KC-135 BL124.32 AIRFOIL (kc135b-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: KC-135 BL124.32 AIRFOIL (kc135b-il) Reynolds number: 1,000,000 Max Cl/Cd: 98.19 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-kc135b-il-1000000.txt Download as CSV file: xf-kc135b-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.500 -0.4171 0.08650 0.08492 -0.0380 1.0000 0.0166
-11.250 -0.4258 0.08037 0.07880 -0.0406 1.0000 0.0166
-11.000 -0.4521 0.06907 0.06750 -0.0473 1.0000 0.0166
-10.750 -0.5096 0.05581 0.05408 -0.0549 1.0000 0.0164
-10.500 -0.5340 0.05098 0.04919 -0.0562 1.0000 0.0165
-10.250 -0.5660 0.04605 0.04414 -0.0562 1.0000 0.0164
-10.000 -0.5886 0.04307 0.04107 -0.0542 1.0000 0.0165
-9.750 -0.6112 0.04057 0.03849 -0.0502 1.0000 0.0165
-9.500 -0.6229 0.03886 0.03674 -0.0464 1.0000 0.0166
-9.250 -0.6194 0.03610 0.03389 -0.0460 0.9895 0.0167
-9.000 -0.6025 0.03241 0.03007 -0.0483 0.9757 0.0169
-8.750 -0.5808 0.02876 0.02625 -0.0510 0.9546 0.0173
-8.500 -0.5639 0.02614 0.02342 -0.0515 0.9185 0.0179
-8.250 -0.6269 0.02518 0.02116 -0.0435 0.9434 0.0155
-8.000 -0.6093 0.02024 0.01557 -0.0425 0.9135 0.0156
-7.750 -0.5884 0.01890 0.01392 -0.0414 0.8848 0.0159
-7.500 -0.5681 0.01785 0.01259 -0.0400 0.8613 0.0162
-7.250 -0.5478 0.01590 0.01039 -0.0390 0.8429 0.0166
-7.000 -0.5259 0.01499 0.00935 -0.0380 0.8274 0.0168
-6.750 -0.5034 0.01439 0.00866 -0.0371 0.8142 0.0170
-6.500 -0.4806 0.01387 0.00806 -0.0363 0.8031 0.0173
-6.250 -0.4578 0.01335 0.00745 -0.0354 0.7930 0.0176
-6.000 -0.4347 0.01287 0.00691 -0.0346 0.7844 0.0180
-5.750 -0.4119 0.01242 0.00638 -0.0337 0.7762 0.0184
-5.500 -0.3887 0.01199 0.00590 -0.0329 0.7691 0.0188
-5.250 -0.3650 0.01167 0.00552 -0.0321 0.7621 0.0194
-5.000 -0.3406 0.01142 0.00520 -0.0315 0.7558 0.0199
-4.750 -0.3207 0.01072 0.00444 -0.0301 0.7497 0.0208
-4.500 -0.2974 0.01039 0.00406 -0.0292 0.7439 0.0215
-4.250 -0.2726 0.01015 0.00381 -0.0287 0.7385 0.0224
-4.000 -0.2474 0.00993 0.00356 -0.0282 0.7329 0.0237
-3.750 -0.2220 0.00977 0.00335 -0.0277 0.7277 0.0246
-3.500 -0.1982 0.00940 0.00294 -0.0270 0.7228 0.0266
-3.250 -0.1723 0.00922 0.00277 -0.0266 0.7177 0.0286
-3.000 -0.1460 0.00912 0.00263 -0.0264 0.7127 0.0306
-2.750 -0.1207 0.00889 0.00238 -0.0259 0.7081 0.0344
-2.500 -0.0941 0.00875 0.00226 -0.0257 0.7034 0.0376
-2.250 -0.0680 0.00859 0.00208 -0.0253 0.6985 0.0423
-2.000 -0.0416 0.00850 0.00196 -0.0251 0.6934 0.0477
-1.750 -0.0152 0.00831 0.00182 -0.0248 0.6882 0.0586
-1.500 0.0059 0.00767 0.00160 -0.0237 0.6827 0.1982
-1.250 0.0149 0.00615 0.00129 -0.0207 0.6778 0.5598
-1.000 0.0411 0.00603 0.00129 -0.0203 0.6730 0.6004
-0.750 0.0680 0.00600 0.00128 -0.0201 0.6674 0.6211
-0.500 0.0951 0.00600 0.00127 -0.0199 0.6621 0.6342
-0.250 0.1227 0.00597 0.00127 -0.0198 0.6572 0.6475
0.000 0.1503 0.00597 0.00126 -0.0198 0.6515 0.6561
0.250 0.1775 0.00596 0.00125 -0.0196 0.6448 0.6653
0.500 0.2046 0.00595 0.00124 -0.0194 0.6361 0.6776
0.750 0.2316 0.00594 0.00124 -0.0192 0.6276 0.6863
1.000 0.2590 0.00595 0.00123 -0.0192 0.6195 0.6941
1.250 0.2864 0.00595 0.00124 -0.0191 0.6129 0.6999
1.500 0.3141 0.00596 0.00125 -0.0191 0.6060 0.7062
1.750 0.3412 0.00597 0.00127 -0.0190 0.5988 0.7128
2.000 0.3686 0.00598 0.00129 -0.0189 0.5909 0.7203
2.250 0.3957 0.00600 0.00132 -0.0188 0.5837 0.7280
2.500 0.4229 0.00600 0.00136 -0.0187 0.5761 0.7376
2.750 0.4495 0.00602 0.00141 -0.0184 0.5681 0.7482
