KC-135 BL351.6 AIRFOIL (kc135d-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
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Airfoil: KC-135 BL351.6 AIRFOIL (kc135d-il) Reynolds number: 1,000,000 Max Cl/Cd: 114.87 at α=3.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-kc135d-il-1000000.txt Download as CSV file: xf-kc135d-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.4770 0.06984 0.06827 -0.0391 1.0000 0.0079
-7.750 -0.4798 0.06631 0.06471 -0.0394 1.0000 0.0079
-7.500 -0.4830 0.06308 0.06145 -0.0386 1.0000 0.0079
-7.250 -0.4668 0.05896 0.05725 -0.0421 0.9965 0.0080
-7.000 -0.4473 0.05487 0.05307 -0.0456 0.9892 0.0082
-6.750 -0.4238 0.05072 0.04880 -0.0494 0.9834 0.0084
-6.500 -0.3992 0.04680 0.04475 -0.0525 0.9756 0.0088
-6.250 -0.3710 0.04275 0.04052 -0.0556 0.9681 0.0094
-6.000 -0.3358 0.03898 0.03647 -0.0569 0.9572 0.0110
-5.500 -0.2933 0.01767 0.01477 -0.0507 0.8874 0.0111
-5.250 -0.2869 0.01269 0.00945 -0.0493 0.8760 0.0117
-5.000 -0.2682 0.01114 0.00775 -0.0486 0.8664 0.0120
-4.750 -0.2479 0.00995 0.00642 -0.0480 0.8572 0.0126
-4.500 -0.2258 0.00870 0.00499 -0.0472 0.8484 0.0139
-4.250 -0.2040 0.01551 0.01073 -0.0473 0.8627 0.0114
-4.000 -0.1804 0.01432 0.00937 -0.0466 0.8538 0.0121
-3.750 -0.1549 0.01415 0.00914 -0.0464 0.8450 0.0129
-3.500 -0.1293 0.01292 0.00773 -0.0457 0.8371 0.0137
-3.250 -0.1036 0.01174 0.00637 -0.0450 0.8294 0.0144
-3.000 -0.0769 0.01140 0.00595 -0.0446 0.8215 0.0154
-2.750 -0.0530 0.01003 0.00443 -0.0438 0.8143 0.0169
-2.500 -0.0275 0.00955 0.00394 -0.0434 0.8067 0.0178
-2.250 -0.0019 0.00922 0.00355 -0.0429 0.7998 0.0189
-2.000 0.0240 0.00888 0.00319 -0.0425 0.7920 0.0202
-1.750 0.0498 0.00863 0.00289 -0.0421 0.7843 0.0216
-1.500 0.0761 0.00844 0.00265 -0.0417 0.7757 0.0224
-1.250 0.1004 0.00797 0.00210 -0.0410 0.7667 0.0234
-1.000 0.1251 0.00759 0.00163 -0.0404 0.7570 0.0257
-0.750 0.1515 0.00744 0.00144 -0.0401 0.7465 0.0285
-0.500 0.1781 0.00731 0.00127 -0.0398 0.7371 0.0308
-0.250 0.2048 0.00724 0.00114 -0.0396 0.7287 0.0326
0.000 0.2317 0.00710 0.00098 -0.0394 0.7211 0.0412
0.250 0.2450 0.00535 0.00086 -0.0372 0.7137 0.6307
0.500 0.2672 0.00500 0.00087 -0.0361 0.7054 0.7406
0.750 0.2899 0.00478 0.00089 -0.0348 0.6976 0.8184
1.000 0.3132 0.00463 0.00093 -0.0337 0.6888 0.8860
1.250 0.3434 0.00458 0.00100 -0.0340 0.6802 0.9393
1.500 0.3845 0.00465 0.00106 -0.0369 0.6710 0.9660
1.750 0.4252 0.00474 0.00112 -0.0398 0.6600 0.9770
2.000 0.4573 0.00481 0.00116 -0.0408 0.6490 0.9833
2.250 0.4942 0.00489 0.00120 -0.0429 0.6356 0.9861
2.500 0.5296 0.00497 0.00124 -0.0447 0.6209 0.9897
