KC-135 BL124.32 AIRFOIL (kc135b-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: KC-135 BL124.32 AIRFOIL (kc135b-il) Reynolds number: 50,000 Max Cl/Cd: 31.06 at α=8° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-kc135b-il-50000.txt Download as CSV file: xf-kc135b-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: KC-135 BL124.32 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
------ -------- --------- --------- -------- -------- --------
-11.250 -0.4564 0.12918 0.12189 -0.0103 1.0000 0.2878
-11.000 -0.4545 0.12652 0.11928 -0.0101 1.0000 0.3038
-10.750 -0.4564 0.12425 0.11707 -0.0099 1.0000 0.3199
-10.500 -0.4193 0.11865 0.11142 -0.0084 1.0000 0.3428
-10.250 -0.4218 0.11682 0.10964 -0.0077 1.0000 0.3643
-10.000 -0.4006 0.11273 0.10555 -0.0068 1.0000 0.3872
-9.750 -0.4084 0.11169 0.10458 -0.0055 1.0000 0.4110
-9.500 -0.3822 0.10755 0.10043 -0.0045 1.0000 0.4392
-9.250 -0.3654 0.10400 0.09690 -0.0038 1.0000 0.4629
-9.000 -0.3671 0.10254 0.09550 -0.0023 1.0000 0.4867
-8.500 -0.3504 0.09644 0.08949 -0.0012 1.0000 0.5191
-8.250 -0.3320 0.09196 0.08502 -0.0022 1.0000 0.5236
-8.000 -0.3367 0.08984 0.08296 -0.0013 1.0000 0.5321
-7.750 -0.3368 0.08604 0.07923 -0.0023 1.0000 0.5212
-7.500 -0.4428 0.07689 0.07052 -0.0138 1.0000 0.3695
-7.250 -0.5107 0.06993 0.06392 -0.0178 1.0000 0.3265
-6.750 -0.6152 0.05961 0.05364 -0.0172 1.0000 0.2780
-6.500 -0.6409 0.05551 0.04916 -0.0154 1.0000 0.2487
-6.250 -0.6510 0.05185 0.04492 -0.0134 1.0000 0.2178
-6.000 -0.6479 0.04898 0.04141 -0.0112 1.0000 0.1922
-5.750 -0.6395 0.04637 0.03829 -0.0089 1.0000 0.1758
-5.500 -0.6287 0.04432 0.03565 -0.0064 1.0000 0.1630
-5.250 -0.6158 0.04217 0.03295 -0.0041 1.0000 0.1532
-5.000 -0.5992 0.04029 0.03072 -0.0022 1.0000 0.1468
-4.750 -0.5814 0.03830 0.02836 -0.0005 1.0000 0.1403
-4.500 -0.5632 0.03759 0.02696 0.0018 1.0000 0.1346
-4.250 -0.5425 0.03570 0.02490 0.0030 1.0000 0.1333
-4.000 -0.5223 0.03442 0.02334 0.0043 1.0000 0.1339
-3.750 -0.5012 0.03327 0.02196 0.0055 1.0000 0.1346
-3.500 -0.4781 0.03212 0.02065 0.0066 1.0000 0.1352
-3.250 -0.4531 0.03079 0.01937 0.0074 1.0000 0.1367
-3.000 -0.4307 0.02977 0.01845 0.0085 1.0000 0.1424
-2.750 -0.4108 0.02914 0.01775 0.0100 1.0000 0.1485
-2.500 -0.3931 0.02840 0.01700 0.0116 1.0000 0.1538
-2.250 -0.3766 0.02770 0.01625 0.0131 1.0000 0.1639
-2.000 -0.0441 0.03073 0.02169 -0.0185 1.0000 1.0000
-1.750 -0.0479 0.03070 0.02159 -0.0156 1.0000 1.0000
-1.500 -0.0518 0.03064 0.02145 -0.0128 1.0000 1.0000
-1.250 -0.0560 0.03053 0.02127 -0.0100 1.0000 1.0000
-1.000 -0.0607 0.03036 0.02104 -0.0071 1.0000 1.0000
-0.750 -0.0662 0.03014 0.02076 -0.0041 1.0000 1.0000
-0.500 -0.0732 0.02983 0.02038 -0.0008 1.0000 1.0000
