KC-135 BL52.44 AIRFOIL (kc135a-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: KC-135 BL52.44 AIRFOIL (kc135a-il) Reynolds number: 200,000 Max Cl/Cd: 62.1 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-kc135a-il-200000-n5.txt Download as CSV file: xf-kc135a-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: KC-135 BL52.44 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.750 -0.5931 0.09563 0.09154 -0.0411 1.0000 0.0216
-13.500 -0.6141 0.08718 0.08302 -0.0464 1.0000 0.0213
-13.250 -0.6478 0.07779 0.07349 -0.0523 1.0000 0.0212
-13.000 -0.6721 0.07125 0.06682 -0.0558 1.0000 0.0210
-12.750 -0.7030 0.06455 0.05991 -0.0587 1.0000 0.0210
-12.500 -0.7248 0.05966 0.05484 -0.0600 1.0000 0.0209
-12.250 -0.7461 0.05523 0.05021 -0.0603 1.0000 0.0209
-12.000 -0.7682 0.05106 0.04579 -0.0595 1.0000 0.0210
-11.750 -0.7856 0.04762 0.04211 -0.0577 1.0000 0.0211
-11.500 -0.8010 0.04454 0.03875 -0.0551 1.0000 0.0212
-11.250 -0.8131 0.04183 0.03577 -0.0517 1.0000 0.0213
-11.000 -0.8218 0.03949 0.03316 -0.0479 1.0000 0.0214
-10.750 -0.8282 0.03730 0.03068 -0.0438 1.0000 0.0216
-10.500 -0.8252 0.03556 0.02877 -0.0409 1.0000 0.0218
-10.250 -0.8177 0.03446 0.02762 -0.0384 1.0000 0.0220
-10.000 -0.8095 0.03344 0.02654 -0.0359 1.0000 0.0223
-9.750 -0.8012 0.03249 0.02552 -0.0333 1.0000 0.0227
-9.500 -0.7865 0.03143 0.02438 -0.0320 0.9970 0.0232
-9.250 -0.7571 0.02971 0.02245 -0.0334 0.9845 0.0239
-9.000 -0.7252 0.02787 0.02036 -0.0351 0.9732 0.0247
-8.750 -0.6911 0.02618 0.01841 -0.0369 0.9602 0.0254
-8.500 -0.6558 0.02477 0.01691 -0.0391 0.9451 0.0260
-8.250 -0.6199 0.02370 0.01580 -0.0414 0.9278 0.0269
-8.000 -0.5844 0.02263 0.01464 -0.0435 0.9081 0.0278
-7.750 -0.5519 0.02165 0.01353 -0.0449 0.8868 0.0290
-7.500 -0.5238 0.02079 0.01250 -0.0453 0.8654 0.0303
-7.250 -0.5003 0.02017 0.01186 -0.0449 0.8452 0.0317
-7.000 -0.4789 0.01962 0.01122 -0.0440 0.8274 0.0333
-6.750 -0.4589 0.01908 0.01053 -0.0428 0.8121 0.0350
-6.500 -0.4409 0.01849 0.00987 -0.0412 0.7987 0.0362
-6.250 -0.4221 0.01802 0.00934 -0.0398 0.7869 0.0380
-6.000 -0.4025 0.01762 0.00885 -0.0384 0.7758 0.0405
-5.750 -0.3840 0.01714 0.00830 -0.0369 0.7661 0.0428
-5.500 -0.3643 0.01673 0.00785 -0.0355 0.7572 0.0454
-5.250 -0.3435 0.01639 0.00741 -0.0343 0.7492 0.0487
-5.000 -0.3243 0.01593 0.00692 -0.0329 0.7413 0.0518
-4.750 -0.3029 0.01561 0.00651 -0.0318 0.7343 0.0562
-4.500 -0.2821 0.01523 0.00610 -0.0306 0.7266 0.0611
-4.250 -0.2600 0.01494 0.00572 -0.0296 0.7200 0.0680
-4.000 -0.2384 0.01456 0.00538 -0.0285 0.7132 0.0803
-3.750 -0.2184 0.01407 0.00501 -0.0272 0.7069 0.1156
-3.250 -0.2008 0.01187 0.00440 -0.0211 0.6955 0.4975
-3.000 -0.1769 0.01184 0.00440 -0.0201 0.6895 0.5323
-2.750 -0.1519 0.01188 0.00436 -0.0194 0.6844 0.5562
-2.500 -0.1271 0.01189 0.00439 -0.0186 0.6782 0.5766
-2.250 -0.1018 0.01192 0.00439 -0.0180 0.6725 0.5938
-2.000 -0.0761 0.01197 0.00436 -0.0174 0.6679 0.6084
