KC-135 BL124.32 AIRFOIL (kc135b-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: KC-135 BL124.32 AIRFOIL (kc135b-il) Reynolds number: 50,000 Max Cl/Cd: 31.77 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-kc135b-il-50000-n5.txt Download as CSV file: xf-kc135b-il-50000-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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.000 -0.4974 0.13276 0.12535 -0.0219 1.0000 0.1344
-11.750 -0.4785 0.12817 0.12076 -0.0205 1.0000 0.1390
-11.500 -0.4791 0.12512 0.11775 -0.0218 1.0000 0.1483
-11.250 -0.4770 0.12123 0.11392 -0.0226 1.0000 0.1541
-11.000 -0.4697 0.11790 0.11060 -0.0228 1.0000 0.1611
-10.500 -0.3945 0.09284 0.08603 -0.0399 1.0000 0.0708
-10.250 -0.3979 0.08788 0.08109 -0.0414 1.0000 0.0683
-10.000 -0.4117 0.08158 0.07482 -0.0446 1.0000 0.0657
-9.750 -0.4403 0.07470 0.06792 -0.0486 1.0000 0.0634
-9.500 -0.4886 0.06908 0.06219 -0.0510 1.0000 0.0615
-9.000 -0.5961 0.07275 0.06520 -0.0441 1.0000 0.0595
-8.750 -0.5971 0.06930 0.06172 -0.0427 1.0000 0.0587
-8.500 -0.6009 0.06618 0.05850 -0.0408 1.0000 0.0579
-8.250 -0.6052 0.06322 0.05542 -0.0384 1.0000 0.0572
-8.000 -0.6091 0.06042 0.05248 -0.0357 1.0000 0.0566
-7.750 -0.6118 0.05782 0.04971 -0.0328 1.0000 0.0560
-7.500 -0.6142 0.05534 0.04704 -0.0297 1.0000 0.0555
-7.250 -0.6162 0.05309 0.04458 -0.0262 1.0000 0.0550
-7.000 -0.6177 0.05103 0.04231 -0.0227 1.0000 0.0548
-6.750 -0.6181 0.04915 0.04019 -0.0192 1.0000 0.0550
-6.500 -0.6169 0.04738 0.03816 -0.0158 1.0000 0.0557
-6.250 -0.6120 0.04561 0.03609 -0.0129 0.9994 0.0566
-6.000 -0.5829 0.04302 0.03297 -0.0143 0.9905 0.0576
-5.750 -0.5521 0.04054 0.03005 -0.0155 0.9823 0.0580
-5.500 -0.5188 0.03829 0.02739 -0.0169 0.9750 0.0584
-5.250 -0.4871 0.03650 0.02518 -0.0177 0.9668 0.0596
-5.000 -0.4530 0.03445 0.02297 -0.0193 0.9602 0.0625
-4.750 -0.4176 0.03287 0.02132 -0.0209 0.9534 0.0653
-4.500 -0.3757 0.03143 0.01976 -0.0230 0.9490 0.0677
-4.250 -0.3424 0.03047 0.01862 -0.0236 0.9412 0.0721
-4.000 -0.3054 0.02929 0.01743 -0.0251 0.9358 0.0769
-3.750 -0.2772 0.02840 0.01647 -0.0254 0.9280 0.0813
-3.500 -0.2474 0.02761 0.01550 -0.0261 0.9208 0.0890
-3.250 -0.2231 0.02669 0.01454 -0.0262 0.9126 0.0967
-3.000 -0.1960 0.02585 0.01361 -0.0267 0.9051 0.1091
-2.750 -0.1713 0.02496 0.01274 -0.0268 0.8975 0.1308
-2.500 -0.1689 0.02243 0.01247 -0.0231 0.8891 0.5289
-2.250 -0.1555 0.02266 0.01302 -0.0184 0.8809 0.6843
-2.000 -0.1345 0.02311 0.01355 -0.0149 0.8741 0.7566
-1.750 -0.0967 0.02399 0.01444 -0.0130 0.8705 0.8214
-1.500 -0.0482 0.02484 0.01513 -0.0144 0.8658 0.8579
-1.250 -0.0181 0.02479 0.01488 -0.0153 0.8587 0.8667
-1.000 0.0238 0.02471 0.01461 -0.0183 0.8542 0.8731
-0.750 0.0479 0.02478 0.01458 -0.0183 0.8453 0.8826
-0.500 0.0885 0.02476 0.01442 -0.0211 0.8402 0.8894
-0.250 0.1187 0.02484 0.01441 -0.0222 0.8330 0.8990
0.000 0.1575 0.02490 0.01439 -0.0249 0.8267 0.9062
0.250 0.1984 0.02488 0.01428 -0.0277 0.8222 0.9145
0.500 0.2318 0.02509 0.01447 -0.0297 0.8141 0.9233