-0.250 -0.0821 0.02942 0.01993 0.0028 1.0000 1.0000
0.000 -0.0684 0.02940 0.01979 0.0023 0.9946 1.0000
0.250 -0.0505 0.02950 0.01977 0.0013 0.9870 1.0000
0.500 -0.0369 0.02960 0.01975 0.0012 0.9797 1.0000
0.750 -0.0192 0.02993 0.01993 0.0006 0.9726 1.0000
1.000 0.0002 0.03039 0.02024 -0.0001 0.9654 1.0000
1.250 0.0201 0.03094 0.02066 -0.0006 0.9581 1.0000
1.500 0.0473 0.03177 0.02137 -0.0023 0.9504 1.0000
1.750 0.0669 0.03241 0.02191 -0.0026 0.9420 1.0000
2.000 0.1008 0.03341 0.02283 -0.0052 0.9303 1.0000
2.250 0.1385 0.03444 0.02380 -0.0083 0.9164 1.0000
2.500 0.1733 0.03538 0.02471 -0.0108 0.9022 1.0000
2.750 0.1961 0.03614 0.02545 -0.0112 0.8891 1.0000
3.000 0.2219 0.03703 0.02634 -0.0121 0.8758 1.0000
3.250 0.2500 0.03798 0.02729 -0.0132 0.8617 1.0000
3.500 0.2810 0.03892 0.02826 -0.0147 0.8457 1.0000
3.750 0.3135 0.03982 0.02922 -0.0162 0.8283 1.0000
4.000 0.3549 0.04063 0.03012 -0.0186 0.8086 1.0000
4.250 0.3916 0.04129 0.03088 -0.0200 0.7874 1.0000
4.500 0.4225 0.04181 0.03152 -0.0203 0.7644 1.0000
4.750 0.4819 0.04174 0.03165 -0.0236 0.7414 1.0000
5.000 0.5019 0.04220 0.03222 -0.0221 0.7170 1.0000
5.250 0.5698 0.04123 0.03156 -0.0255 0.6949 1.0000
5.500 0.5890 0.04149 0.03193 -0.0234 0.6694 1.0000
5.750 0.6652 0.03905 0.02988 -0.0260 0.6478 1.0000
6.000 0.6912 0.03848 0.02947 -0.0237 0.6210 1.0000
6.250 0.7369 0.03660 0.02785 -0.0226 0.5948 1.0000
6.500 0.7904 0.03397 0.02544 -0.0218 0.5664 1.0000
6.750 0.8297 0.03213 0.02375 -0.0200 0.5332 1.0000
7.000 0.8686 0.03045 0.02207 -0.0182 0.4972 1.0000
7.250 0.8981 0.02969 0.02120 -0.0162 0.4607 1.0000
7.500 0.9182 0.02977 0.02119 -0.0136 0.4250 1.0000
8.000 0.9528 0.03068 0.02165 -0.0083 0.3515 1.0000
8.250 0.9688 0.03170 0.02228 -0.0059 0.3124 1.0000
8.500 0.9772 0.03328 0.02376 -0.0030 0.2764 1.0000
8.750 0.9853 0.03498 0.02530 0.0000 0.2404 1.0000
9.000 0.9971 0.03688 0.02692 0.0024 0.2073 1.0000
9.250 1.0071 0.03911 0.02916 0.0049 0.1821 1.0000
9.500 1.0258 0.04148 0.03139 0.0061 0.1625 1.0000
9.750 1.0376 0.04388 0.03397 0.0080 0.1491 1.0000
10.000 1.0470 0.04688 0.03729 0.0101 0.1408 1.0000
10.250 1.0673 0.04971 0.04004 0.0107 0.1318 1.0000
10.500 1.0600 0.05273 0.04361 0.0142 0.1281 1.0000
10.750 1.0575 0.05578 0.04699 0.0169 0.1243 1.0000
11.000 1.0715 0.05900 0.05026 0.0178 0.1199 1.0000
11.250 1.0658 0.06283 0.05431 0.0201 0.1182 1.0000
11.500 1.0454 0.06633 0.05812 0.0235 0.1179 1.0000
11.750 1.0235 0.07003 0.06204 0.0264 0.1179 1.0000
12.000 0.9990 0.07417 0.06638 0.0282 0.1180 1.0000
12.250 0.9751 0.07891 0.07127 0.0288 0.1184 1.0000
12.500 0.7982 0.10347 0.09602 0.0134 0.1434 1.0000
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Polar data table (+)
Polar graphs
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