KC-135 BL124.32 AIRFOIL (kc135b-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: KC-135 BL124.32 AIRFOIL (kc135b-il) Reynolds number: 500,000 Max Cl/Cd: 71.22 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-kc135b-il-500000-n5.txt Download as CSV file: xf-kc135b-il-500000-n5.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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.5412 0.08493 0.08253 -0.0392 1.0000 0.0117
-11.000 -0.5733 0.07319 0.07076 -0.0486 1.0000 0.0115
-10.750 -0.6053 0.06593 0.06340 -0.0529 1.0000 0.0113
-10.500 -0.6321 0.06109 0.05846 -0.0537 1.0000 0.0115
-10.250 -0.6596 0.05724 0.05448 -0.0517 1.0000 0.0113
-10.000 -0.6833 0.05428 0.05142 -0.0473 1.0000 0.0115
-9.750 -0.7016 0.05053 0.04749 -0.0435 1.0000 0.0115
-9.500 -0.7137 0.04593 0.04265 -0.0404 0.9934 0.0117
-9.250 -0.7514 0.02620 0.02120 -0.0368 0.9675 0.0129
-9.000 -0.7200 0.02479 0.01965 -0.0388 0.9537 0.0132
-8.750 -0.6858 0.02357 0.01828 -0.0412 0.9372 0.0135
-8.500 -0.6545 0.02212 0.01659 -0.0428 0.9162 0.0138
-8.250 -0.6289 0.02089 0.01513 -0.0429 0.8920 0.0140
-7.750 -0.5846 0.01885 0.01264 -0.0413 0.8516 0.0147
-7.500 -0.5628 0.01793 0.01151 -0.0403 0.8355 0.0150
-7.250 -0.5409 0.01714 0.01054 -0.0394 0.8220 0.0154
-7.000 -0.5189 0.01639 0.00965 -0.0384 0.8098 0.0157
-6.750 -0.4965 0.01585 0.00896 -0.0375 0.7991 0.0161
-6.500 -0.4754 0.01518 0.00820 -0.0365 0.7895 0.0165
-6.250 -0.4530 0.01473 0.00770 -0.0356 0.7807 0.0169
-6.000 -0.4304 0.01433 0.00723 -0.0347 0.7729 0.0174
-5.750 -0.4078 0.01391 0.00675 -0.0339 0.7651 0.0178
-5.250 -0.3625 0.01310 0.00580 -0.0321 0.7520 0.0189
-5.000 -0.3395 0.01275 0.00537 -0.0312 0.7455 0.0197
-4.750 -0.3167 0.01237 0.00494 -0.0304 0.7399 0.0204
-4.500 -0.2932 0.01204 0.00458 -0.0296 0.7341 0.0212
-4.250 -0.2689 0.01179 0.00430 -0.0290 0.7286 0.0223
-4.000 -0.2441 0.01158 0.00404 -0.0285 0.7235 0.0238
-3.750 -0.2192 0.01134 0.00377 -0.0280 0.7181 0.0252
-3.500 -0.1947 0.01109 0.00350 -0.0274 0.7132 0.0271
-3.250 -0.1694 0.01091 0.00328 -0.0270 0.7086 0.0291
-3.000 -0.1436 0.01073 0.00308 -0.0266 0.7033 0.0312
-2.750 -0.1183 0.01052 0.00287 -0.0262 0.6985 0.0347
-2.250 -0.0664 0.01022 0.00255 -0.0255 0.6894 0.0431
-2.000 -0.0401 0.01009 0.00241 -0.0252 0.6844 0.0489
-1.750 -0.0142 0.00994 0.00227 -0.0249 0.6799 0.0600
-1.500 0.0109 0.00969 0.00213 -0.0245 0.6756 0.0983
-1.250 0.0173 0.00781 0.00171 -0.0212 0.6708 0.5228
-1.000 0.0418 0.00767 0.00171 -0.0205 0.6658 0.5795
-0.750 0.0678 0.00761 0.00170 -0.0201 0.6604 0.6052
-0.500 0.0945 0.00758 0.00169 -0.0199 0.6543 0.6232
-0.250 0.1212 0.00757 0.00168 -0.0196 0.6488 0.6377
0.000 0.1478 0.00754 0.00168 -0.0193 0.6433 0.6538
0.250 0.1746 0.00752 0.00168 -0.0191 0.6368 0.6667
0.750 0.2292 0.00752 0.00168 -0.0188 0.6256 0.6812
1.000 0.2560 0.00754 0.00167 -0.0186 0.6165 0.6865
1.500 0.3095 0.00757 0.00167 -0.0182 0.5922 0.6978
1.750 0.3363 0.00760 0.00169 -0.0180 0.5831 0.7044
2.000 0.3630 0.00763 0.00172 -0.0178 0.5728 0.7110
2.250 0.3898 0.00765 0.00176 -0.0176 0.5638 0.7182
2.750 0.4426 0.00773 0.00187 -0.0171 0.5436 0.7353
3.000 0.4686 0.00777 0.00194 -0.0168 0.5315 0.7450
3.250 0.4945 0.00783 0.00202 -0.0164 0.5196 0.7562
3.500 0.5198 0.00789 0.00211 -0.0159 0.5045 0.7683