0.750 0.2690 0.02512 0.01447 -0.0320 0.8084 0.9330
1.000 0.3097 0.02526 0.01461 -0.0353 0.8019 0.9410
1.250 0.3461 0.02539 0.01475 -0.0376 0.7949 0.9513
1.500 0.3896 0.02536 0.01473 -0.0410 0.7901 0.9600
1.750 0.4225 0.02565 0.01509 -0.0432 0.7810 0.9721
2.000 0.4670 0.02553 0.01502 -0.0466 0.7747 0.9810
2.250 0.5036 0.02558 0.01514 -0.0491 0.7629 0.9929
2.500 0.5345 0.02550 0.01511 -0.0501 0.7511 1.0000
2.750 0.5526 0.02538 0.01502 -0.0483 0.7409 1.0000
3.000 0.5609 0.02559 0.01525 -0.0453 0.7289 1.0000
3.250 0.5696 0.02585 0.01554 -0.0422 0.7170 1.0000
3.500 0.5856 0.02589 0.01560 -0.0400 0.7051 1.0000
3.750 0.6070 0.02572 0.01548 -0.0383 0.6929 1.0000
4.000 0.6247 0.02566 0.01547 -0.0360 0.6790 1.0000
4.250 0.6401 0.02570 0.01556 -0.0335 0.6642 1.0000
4.500 0.6566 0.02573 0.01565 -0.0312 0.6493 1.0000
4.750 0.6740 0.02574 0.01575 -0.0290 0.6342 1.0000
5.000 0.6923 0.02570 0.01580 -0.0268 0.6185 1.0000
5.250 0.7115 0.02561 0.01580 -0.0247 0.6019 1.0000
5.500 0.7281 0.02563 0.01591 -0.0223 0.5834 1.0000
5.750 0.7426 0.02571 0.01612 -0.0196 0.5621 1.0000
6.000 0.7627 0.02554 0.01603 -0.0175 0.5401 1.0000
6.250 0.7771 0.02565 0.01623 -0.0149 0.5131 1.0000
6.500 0.7940 0.02569 0.01631 -0.0125 0.4832 1.0000
6.750 0.8116 0.02576 0.01637 -0.0101 0.4498 1.0000
7.000 0.8270 0.02603 0.01654 -0.0076 0.4140 1.0000
7.250 0.8410 0.02652 0.01687 -0.0051 0.3794 1.0000
7.500 0.8535 0.02723 0.01739 -0.0026 0.3486 1.0000
7.750 0.8648 0.02813 0.01813 -0.0001 0.3218 1.0000
8.000 0.8754 0.02914 0.01900 0.0022 0.2974 1.0000
8.250 0.8838 0.03021 0.02004 0.0047 0.2729 1.0000
8.500 0.8891 0.03131 0.02103 0.0074 0.2502 1.0000
8.750 0.8918 0.03244 0.02216 0.0104 0.2273 1.0000
9.000 0.8946 0.03368 0.02334 0.0130 0.2071 1.0000
9.250 0.8981 0.03504 0.02468 0.0153 0.1870 1.0000
9.500 0.9016 0.03654 0.02618 0.0173 0.1672 1.0000
9.750 0.9051 0.03819 0.02779 0.0191 0.1491 1.0000
10.000 0.9083 0.03997 0.02952 0.0208 0.1326 1.0000
10.250 0.9129 0.04184 0.03137 0.0222 0.1174 1.0000
10.500 0.9176 0.04376 0.03328 0.0234 0.1054 1.0000
10.750 0.9253 0.04569 0.03530 0.0246 0.0952 1.0000
11.000 0.9336 0.04767 0.03737 0.0256 0.0869 1.0000
11.250 0.9406 0.04964 0.03928 0.0265 0.0811 1.0000
11.500 0.9535 0.05175 0.04165 0.0275 0.0753 1.0000
11.750 0.9622 0.05383 0.04380 0.0283 0.0710 1.0000
12.000 0.9703 0.05623 0.04635 0.0290 0.0672 1.0000
12.250 0.9749 0.05902 0.04944 0.0296 0.0640 1.0000
12.500 0.9789 0.06183 0.05245 0.0301 0.0617 1.0000
12.750 0.9835 0.06451 0.05520 0.0305 0.0596 1.0000
13.000 0.9828 0.06787 0.05870 0.0306 0.0578 1.0000
13.250 0.9714 0.07236 0.06353 0.0300 0.0568 1.0000
13.500 0.9564 0.07740 0.06886 0.0288 0.0560 1.0000
13.750 0.9385 0.08315 0.07487 0.0269 0.0557 1.0000
14.000 0.9155 0.08998 0.08194 0.0239 0.0555 1.0000
14.250 0.8883 0.09825 0.09041 0.0196 0.0558 1.0000
14.500 0.8588 0.10805 0.10038 0.0141 0.0566 1.0000
14.750 0.8289 0.11928 0.11169 0.0077 0.0574 1.0000
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