KC-135 BL200.76 AIRFOIL (kc135c-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: KC-135 BL200.76 AIRFOIL (kc135c-il) Reynolds number: 500,000 Max Cl/Cd: 73.08 at α=3.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-kc135c-il-500000-n5.txt Download as CSV file: xf-kc135c-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: KC-135 BL200.76 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.5015 0.08304 0.08075 -0.0334 1.0000 0.0080
-9.500 -0.5079 0.07750 0.07524 -0.0379 1.0000 0.0079
-9.250 -0.5235 0.07149 0.06921 -0.0431 1.0000 0.0079
-9.000 -0.5427 0.06737 0.06506 -0.0437 1.0000 0.0079
-8.750 -0.5555 0.06450 0.06214 -0.0421 1.0000 0.0079
-8.500 -0.5670 0.06056 0.05811 -0.0408 1.0000 0.0079
-8.250 -0.5724 0.05745 0.05492 -0.0390 1.0000 0.0078
-8.000 -0.5662 0.05025 0.04743 -0.0412 0.9832 0.0080
-7.750 -0.5523 0.04417 0.04103 -0.0431 0.9677 0.0082
-7.500 -0.5296 0.04078 0.03742 -0.0451 0.9541 0.0085
-7.250 -0.5046 0.03800 0.03442 -0.0467 0.9389 0.0087
-7.000 -0.4846 0.03461 0.03073 -0.0468 0.9207 0.0089
-6.750 -0.4647 0.03247 0.02835 -0.0462 0.9034 0.0097
-6.500 -0.4498 0.02870 0.02418 -0.0442 0.8868 0.0101
-6.250 -0.4395 0.02097 0.01557 -0.0401 0.8726 0.0110
-6.000 -0.4195 0.01845 0.01265 -0.0388 0.8609 0.0114
-5.750 -0.3962 0.01756 0.01159 -0.0381 0.8504 0.0118
-5.500 -0.3719 0.01704 0.01095 -0.0377 0.8411 0.0123
-5.250 -0.3475 0.01618 0.00992 -0.0371 0.8328 0.0128
-5.000 -0.3228 0.01533 0.00891 -0.0365 0.8244 0.0135
-4.750 -0.2982 0.01429 0.00769 -0.0358 0.8168 0.0141
-4.500 -0.2739 0.01350 0.00677 -0.0351 0.8092 0.0145
-4.250 -0.2496 0.01290 0.00604 -0.0345 0.8024 0.0149
-4.000 -0.2264 0.01219 0.00525 -0.0336 0.7952 0.0153
-3.750 -0.2029 0.01168 0.00469 -0.0329 0.7885 0.0160
-3.500 -0.1777 0.01143 0.00442 -0.0325 0.7813 0.0170
-3.250 -0.1531 0.01110 0.00403 -0.0319 0.7749 0.0178
-3.000 -0.1286 0.01073 0.00361 -0.0313 0.7682 0.0187
-2.750 -0.1038 0.01043 0.00324 -0.0307 0.7620 0.0196
-2.500 -0.0790 0.01010 0.00286 -0.0302 0.7556 0.0208
-2.250 -0.0537 0.00985 0.00257 -0.0297 0.7493 0.0227
-2.000 -0.0276 0.00968 0.00238 -0.0294 0.7438 0.0252
-1.750 -0.0015 0.00952 0.00219 -0.0291 0.7379 0.0286
-1.250 0.0512 0.00924 0.00187 -0.0286 0.7270 0.0396
-1.000 0.0776 0.00912 0.00175 -0.0283 0.7214 0.0500
-0.750 0.1032 0.00893 0.00164 -0.0280 0.7146 0.0870
-0.500 0.1113 0.00703 0.00139 -0.0250 0.7076 0.6098
-0.250 0.1358 0.00692 0.00139 -0.0242 0.7005 0.6624
0.000 0.1614 0.00685 0.00138 -0.0237 0.6922 0.6910
0.250 0.1873 0.00682 0.00137 -0.0233 0.6832 0.7125
0.500 0.2127 0.00678 0.00136 -0.0227 0.6727 0.7346
0.750 0.2376 0.00671 0.00137 -0.0220 0.6603 0.7630
1.000 0.2641 0.00670 0.00137 -0.0217 0.6497 0.7753
1.250 0.2909 0.00671 0.00138 -0.0215 0.6426 0.7856
1.500 0.3178 0.00670 0.00141 -0.0214 0.6346 0.7964
1.750 0.3444 0.00671 0.00144 -0.0211 0.6255 0.8083
2.000 0.3707 0.00673 0.00147 -0.0208 0.6153 0.8222
2.250 0.3972 0.00673 0.00153 -0.0205 0.6049 0.8377
2.500 0.4234 0.00676 0.00159 -0.0201 0.5921 0.8545
2.750 0.4497 0.00681 0.00166 -0.0198 0.5763 0.8724
3.000 0.4763 0.00689 0.00175 -0.0195 0.5565 0.8916