3.000 0.4761 0.00603 0.00146 -0.0182 0.5583 0.7604
3.250 0.5024 0.00605 0.00152 -0.0179 0.5479 0.7747
3.500 0.5280 0.00607 0.00158 -0.0175 0.5367 0.7917
3.750 0.5529 0.00610 0.00166 -0.0169 0.5220 0.8127
4.000 0.5774 0.00614 0.00175 -0.0163 0.5030 0.8374
4.250 0.6009 0.00622 0.00186 -0.0154 0.4798 0.8655
4.500 0.6245 0.00636 0.00200 -0.0145 0.4502 0.8952
4.750 0.6488 0.00668 0.00221 -0.0140 0.4006 0.9243
5.000 0.6739 0.00745 0.00261 -0.0140 0.3138 0.9490
5.250 0.7081 0.00791 0.00292 -0.0159 0.2728 0.9630
5.500 0.7435 0.00837 0.00321 -0.0180 0.2347 0.9714
5.750 0.7771 0.00877 0.00348 -0.0197 0.2071 0.9779
6.000 0.8084 0.00912 0.00375 -0.0209 0.1873 0.9846
6.250 0.8428 0.00946 0.00402 -0.0227 0.1693 0.9885
6.500 0.8763 0.00979 0.00429 -0.0243 0.1543 0.9927
6.750 0.9097 0.01013 0.00457 -0.0260 0.1384 0.9961
7.000 0.9437 0.01056 0.00489 -0.0279 0.1176 0.9989
7.250 0.9668 0.01107 0.00525 -0.0275 0.0908 1.0000
7.500 0.9785 0.01164 0.00567 -0.0248 0.0659 1.0000
7.750 0.9899 0.01224 0.00613 -0.0219 0.0452 1.0000
8.000 1.0041 0.01272 0.00656 -0.0196 0.0362 1.0000
8.250 1.0196 0.01314 0.00697 -0.0174 0.0314 1.0000
8.500 1.0359 0.01353 0.00736 -0.0155 0.0288 1.0000
8.750 1.0497 0.01406 0.00789 -0.0131 0.0260 1.0000
9.000 1.0674 0.01437 0.00825 -0.0115 0.0250 1.0000
9.250 1.0838 0.01474 0.00864 -0.0096 0.0238 1.0000
9.500 1.0983 0.01520 0.00911 -0.0075 0.0224 1.0000
9.750 1.1055 0.01583 0.00978 -0.0040 0.0207 1.0000
10.000 1.1193 0.01617 0.01016 -0.0017 0.0201 1.0000
10.250 1.1326 0.01658 0.01061 0.0005 0.0192 1.0000
10.500 1.1454 0.01708 0.01113 0.0027 0.0183 1.0000
10.750 1.1569 0.01769 0.01177 0.0049 0.0174 1.0000
11.000 1.1633 0.01864 0.01278 0.0077 0.0163 1.0000
11.250 1.1774 0.01922 0.01342 0.0092 0.0159 1.0000
11.500 1.1902 0.01992 0.01417 0.0108 0.0152 1.0000
11.750 1.2036 0.02062 0.01490 0.0122 0.0146 1.0000
12.000 1.2144 0.02152 0.01585 0.0138 0.0140 1.0000
12.250 1.2195 0.02287 0.01725 0.0157 0.0132 1.0000
12.500 1.2253 0.02425 0.01871 0.0173 0.0128 1.0000
12.750 1.2375 0.02523 0.01976 0.0182 0.0126 1.0000
13.000 1.2513 0.02611 0.02070 0.0190 0.0119 1.0000
13.250 1.2597 0.02746 0.02212 0.0199 0.0117 1.0000
13.500 1.2681 0.02884 0.02357 0.0208 0.0114 1.0000
13.750 1.2769 0.03023 0.02502 0.0215 0.0112 1.0000
14.000 1.2843 0.03178 0.02662 0.0222 0.0108 1.0000
14.250 1.2881 0.03370 0.02861 0.0229 0.0107 1.0000
14.500 1.2848 0.03630 0.03130 0.0236 0.0102 1.0000
14.750 1.2817 0.03899 0.03410 0.0241 0.0099 1.0000
15.000 1.2845 0.04119 0.03639 0.0244 0.0099 1.0000
15.250 1.2881 0.04335 0.03864 0.0245 0.0098 1.0000
15.500 1.2861 0.04618 0.04158 0.0246 0.0097 1.0000
15.750 1.2827 0.04927 0.04477 0.0244 0.0097 1.0000
16.000 1.2873 0.05160 0.04718 0.0241 0.0093 1.0000
16.250 1.2836 0.05493 0.05063 0.0235 0.0093 1.0000
16.500 1.2803 0.05835 0.05415 0.0228 0.0092 1.0000
16.750 1.2751 0.06213 0.05803 0.0219 0.0091 1.0000
17.000 1.2712 0.06585 0.06185 0.0208 0.0090 1.0000
17.250 1.2681 0.06962 0.06570 0.0195 0.0087 1.0000
17.500 1.2542 0.07490 0.07112 0.0178 0.0088 1.0000
17.750 1.2543 0.07846 0.07474 0.0162 0.0086 1.0000
18.000 1.2423 0.08377 0.08017 0.0142 0.0086 1.0000
18.250 1.2300 0.08933 0.08584 0.0119 0.0085 1.0000
18.500 1.2184 0.09490 0.09151 0.0095 0.0084 1.0000
18.750 1.2084 0.10034 0.09704 0.0070 0.0083 1.0000
19.000 1.1984 0.10586 0.10266 0.0044 0.0083 1.0000
19.250 1.1814 0.11256 0.10947 0.0013 0.0083 1.0000
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