KC-135 BL200.76 AIRFOIL (kc135c-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: KC-135 BL200.76 AIRFOIL (kc135c-il) Reynolds number: 1,000,000 Max Cl/Cd: 78.85 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-kc135c-il-1000000-n5.txt Download as CSV file: xf-kc135c-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.5200 0.07997 0.07835 -0.0336 1.0000 0.0050
-9.500 -0.5333 0.07297 0.07136 -0.0407 1.0000 0.0050
-9.250 -0.5567 0.06764 0.06599 -0.0438 1.0000 0.0050
-9.000 -0.5800 0.06359 0.06188 -0.0421 1.0000 0.0051
-8.750 -0.5880 0.05796 0.05611 -0.0433 0.9842 0.0052
-8.500 -0.5958 0.04316 0.04072 -0.0489 0.9536 0.0058
-8.250 -0.5786 0.03884 0.03609 -0.0502 0.9247 0.0059
-8.000 -0.5621 0.03711 0.03416 -0.0494 0.8987 0.0061
-7.750 -0.5998 0.01866 0.01416 -0.0397 0.8706 0.0076
-7.500 -0.5792 0.01701 0.01219 -0.0386 0.8571 0.0080
-7.250 -0.5564 0.01621 0.01120 -0.0379 0.8455 0.0081
-6.750 -0.5117 0.01426 0.00891 -0.0363 0.8265 0.0088
-6.500 -0.4876 0.01374 0.00829 -0.0357 0.8188 0.0090
-6.250 -0.4628 0.01335 0.00782 -0.0353 0.8112 0.0092
-6.000 -0.4386 0.01281 0.00717 -0.0347 0.8040 0.0095
-5.750 -0.4142 0.01229 0.00656 -0.0342 0.7964 0.0098
-5.500 -0.3898 0.01183 0.00600 -0.0336 0.7894 0.0102
-5.250 -0.3653 0.01137 0.00547 -0.0330 0.7822 0.0106
-5.000 -0.3403 0.01108 0.00509 -0.0326 0.7753 0.0109
-4.750 -0.3153 0.01073 0.00468 -0.0321 0.7678 0.0112
-4.500 -0.2924 0.01018 0.00403 -0.0312 0.7604 0.0116
-4.250 -0.2678 0.00982 0.00363 -0.0307 0.7528 0.0120
-4.000 -0.2428 0.00956 0.00331 -0.0302 0.7461 0.0123
-3.750 -0.2171 0.00933 0.00305 -0.0298 0.7398 0.0127
-3.500 -0.1916 0.00912 0.00279 -0.0294 0.7335 0.0132
-3.250 -0.1657 0.00892 0.00255 -0.0291 0.7278 0.0138
-3.000 -0.1396 0.00875 0.00234 -0.0288 0.7220 0.0145
-2.750 -0.1134 0.00860 0.00214 -0.0285 0.7171 0.0150
-2.500 -0.0874 0.00837 0.00189 -0.0282 0.7123 0.0165
-2.250 -0.0608 0.00824 0.00175 -0.0280 0.7072 0.0178
-2.000 -0.0342 0.00814 0.00162 -0.0278 0.7026 0.0195
-1.750 -0.0072 0.00802 0.00149 -0.0277 0.6974 0.0220
-1.500 0.0195 0.00793 0.00140 -0.0275 0.6906 0.0255
-1.250 0.0464 0.00786 0.00131 -0.0274 0.6837 0.0287
-1.000 0.0733 0.00777 0.00123 -0.0272 0.6767 0.0352
-0.750 0.1001 0.00770 0.00116 -0.0271 0.6687 0.0437
-0.500 0.1266 0.00762 0.00110 -0.0268 0.6589 0.0612
-0.250 0.1389 0.00596 0.00083 -0.0246 0.6491 0.5342
0.000 0.1627 0.00573 0.00083 -0.0238 0.6372 0.6201
0.250 0.1888 0.00570 0.00082 -0.0235 0.6246 0.6479
0.500 0.2153 0.00567 0.00082 -0.0232 0.6159 0.6705
0.750 0.2425 0.00566 0.00083 -0.0231 0.6086 0.6843
1.000 0.2689 0.00565 0.00084 -0.0229 0.5989 0.7020
1.250 0.2951 0.00563 0.00087 -0.0226 0.5883 0.7248
1.500 0.3223 0.00565 0.00089 -0.0225 0.5785 0.7314
1.750 0.3492 0.00570 0.00092 -0.0223 0.5654 0.7394
2.000 0.3757 0.00576 0.00096 -0.0221 0.5488 0.7476
2.250 0.4018 0.00586 0.00101 -0.0219 0.5268 0.7569
2.500 0.4268 0.00601 0.00108 -0.0214 0.4917 0.7668
2.750 0.4503 0.00628 0.00120 -0.0207 0.4420 0.7782
3.000 0.4730 0.00661 0.00136 -0.0199 0.3879 0.7920
3.250 0.4961 0.00689 0.00152 -0.0191 0.3425 0.8076
3.500 0.5194 0.00714 0.00169 -0.0183 0.3056 0.8250
