BOEING 707 .54 SPAN AIRFOIL (b707d-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: BOEING 707 .54 SPAN AIRFOIL (b707d-il) Reynolds number: 50,000 Max Cl/Cd: 36.73 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-b707d-il-50000.txt Download as CSV file: xf-b707d-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: BOEING 707 .54 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
------ -------- --------- --------- -------- -------- --------
-8.750 -0.4659 0.10111 0.09440 -0.0156 1.0000 0.2402
-8.500 -0.4714 0.09859 0.09198 -0.0157 1.0000 0.2555
-8.250 -0.4805 0.09632 0.08983 -0.0156 1.0000 0.2704
-8.000 -0.4538 0.09226 0.08570 -0.0113 1.0000 0.3111
-7.750 -0.4386 0.08924 0.08269 -0.0078 1.0000 0.3525
-7.500 -0.4493 0.08782 0.08141 -0.0052 1.0000 0.3842
-7.250 -0.3973 0.08323 0.07669 0.0003 1.0000 0.4622
-7.000 -0.3818 0.08112 0.07460 0.0046 1.0000 0.5242
-6.750 -0.3362 0.07671 0.07008 0.0074 1.0000 0.6061
-6.500 -0.3045 0.07316 0.06649 0.0093 1.0000 0.6805
-6.250 -0.2643 0.06855 0.06183 0.0086 1.0000 0.7521
-6.000 -0.2315 0.06408 0.05734 0.0066 1.0000 0.8002
-5.750 -0.2191 0.06123 0.05451 0.0061 1.0000 0.8142
-5.000 -0.3118 0.05834 0.05226 0.0144 1.0000 0.6721
-4.750 -0.3721 0.05791 0.05219 0.0201 1.0000 0.6268
-4.000 -0.4559 0.04187 0.03541 -0.0104 1.0000 0.3532
-3.750 -0.4068 0.03815 0.03009 -0.0178 1.0000 0.2399
-3.500 -0.3760 0.03608 0.02726 -0.0178 1.0000 0.1948
-3.250 -0.3488 0.03444 0.02497 -0.0167 1.0000 0.1672
-3.000 -0.3244 0.03287 0.02292 -0.0155 1.0000 0.1530
-2.750 -0.3006 0.03144 0.02103 -0.0143 1.0000 0.1449
-2.500 -0.2770 0.03022 0.01948 -0.0132 1.0000 0.1398
-2.250 -0.2526 0.02884 0.01785 -0.0121 1.0000 0.1340
-2.000 -0.2285 0.02831 0.01680 -0.0107 1.0000 0.1283
-1.750 -0.2045 0.02707 0.01553 -0.0097 1.0000 0.1264
-1.500 -0.1799 0.02613 0.01450 -0.0087 1.0000 0.1256
-1.250 -0.1566 0.02545 0.01370 -0.0075 1.0000 0.1261
-1.000 -0.1351 0.02479 0.01297 -0.0064 1.0000 0.1311
-0.750 -0.1149 0.02428 0.01236 -0.0054 1.0000 0.1399
-0.500 -0.0943 0.02378 0.01180 -0.0045 1.0000 0.1484
-0.250 -0.0726 0.02339 0.01136 -0.0039 1.0000 0.1626
0.000 -0.0289 0.02028 0.01125 -0.0058 1.0000 1.0000
0.250 -0.0098 0.02065 0.01105 -0.0044 1.0000 1.0000
0.500 0.0086 0.02104 0.01099 -0.0035 1.0000 1.0000
0.750 0.0267 0.02146 0.01111 -0.0027 1.0000 1.0000
1.000 0.0448 0.02191 0.01134 -0.0021 1.0000 1.0000
1.250 0.0630 0.02239 0.01164 -0.0015 1.0000 1.0000
1.500 0.0810 0.02291 0.01202 -0.0010 1.0000 1.0000
1.750 0.0990 0.02346 0.01244 -0.0006 1.0000 1.0000
2.000 0.1169 0.02406 0.01295 -0.0002 1.0000 1.0000
2.250 0.1346 0.02469 0.01351 0.0001 1.0000 1.0000
2.500 0.1522 0.02538 0.01415 0.0004 1.0000 1.0000
2.750 0.1930 0.02665 0.01543 -0.0040 0.9887 1.0000
3.000 0.2528 0.02832 0.01714 -0.0118 0.9673 1.0000
3.250 0.3077 0.02959 0.01850 -0.0181 0.9436 1.0000
3.500 0.3585 0.03061 0.01969 -0.0232 0.9189 1.0000
3.750 0.4109 0.03146 0.02073 -0.0281 0.8937 1.0000
4.000 0.4658 0.03206 0.02156 -0.0329 0.8677 1.0000
4.250 0.5217 0.03230 0.02216 -0.0371 0.8404 1.0000
4.500 0.5747 0.03216 0.02237 -0.0401 0.8108 1.0000
4.750 0.6315 0.03147 0.02217 -0.0428 0.7784 1.0000
5.000 0.6976 0.02961 0.02083 -0.0447 0.7442 1.0000
5.250 0.7545 0.02656 0.01821 -0.0429 0.7001 1.0000
5.500 0.7854 0.02460 0.01653 -0.0386 0.6483 1.0000
5.750 0.8111 0.02344 0.01550 -0.0347 0.5931 1.0000
6.000 0.8280 0.02272 0.01468 -0.0300 0.5221 1.0000
6.250 0.8397 0.02286 0.01442 -0.0254 0.4387 1.0000
6.500 0.8405 0.02422 0.01503 -0.0203 0.3345 1.0000
6.750 0.8327 0.02711 0.01683 -0.0150 0.2089 1.0000
7.000 0.8455 0.02985 0.01895 -0.0123 0.1478 1.0000
7.250 0.8767 0.03235 0.02128 -0.0117 0.1238 1.0000
7.500 0.9063 0.03476 0.02379 -0.0112 0.1073 1.0000
7.750 0.9376 0.03783 0.02685 -0.0112 0.0982 1.0000
8.000 0.9593 0.04054 0.03001 -0.0099 0.0908 1.0000
8.250 0.9831 0.04414 0.03376 -0.0092 0.0872 1.0000
8.500 1.0012 0.04838 0.03842 -0.0079 0.0866 1.0000
8.750 1.0110 0.05229 0.04288 -0.0058 0.0863 1.0000
9.000 1.0164 0.05632 0.04739 -0.0036 0.0861 1.0000
9.250 1.0170 0.06046 0.05199 -0.0014 0.0860 1.0000
9.500 1.0174 0.06480 0.05666 0.0005 0.0863 1.0000
9.750 0.9812 0.06927 0.06192 0.0042 0.0912 1.0000
10.000 0.9572 0.07383 0.06674 0.0062 0.0932 1.0000
10.250 0.9360 0.07827 0.07130 0.0074 0.0952 1.0000
10.500 0.9190 0.08320 0.07630 0.0072 0.0969 1.0000
10.750 0.9103 0.08844 0.08158 0.0066 0.0983 1.0000
11.000 0.8391 0.10069 0.09384 -0.0041 0.1076 1.0000
11.250 0.8415 0.10642 0.09956 -0.0052 0.1112 1.0000
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Polar data table (+)
Polar graphs
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