3.250 0.5043 0.00703 0.00186 -0.0196 0.5274 0.9107
3.500 0.5335 0.00730 0.00200 -0.0201 0.4795 0.9284
3.750 0.5633 0.00776 0.00223 -0.0209 0.4158 0.9432
4.000 0.5932 0.00832 0.00251 -0.0219 0.3502 0.9554
4.250 0.6223 0.00894 0.00283 -0.0228 0.2840 0.9661
4.500 0.6536 0.00941 0.00312 -0.0241 0.2409 0.9743
4.750 0.6854 0.00981 0.00340 -0.0254 0.2117 0.9808
5.000 0.7158 0.01016 0.00367 -0.0263 0.1881 0.9876
5.250 0.7469 0.01052 0.00393 -0.0275 0.1638 0.9931
5.500 0.7775 0.01097 0.00425 -0.0287 0.1299 0.9985
5.750 0.7997 0.01151 0.00461 -0.0281 0.0958 1.0000
6.000 0.8158 0.01212 0.00504 -0.0262 0.0603 1.0000
6.250 0.8326 0.01270 0.00548 -0.0244 0.0389 1.0000
6.500 0.8518 0.01311 0.00587 -0.0229 0.0315 1.0000
6.750 0.8714 0.01351 0.00629 -0.0216 0.0271 1.0000
7.000 0.8915 0.01386 0.00669 -0.0203 0.0247 1.0000
7.250 0.9106 0.01429 0.00713 -0.0189 0.0220 1.0000
7.500 0.9297 0.01474 0.00761 -0.0175 0.0196 1.0000
7.750 0.9495 0.01514 0.00807 -0.0163 0.0179 1.0000
8.000 0.9685 0.01559 0.00855 -0.0149 0.0164 1.0000
8.250 0.9853 0.01624 0.00922 -0.0132 0.0146 1.0000
8.500 1.0041 0.01671 0.00976 -0.0119 0.0139 1.0000
8.750 1.0219 0.01724 0.01036 -0.0104 0.0129 1.0000
9.000 1.0394 0.01779 0.01098 -0.0089 0.0121 1.0000
9.250 1.0562 0.01838 0.01159 -0.0074 0.0112 1.0000
9.500 1.0690 0.01922 0.01249 -0.0052 0.0105 1.0000
9.750 1.0840 0.01982 0.01318 -0.0034 0.0101 1.0000
10.000 1.0958 0.02050 0.01395 -0.0011 0.0097 1.0000
10.250 1.1065 0.02126 0.01479 0.0014 0.0093 1.0000
10.500 1.1171 0.02206 0.01569 0.0036 0.0090 1.0000
10.750 1.1285 0.02286 0.01656 0.0057 0.0086 1.0000
11.000 1.1387 0.02376 0.01755 0.0076 0.0084 1.0000
11.250 1.1476 0.02479 0.01866 0.0096 0.0082 1.0000
11.500 1.1554 0.02594 0.01989 0.0116 0.0079 1.0000
11.750 1.1597 0.02742 0.02147 0.0136 0.0077 1.0000
12.000 1.1628 0.02909 0.02325 0.0156 0.0075 1.0000
12.250 1.1693 0.03054 0.02483 0.0171 0.0074 1.0000
12.750 1.1808 0.03371 0.02829 0.0195 0.0071 1.0000
13.000 1.1838 0.03564 0.03037 0.0207 0.0069 1.0000
13.250 1.1853 0.03777 0.03264 0.0217 0.0068 1.0000
13.500 1.1887 0.03977 0.03477 0.0223 0.0066 1.0000
13.750 1.1890 0.04218 0.03733 0.0228 0.0065 1.0000
14.000 1.1842 0.04526 0.04058 0.0232 0.0064 1.0000
14.250 1.1833 0.04798 0.04343 0.0231 0.0062 1.0000
14.500 1.1790 0.05124 0.04684 0.0228 0.0061 1.0000
14.750 1.1719 0.05499 0.05076 0.0222 0.0062 1.0000
15.000 1.1641 0.05907 0.05497 0.0211 0.0060 1.0000
15.250 1.1548 0.06357 0.05963 0.0196 0.0060 1.0000
15.500 1.1414 0.06907 0.06531 0.0174 0.0060 1.0000
15.750 1.1362 0.07362 0.06996 0.0150 0.0059 1.0000
16.000 1.1206 0.08019 0.07671 0.0117 0.0059 1.0000
16.250 1.0985 0.08846 0.08517 0.0074 0.0059 1.0000
16.500 1.0891 0.09465 0.09146 0.0037 0.0058 1.0000
16.750 1.0674 0.10353 0.10052 -0.0011 0.0058 1.0000
17.000 1.0387 0.11430 0.11148 -0.0070 0.0060 1.0000
17.250 1.0049 0.12667 0.12404 -0.0138 0.0061 1.0000
17.500 0.9698 0.14021 0.13774 -0.0212 0.0061 1.0000
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Polar data table (+)
Polar graphs
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