3.750 0.5420 0.00743 0.00187 -0.0175 0.2641 0.8446
4.000 0.5644 0.00770 0.00207 -0.0166 0.2262 0.8667
4.250 0.5881 0.00789 0.00224 -0.0159 0.2056 0.8925
4.500 0.6143 0.00802 0.00241 -0.0156 0.1926 0.9192
4.750 0.6445 0.00824 0.00261 -0.0164 0.1722 0.9413
5.000 0.6779 0.00860 0.00286 -0.0181 0.1415 0.9567
5.250 0.7112 0.00902 0.00315 -0.0198 0.1106 0.9675
5.500 0.7426 0.00952 0.00348 -0.0211 0.0769 0.9764
5.750 0.7735 0.01018 0.00394 -0.0224 0.0385 0.9824
6.000 0.8036 0.01053 0.00425 -0.0233 0.0297 0.9880
6.250 0.8338 0.01083 0.00454 -0.0242 0.0254 0.9928
6.500 0.8628 0.01117 0.00488 -0.0249 0.0215 0.9976
6.750 0.8933 0.01147 0.00519 -0.0259 0.0193 1.0000
7.000 0.9141 0.01175 0.00548 -0.0247 0.0176 1.0000
7.250 0.9344 0.01208 0.00580 -0.0234 0.0158 1.0000
7.500 0.9551 0.01239 0.00614 -0.0223 0.0143 1.0000
7.750 0.9759 0.01269 0.00646 -0.0211 0.0131 1.0000
8.000 0.9962 0.01303 0.00680 -0.0200 0.0117 1.0000
8.250 1.0158 0.01343 0.00722 -0.0186 0.0104 1.0000
8.500 1.0361 0.01377 0.00759 -0.0175 0.0098 1.0000
8.750 1.0560 0.01415 0.00800 -0.0163 0.0090 1.0000
9.000 1.0753 0.01457 0.00844 -0.0150 0.0083 1.0000
9.250 1.0939 0.01504 0.00895 -0.0136 0.0077 1.0000
9.500 1.1119 0.01555 0.00950 -0.0121 0.0074 1.0000
9.750 1.1304 0.01600 0.01001 -0.0108 0.0072 1.0000
10.000 1.1480 0.01650 0.01058 -0.0093 0.0069 1.0000
10.250 1.1649 0.01703 0.01116 -0.0078 0.0066 1.0000
10.500 1.1811 0.01757 0.01176 -0.0061 0.0065 1.0000
10.750 1.1952 0.01811 0.01235 -0.0041 0.0062 1.0000
11.000 1.2075 0.01868 0.01298 -0.0018 0.0060 1.0000
11.250 1.2205 0.01924 0.01358 0.0003 0.0057 1.0000
11.500 1.2302 0.02005 0.01446 0.0027 0.0055 1.0000
11.750 1.2375 0.02104 0.01554 0.0053 0.0053 1.0000
12.000 1.2473 0.02192 0.01651 0.0073 0.0052 1.0000
12.250 1.2577 0.02279 0.01746 0.0091 0.0051 1.0000
12.500 1.2669 0.02378 0.01854 0.0109 0.0051 1.0000
12.750 1.2773 0.02472 0.01957 0.0124 0.0049 1.0000
13.000 1.2845 0.02596 0.02091 0.0141 0.0049 1.0000
13.250 1.2905 0.02734 0.02239 0.0156 0.0049 1.0000
13.500 1.2991 0.02856 0.02370 0.0168 0.0047 1.0000
13.750 1.3041 0.03014 0.02540 0.0181 0.0046 1.0000
14.000 1.3056 0.03209 0.02747 0.0193 0.0046 1.0000
14.250 1.3108 0.03379 0.02926 0.0201 0.0044 1.0000
14.500 1.3139 0.03576 0.03135 0.0208 0.0043 1.0000
14.750 1.3134 0.03816 0.03387 0.0214 0.0044 1.0000
15.000 1.3145 0.04050 0.03631 0.0217 0.0042 1.0000
15.250 1.3124 0.04325 0.03919 0.0218 0.0042 1.0000
15.500 1.3057 0.04667 0.04275 0.0217 0.0042 1.0000
15.750 1.3092 0.04902 0.04517 0.0213 0.0040 1.0000
16.000 1.3025 0.05272 0.04901 0.0206 0.0041 1.0000
16.250 1.2884 0.05767 0.05412 0.0193 0.0040 1.0000
16.500 1.2872 0.06109 0.05762 0.0180 0.0039 1.0000
16.750 1.2771 0.06600 0.06266 0.0161 0.0039 1.0000
17.000 1.2586 0.07257 0.06939 0.0131 0.0039 1.0000
17.250 1.2358 0.08025 0.07724 0.0094 0.0040 1.0000
17.500 1.2220 0.08674 0.08385 0.0061 0.0039 1.0000
17.750 1.1983 0.09527 0.09253 0.0017 0.0039 1.0000
18.000 1.1747 0.10389 0.10128 -0.0027 0.0039 1.0000
18.250 1.1485 0.11329 0.11082 -0.0075 0.0040 1.0000
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