0.02581 0.01476 0.0074 0.2898 1.0000
4.750 0.5841 0.02698 0.01569 0.0091 0.2668 1.0000
5.000 0.6054 0.02814 0.01674 0.0103 0.2522 1.0000
5.250 0.6265 0.02928 0.01797 0.0115 0.2418 1.0000
5.500 0.6476 0.03055 0.01932 0.0127 0.2350 1.0000
5.750 0.6675 0.03188 0.02083 0.0139 0.2294 1.0000
6.000 0.6875 0.03324 0.02225 0.0150 0.2254 1.0000
6.250 0.7069 0.03486 0.02396 0.0161 0.2226 1.0000
6.500 0.7230 0.03669 0.02618 0.0175 0.2202 1.0000
6.750 0.7374 0.03863 0.02842 0.0189 0.2181 1.0000
7.000 0.7506 0.04065 0.03073 0.0204 0.2161 1.0000
7.250 0.7627 0.04274 0.03306 0.0219 0.2142 1.0000
7.500 0.7731 0.04506 0.03563 0.0234 0.2131 1.0000
7.750 0.7797 0.04779 0.03865 0.0250 0.2131 1.0000
8.000 0.7795 0.05117 0.04236 0.0267 0.2143 1.0000
8.250 0.7729 0.05501 0.04652 0.0283 0.2162 1.0000
8.500 0.7629 0.05914 0.05087 0.0298 0.2185 1.0000
8.750 0.7559 0.06320 0.05505 0.0309 0.2209 1.0000
9.000 0.7582 0.06697 0.05889 0.0315 0.2228 1.0000
9.500 0.4684 0.10650 0.09787 0.0023 0.4006 1.0000
9.750 0.4923 0.11042 0.10185 0.0019 0.3960 1.0000
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Polar data table (+)
Polar graphs
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