KC-135 BL351.6 AIRFOIL (kc135d-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: KC-135 BL351.6 AIRFOIL (kc135d-il) Reynolds number: 50,000 Max Cl/Cd: 36.24 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-kc135d-il-50000.txt Download as CSV file: xf-kc135d-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: KC-135 BL351.6 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
------ -------- --------- --------- -------- -------- --------
-9.250 -0.4739 0.10955 0.10273 -0.0184 1.0000 0.1872
-9.000 -0.4663 0.10577 0.09899 -0.0178 1.0000 0.2006
-8.750 -0.4657 0.10269 0.09598 -0.0178 1.0000 0.2151
-8.500 -0.4544 0.09873 0.09207 -0.0160 1.0000 0.2364
-8.250 -0.4562 0.09616 0.08958 -0.0154 1.0000 0.2564
-8.000 -0.4476 0.09290 0.08634 -0.0134 1.0000 0.2823
-7.750 -0.4423 0.09007 0.08357 -0.0114 1.0000 0.3109
-7.500 -0.4452 0.08794 0.08154 -0.0091 1.0000 0.3426
-7.250 -0.4213 0.08479 0.07838 -0.0044 1.0000 0.3973
-7.000 -0.3950 0.08191 0.07549 0.0009 1.0000 0.4678
-6.750 -0.3640 0.07900 0.07254 0.0062 1.0000 0.5538
-6.500 -0.3057 0.07376 0.06717 0.0086 1.0000 0.6618
-6.250 -0.2629 0.06899 0.06234 0.0083 1.0000 0.7456
-5.000 -0.2876 0.05816 0.05206 0.0133 1.0000 0.7018
-3.750 -0.4223 0.03933 0.03204 -0.0160 1.0000 0.2852
-3.500 -0.3870 0.03672 0.02851 -0.0175 1.0000 0.2244
-3.250 -0.3562 0.03507 0.02599 -0.0169 1.0000 0.1850
-3.000 -0.3284 0.03383 0.02398 -0.0156 1.0000 0.1589
-2.750 -0.3031 0.03219 0.02188 -0.0143 1.0000 0.1443
-2.500 -0.2786 0.03028 0.01973 -0.0132 1.0000 0.1357
-2.250 -0.2542 0.02944 0.01836 -0.0118 1.0000 0.1315
-2.000 -0.2303 0.02795 0.01674 -0.0109 1.0000 0.1330
-1.750 -0.2060 0.02712 0.01562 -0.0096 1.0000 0.1312
-1.500 -0.1811 0.02616 0.01453 -0.0085 1.0000 0.1310
-1.250 -0.1569 0.02517 0.01353 -0.0075 1.0000 0.1332
-1.000 -0.1357 0.02451 0.01281 -0.0064 1.0000 0.1417
-0.750 -0.1153 0.02391 0.01215 -0.0053 1.0000 0.1513
-0.500 -0.0941 0.02344 0.01158 -0.0044 1.0000 0.1627
-0.250 -0.0715 0.02288 0.01106 -0.0040 1.0000 0.1901
0.000 -0.0281 0.02025 0.01101 -0.0055 1.0000 1.0000
0.250 -0.0097 0.02061 0.01087 -0.0043 1.0000 1.0000
0.500 0.0084 0.02100 0.01091 -0.0034 1.0000 1.0000
0.750 0.0265 0.02142 0.01106 -0.0027 1.0000 1.0000
1.000 0.0445 0.02188 0.01128 -0.0021 1.0000 1.0000
1.250 0.0625 0.02237 0.01159 -0.0015 1.0000 1.0000
1.500 0.0805 0.02289 0.01197 -0.0010 1.0000 1.0000
1.750 0.0984 0.02346 0.01242 -0.0006 1.0000 1.0000
2.000 0.1162 0.02406 0.01292 -0.0002 1.0000 1.0000
2.250 0.1339 0.02471 0.01349 0.0001 1.0000 1.0000
2.500 0.1513 0.02541 0.01414 0.0004 1.0000 1.0000
2.750 0.1952 0.02677 0.01549 -0.0047 0.9873 1.0000
3.000 0.2536 0.02834 0.01710 -0.0121 0.9650 1.0000
3.250 0.3152 0.02977 0.01862 -0.0196 0.9414 1.0000
3.500 0.3629 0.03068 0.01965 -0.0241 0.9168 1.0000
3.750 0.4120 0.03147 0.02064 -0.0284 0.8917 1.0000
4.000 0.4631 0.03209 0.02147 -0.0326 0.8668 1.0000
4.250 0.5189 0.03241 0.02207 -0.0369 0.8411 1.0000
4.500 0.5752 0.03229 0.02234 -0.0406 0.8133 1.0000
4.750 0.6280 0.03176 0.02220 -0.0429 0.7821 1.0000
5.000 0.6838 0.03053 0.02145 -0.0442 0.7488 1.0000
5.250 0.7388 0.02863 0.02000 -0.0440 0.7122 1.0000
5.500 0.7806 0.02687 0.01857 -0.0417 0.6675 1.0000
5.750 0.8188 0.02515 0.01708 -0.0387 0.6155 1.0000
6.000 0.8448 0.02437 0.01630 -0.0351 0.5573 1.0000
6.250 0.8625 0.02380 0.01545 -0.0305 0.4903 1.0000
6.500 0.8698 0.02412 0.01531 -0.0256 0.4147 1.0000
6.750 0.8755 0.02533 0.01604 -0.0214 0.3391 1.0000
7.000 0.8740 0.02785 0.01771 -0.0167 0.2372 1.0000
7.250 0.8867 0.03089 0.02020 -0.0138 0.1638 1.0000
7.500 0.9085 0.03312 0.02225 -0.0124 0.1335 1.0000
7.750 0.9388 0.03588 0.02499 -0.0121 0.1180 1.0000
8.000 0.9619 0.03849 0.02781 -0.0111 0.1062 1.0000
8.250 0.9853 0.04199 0.03161 -0.0102 0.1008 1.0000
8.500 1.0019 0.04572 0.03593 -0.0085 0.0987 1.0000
8.750 1.0126 0.04953 0.04031 -0.0064 0.0968 1.0000
9.000 1.0199 0.05318 0.04439 -0.0044 0.0946 1.0000
9.250 1.0347 0.05686 0.04810 -0.0035 0.0911 1.0000
9.500 1.0254 0.06104 0.05294 -0.0005 0.0923 1.0000
9.750 1.0083 0.06577 0.05819 0.0023 0.0943 1.0000
10.000 0.9883 0.07049 0.06325 0.0044 0.0961 1.0000
10.250 0.9653 0.07486 0.06782 0.0063 0.0977 1.0000
10.500 0.9424 0.07947 0.07255 0.0071 0.0993 1.0000
10.750 0.9250 0.08460 0.07774 0.0066 0.1010 1.0000
11.000 0.9151 0.09003 0.08321 0.0056 0.1023 1.0000
11.250 0.8359 0.10643 0.09954 -0.0089 0.1194 1.0000
11.500 0.8561 0.10818 0.10133 -0.0053 0.1157 1.0000
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Polar data table (+)
Polar graphs
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