KC-135 BL200.76 AIRFOIL (kc135c-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: KC-135 BL200.76 AIRFOIL (kc135c-il) Reynolds number: 100,000 Max Cl/Cd: 52.04 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-kc135c-il-100000.txt Download as CSV file: xf-kc135c-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.3755 0.10574 0.10098 -0.0259 1.0000 0.0770
-10.250 -0.3827 0.10207 0.09735 -0.0284 1.0000 0.0792
-10.000 -0.4712 0.10482 0.09977 -0.0254 1.0000 0.0715
-9.750 -0.4688 0.10127 0.09625 -0.0265 1.0000 0.0739
-9.500 -0.4711 0.09751 0.09254 -0.0288 1.0000 0.0771
-9.250 -0.4786 0.09341 0.08852 -0.0327 1.0000 0.0789
-9.000 -0.4928 0.08886 0.08404 -0.0380 1.0000 0.0797
-8.750 -0.5075 0.08540 0.08060 -0.0399 1.0000 0.0799
-8.500 -0.5317 0.08326 0.07839 -0.0402 1.0000 0.0805
-8.250 -0.5506 0.08168 0.07664 -0.0394 1.0000 0.0809
-8.000 -0.5237 0.07402 0.06929 -0.0389 1.0000 0.0848
-7.750 -0.5234 0.07095 0.06622 -0.0378 1.0000 0.0877
-7.500 -0.5293 0.06813 0.06335 -0.0367 1.0000 0.0909
-7.250 -0.5497 0.06785 0.06272 -0.0341 1.0000 0.0951
-7.000 -0.5541 0.06367 0.05852 -0.0321 1.0000 0.0971
-6.750 -0.5460 0.05978 0.05483 -0.0302 1.0000 0.1006
-6.500 -0.5499 0.05779 0.05278 -0.0270 1.0000 0.1057
-6.250 -0.5666 0.05730 0.05187 -0.0224 1.0000 0.1115
-6.000 -0.5609 0.05341 0.04820 -0.0205 1.0000 0.1152
-5.750 -0.5686 0.05286 0.04724 -0.0167 1.0000 0.1262
-5.500 -0.5468 0.03785 0.03303 -0.0141 1.0000 0.1305
-5.250 -0.5473 0.03551 0.03050 -0.0119 1.0000 0.1431
-5.000 -0.5563 0.04463 0.03900 -0.0103 1.0000 0.1598
-4.500 -0.5484 0.04133 0.03538 -0.0058 1.0000 0.2133
-4.250 -0.5317 0.03786 0.03219 -0.0056 0.9970 0.2531
-4.000 -0.5077 0.03504 0.02938 -0.0063 0.9916 0.2967
-3.750 -0.4748 0.03257 0.02656 -0.0081 0.9859 0.3133
-3.500 -0.4313 0.02979 0.02318 -0.0106 0.9810 0.2801
-3.250 -0.3521 0.02961 0.02077 -0.0106 0.9760 0.0946
-3.000 -0.3140 0.02718 0.01814 -0.0121 0.9720 0.0874
-2.750 -0.2783 0.02625 0.01673 -0.0126 0.9665 0.0824
-2.500 -0.2433 0.02506 0.01539 -0.0136 0.9613 0.0802
-2.250 -0.2039 0.02380 0.01405 -0.0155 0.9573 0.0803
-2.000 -0.1747 0.02256 0.01292 -0.0160 0.9517 0.0852
-1.750 -0.1442 0.02174 0.01218 -0.0165 0.9459 0.0901
-1.500 -0.1081 0.02114 0.01153 -0.0181 0.9415 0.0964
-1.250 -0.0890 0.02066 0.01103 -0.0169 0.9336 0.1093
-1.000 -0.0556 0.01997 0.01042 -0.0181 0.9285 0.1445
-0.750 -0.0118 0.01835 0.01179 -0.0158 0.9291 0.9381
-0.500 0.1941 0.01917 0.01207 -0.0474 0.9455 1.0000
-0.250 0.2272 0.01912 0.01193 -0.0499 0.9380 1.0000
0.000 0.2590 0.01907 0.01182 -0.0520 0.9301 1.0000
0.250 0.2862 0.01908 0.01179 -0.0533 0.9217 1.0000