3.750 0.5442 0.00798 0.00221 -0.0153 0.4841 0.7827
4.000 0.5680 0.00810 0.00233 -0.0145 0.4612 0.7997
4.250 0.5904 0.00829 0.00249 -0.0135 0.4277 0.8195
4.500 0.6099 0.00865 0.00271 -0.0120 0.3737 0.8422
4.750 0.6296 0.00908 0.00301 -0.0107 0.3266 0.8686
5.000 0.6539 0.00941 0.00331 -0.0102 0.2979 0.8967
5.250 0.6845 0.00974 0.00362 -0.0111 0.2720 0.9222
5.500 0.7181 0.01026 0.00398 -0.0129 0.2325 0.9418
5.750 0.7517 0.01080 0.00436 -0.0148 0.1956 0.9564
6.000 0.7850 0.01126 0.00471 -0.0165 0.1714 0.9679
6.250 0.8179 0.01163 0.00504 -0.0181 0.1559 0.9770
6.500 0.8492 0.01200 0.00537 -0.0193 0.1420 0.9850
6.750 0.8801 0.01240 0.00572 -0.0205 0.1255 0.9918
7.000 0.9095 0.01291 0.00612 -0.0215 0.1045 0.9988
7.250 0.9287 0.01340 0.00652 -0.0203 0.0844 1.0000
7.500 0.9428 0.01390 0.00692 -0.0180 0.0682 1.0000
7.750 0.9568 0.01442 0.00737 -0.0158 0.0531 1.0000
8.000 0.9702 0.01496 0.00785 -0.0134 0.0417 1.0000
8.250 0.9847 0.01545 0.00831 -0.0113 0.0355 1.0000
8.500 0.9991 0.01592 0.00879 -0.0091 0.0312 1.0000
8.750 1.0138 0.01638 0.00926 -0.0070 0.0286 1.0000
9.000 1.0260 0.01690 0.00979 -0.0045 0.0262 1.0000
9.250 1.0383 0.01732 0.01026 -0.0020 0.0246 1.0000
9.500 1.0502 0.01780 0.01078 0.0005 0.0233 1.0000
9.750 1.0616 0.01837 0.01136 0.0029 0.0219 1.0000
10.000 1.0722 0.01903 0.01206 0.0052 0.0207 1.0000
10.250 1.0851 0.01962 0.01272 0.0072 0.0200 1.0000
10.500 1.0976 0.02028 0.01344 0.0090 0.0191 1.0000
10.750 1.1098 0.02098 0.01420 0.0107 0.0182 1.0000
11.000 1.1213 0.02178 0.01503 0.0124 0.0173 1.0000
11.250 1.1299 0.02280 0.01609 0.0142 0.0165 1.0000
11.500 1.1410 0.02371 0.01708 0.0157 0.0159 1.0000
11.750 1.1529 0.02461 0.01805 0.0169 0.0152 1.0000
12.000 1.1628 0.02569 0.01920 0.0182 0.0146 1.0000
12.250 1.1729 0.02679 0.02037 0.0193 0.0140 1.0000
12.500 1.1811 0.02809 0.02173 0.0205 0.0136 1.0000
12.750 1.1871 0.02962 0.02332 0.0216 0.0132 1.0000
13.000 1.1947 0.03106 0.02484 0.0225 0.0125 1.0000
13.250 1.2005 0.03269 0.02657 0.0234 0.0124 1.0000
13.500 1.2073 0.03430 0.02828 0.0241 0.0120 1.0000
13.750 1.2127 0.03606 0.03013 0.0248 0.0117 1.0000
14.000 1.2182 0.03785 0.03201 0.0253 0.0113 1.0000
14.250 1.2219 0.03988 0.03413 0.0257 0.0110 1.0000
14.500 1.2246 0.04204 0.03637 0.0260 0.0108 1.0000
14.750 1.2280 0.04419 0.03860 0.0262 0.0104 1.0000
15.000 1.2272 0.04687 0.04135 0.0262 0.0101 1.0000
15.250 1.2258 0.04970 0.04428 0.0260 0.0100 1.0000
15.500 1.2234 0.05277 0.04747 0.0257 0.0098 1.0000
15.750 1.2194 0.05615 0.05097 0.0252 0.0098 1.0000
16.000 1.2202 0.05909 0.05404 0.0245 0.0094 1.0000
16.250 1.2153 0.06282 0.05788 0.0236 0.0094 1.0000
16.500 1.2101 0.06675 0.06194 0.0224 0.0093 1.0000
16.750 1.2035 0.07104 0.06635 0.0210 0.0091 1.0000
17.000 1.1971 0.07540 0.07083 0.0194 0.0090 1.0000
17.250 1.1903 0.07997 0.07552 0.0175 0.0088 1.0000
17.500 1.1782 0.08550 0.08119 0.0152 0.0089 1.0000
17.750 1.1694 0.09072 0.08652 0.0129 0.0088 1.0000
18.000 1.1585 0.09635 0.09228 0.0103 0.0087 1.0000
18.250 1.1454 0.10252 0.09857 0.0074 0.0086 1.0000
18.500 1.1342 0.10851 0.10467 0.0044 0.0085 1.0000
18.750 1.1224 0.11466 0.11093 0.0013 0.0084 1.0000
19.000 1.1105 0.12086 0.11724 -0.0018 0.0085 1.0000
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