2.750 0.5633 0.00509 0.00130 -0.0462 0.6024 0.9935
3.000 0.5980 0.00521 0.00135 -0.0479 0.5767 0.9963
3.250 0.6318 0.00550 0.00144 -0.0495 0.5182 0.9991
3.500 0.6560 0.00595 0.00158 -0.0491 0.4433 1.0000
3.750 0.6734 0.00652 0.00180 -0.0473 0.3601 1.0000
4.000 0.6916 0.00706 0.00204 -0.0457 0.2949 1.0000
4.250 0.7118 0.00746 0.00226 -0.0444 0.2505 1.0000
4.500 0.7334 0.00775 0.00244 -0.0433 0.2240 1.0000
4.750 0.7552 0.00804 0.00264 -0.0423 0.1999 1.0000
5.000 0.7769 0.00836 0.00284 -0.0413 0.1731 1.0000
5.250 0.7977 0.00875 0.00308 -0.0401 0.1397 1.0000
5.500 0.8153 0.00942 0.00348 -0.0384 0.0829 1.0000
5.750 0.8316 0.01025 0.00402 -0.0365 0.0322 1.0000
6.000 0.8524 0.01071 0.00445 -0.0353 0.0228 1.0000
6.250 0.8748 0.01102 0.00479 -0.0344 0.0202 1.0000
6.500 0.8956 0.01150 0.00529 -0.0331 0.0164 1.0000
6.750 0.9165 0.01197 0.00583 -0.0319 0.0146 1.0000
7.000 0.9385 0.01235 0.00624 -0.0310 0.0133 1.0000
7.250 0.9599 0.01278 0.00672 -0.0299 0.0123 1.0000
7.500 0.9801 0.01334 0.00731 -0.0287 0.0113 1.0000
7.750 0.9939 0.01452 0.00865 -0.0263 0.0103 1.0000
8.000 1.0132 0.01515 0.00935 -0.0250 0.0100 1.0000
8.250 1.0343 0.01561 0.00985 -0.0240 0.0094 1.0000
8.500 1.0539 0.01619 0.01050 -0.0228 0.0090 1.0000
8.750 1.0723 0.01688 0.01126 -0.0214 0.0085 1.0000
9.000 1.0895 0.01768 0.01213 -0.0198 0.0082 1.0000
9.250 1.1058 0.01858 0.01313 -0.0182 0.0080 1.0000
9.500 1.1230 0.01932 0.01393 -0.0167 0.0077 1.0000
9.750 1.1379 0.02029 0.01498 -0.0150 0.0075 1.0000
10.000 1.1500 0.02159 0.01638 -0.0129 0.0072 1.0000
10.250 1.1597 0.02332 0.01825 -0.0105 0.0071 1.0000
10.500 1.1611 0.02680 0.02204 -0.0073 0.0067 1.0000
10.750 1.1713 0.02744 0.02279 -0.0048 0.0066 1.0000
11.000 1.1822 0.02779 0.02322 -0.0025 0.0063 1.0000
11.250 1.1852 0.02964 0.02526 0.0005 0.0062 1.0000
11.500 1.1932 0.03044 0.02617 0.0026 0.0059 1.0000
11.750 1.1899 0.03296 0.02891 0.0056 0.0060 1.0000
12.000 1.1898 0.03479 0.03091 0.0079 0.0058 1.0000
12.250 1.1849 0.03725 0.03356 0.0102 0.0056 1.0000
12.500 1.1744 0.04042 0.03696 0.0123 0.0056 1.0000
12.750 1.1687 0.04305 0.03974 0.0135 0.0055 1.0000
13.000 1.1480 0.04778 0.04473 0.0145 0.0055 1.0000
13.250 1.1454 0.05036 0.04741 0.0145 0.0054 1.0000
13.500 1.1261 0.05548 0.05273 0.0138 0.0054 1.0000
13.750 1.0987 0.06234 0.05983 0.0118 0.0055 1.0000
14.000 1.0684 0.07051 0.06821 0.0080 0.0056 1.0000
14.250 1.0361 0.08033 0.07824 0.0023 0.0058 1.0000
14.500 1.0417 0.08338 0.08132 0.0001 0.0054 1.0000
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Polar data table (+)
Polar graphs
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