0.500 0.3237 0.01902 0.01168 -0.0562 0.9149 1.0000
0.750 0.3450 0.01910 0.01175 -0.0562 0.9053 1.0000
1.000 0.3886 0.01894 0.01158 -0.0597 0.8989 1.0000
1.250 0.4166 0.01879 0.01143 -0.0601 0.8865 1.0000
1.500 0.4566 0.01827 0.01094 -0.0618 0.8726 1.0000
1.750 0.4865 0.01787 0.01054 -0.0616 0.8582 1.0000
2.000 0.5060 0.01780 0.01049 -0.0600 0.8461 1.0000
2.250 0.5282 0.01775 0.01045 -0.0588 0.8358 1.0000
2.500 0.5510 0.01767 0.01040 -0.0576 0.8255 1.0000
2.750 0.5666 0.01779 0.01057 -0.0553 0.8130 1.0000
3.000 0.5847 0.01784 0.01067 -0.0532 0.8007 1.0000
3.250 0.6049 0.01783 0.01071 -0.0513 0.7882 1.0000
3.500 0.6263 0.01774 0.01067 -0.0494 0.7750 1.0000
3.750 0.6482 0.01759 0.01062 -0.0475 0.7610 1.0000
4.000 0.6701 0.01739 0.01049 -0.0455 0.7456 1.0000
4.250 0.6928 0.01712 0.01029 -0.0436 0.7289 1.0000
4.500 0.7170 0.01674 0.00997 -0.0416 0.7107 1.0000
4.750 0.7377 0.01648 0.00982 -0.0393 0.6884 1.0000
5.000 0.7598 0.01613 0.00952 -0.0370 0.6626 1.0000
5.250 0.7786 0.01585 0.00931 -0.0342 0.6286 1.0000
5.500 0.7965 0.01553 0.00893 -0.0311 0.5792 1.0000
5.750 0.8092 0.01555 0.00871 -0.0274 0.5007 1.0000
6.000 0.8194 0.01618 0.00879 -0.0237 0.4183 1.0000
6.250 0.8310 0.01707 0.00931 -0.0208 0.3612 1.0000
6.500 0.8438 0.01795 0.00996 -0.0183 0.3160 1.0000
6.750 0.8560 0.01883 0.01067 -0.0159 0.2708 1.0000
7.000 0.8641 0.01995 0.01152 -0.0128 0.2099 1.0000
7.250 0.8651 0.02188 0.01279 -0.0088 0.1257 1.0000
7.500 0.8738 0.02356 0.01419 -0.0058 0.0997 1.0000
7.750 0.8863 0.02508 0.01559 -0.0036 0.0859 1.0000
8.000 0.9037 0.02663 0.01716 -0.0019 0.0769 1.0000
8.250 0.9257 0.02870 0.01914 -0.0011 0.0703 1.0000
8.500 0.9470 0.03028 0.02088 -0.0001 0.0641 1.0000
8.750 0.9771 0.03350 0.02401 -0.0008 0.0598 1.0000
9.000 0.9982 0.03574 0.02667 0.0005 0.0580 1.0000
9.250 1.0148 0.03800 0.02932 0.0021 0.0555 1.0000
9.500 1.0293 0.04044 0.03206 0.0038 0.0531 1.0000
9.750 1.0402 0.04353 0.03555 0.0058 0.0527 1.0000
10.000 1.0442 0.04701 0.03950 0.0085 0.0528 1.0000
10.250 1.0413 0.05079 0.04376 0.0116 0.0537 1.0000
10.500 1.0327 0.05470 0.04812 0.0148 0.0546 1.0000
10.750 1.0201 0.05845 0.05220 0.0180 0.0557 1.0000
11.000 1.0036 0.06201 0.05599 0.0213 0.0566 1.0000
11.250 0.9863 0.06581 0.05999 0.0236 0.0574 1.0000
11.500 0.9696 0.06996 0.06430 0.0248 0.0582 1.0000
11.750 0.9583 0.07510 0.06952 0.0251 0.0593 1.0000
12.000 0.8313 0.07224 0.06715 0.0273 0.0584 1.0000
12.250 0.8068 0.07858 0.07360 0.0255 0.0590 1.0000
12.500 0.7980 0.08486 0.07994 0.0244 0.0601 1.0000
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Polar data table (+)
Polar graphs
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