-1.750 -0.0500 0.01196 0.00438 -0.0169 0.6628 0.6201
-1.500 -0.0235 0.01196 0.00433 -0.0166 0.6574 0.6284
-1.250 0.0039 0.01193 0.00426 -0.0164 0.6524 0.6333
-1.000 0.0312 0.01193 0.00419 -0.0163 0.6477 0.6384
-0.750 0.0582 0.01192 0.00415 -0.0161 0.6423 0.6436
-0.500 0.0856 0.01190 0.00411 -0.0160 0.6374 0.6479
-0.250 0.1130 0.01189 0.00408 -0.0159 0.6330 0.6530
0.000 0.1400 0.01190 0.00407 -0.0157 0.6277 0.6589
0.250 0.1670 0.01190 0.00407 -0.0156 0.6223 0.6642
0.500 0.1942 0.01189 0.00406 -0.0154 0.6174 0.6693
0.750 0.2213 0.01190 0.00406 -0.0152 0.6124 0.6756
1.000 0.2480 0.01191 0.00410 -0.0150 0.6067 0.6819
1.250 0.2749 0.01191 0.00412 -0.0148 0.6017 0.6882
1.500 0.3021 0.01194 0.00413 -0.0147 0.5971 0.6952
1.750 0.3285 0.01195 0.00421 -0.0144 0.5910 0.7022
2.000 0.3548 0.01194 0.00422 -0.0140 0.5838 0.7104
2.250 0.3806 0.01192 0.00424 -0.0136 0.5746 0.7189
2.500 0.4066 0.01191 0.00424 -0.0131 0.5661 0.7283
2.750 0.4325 0.01192 0.00433 -0.0127 0.5586 0.7383
3.000 0.4585 0.01194 0.00439 -0.0123 0.5515 0.7502
3.250 0.4845 0.01196 0.00449 -0.0119 0.5444 0.7629
3.500 0.5103 0.01198 0.00460 -0.0115 0.5367 0.7772
3.750 0.5365 0.01201 0.00470 -0.0111 0.5293 0.7934
4.000 0.5630 0.01205 0.00485 -0.0108 0.5207 0.8121
4.250 0.5906 0.01210 0.00499 -0.0107 0.5119 0.8333
4.500 0.6198 0.01217 0.00515 -0.0109 0.5018 0.8563
4.750 0.6519 0.01227 0.00534 -0.0118 0.4902 0.8785
5.000 0.6864 0.01240 0.00554 -0.0132 0.4771 0.8996
5.250 0.7222 0.01256 0.00573 -0.0150 0.4613 0.9190
5.500 0.7576 0.01275 0.00595 -0.0167 0.4423 0.9360
5.750 0.7911 0.01298 0.00615 -0.0181 0.4182 0.9509
6.000 0.8234 0.01330 0.00639 -0.0194 0.3870 0.9641
6.250 0.8539 0.01375 0.00671 -0.0205 0.3542 0.9768
6.500 0.8839 0.01430 0.00712 -0.0216 0.3226 0.9887
6.750 0.9150 0.01491 0.00761 -0.0232 0.2932 0.9993
7.000 0.9275 0.01539 0.00800 -0.0207 0.2746 1.0000
7.250 0.9385 0.01585 0.00840 -0.0179 0.2586 1.0000
7.750 0.9608 0.01681 0.00926 -0.0125 0.2305 1.0000
8.000 0.9710 0.01731 0.00972 -0.0097 0.2170 1.0000
8.250 0.9798 0.01785 0.01021 -0.0067 0.2028 1.0000
8.500 0.9876 0.01841 0.01072 -0.0035 0.1898 1.0000
8.750 0.9926 0.01896 0.01123 0.0001 0.1781 1.0000
9.000 0.9987 0.01955 0.01178 0.0033 0.1675 1.0000
9.250 1.0077 0.02013 0.01237 0.0060 0.1579 1.0000
9.500 1.0155 0.02082 0.01305 0.0086 0.1490 1.0000
9.750 1.0241 0.02156 0.01379 0.0109 0.1396 1.0000
10.000 1.0335 0.02233 0.01458 0.0129 0.1311 1.0000
10.250 1.0412 0.02326 0.01550 0.0149 0.1231 1.0000
10.500 1.0503 0.02419 0.01645 0.0166 0.1140 1.0000
10.750 1.0587 0.02522 0.01750 0.0182 0.1063 1.0000
11.000 1.0655 0.02643 0.01870 0.0197 0.0982 1.0000
11.250 1.0739 0.02760 0.01990 0.0210 0.0901 1.0000
11.500 1.0807 0.02894 0.02125 0.0222 0.0820 1.0000
11.750 1.0864 0.03042 0.02273 0.0233 0.0748 1.0000
12.000 1.0915 0.03201 0.02432 0.0244 0.0671 1.0000
12.250 1.0972 0.03361 0.02596 0.0253 0.0607 1.0000
12.500 1.1012 0.03539 0.02777 0.0261 0.0558 1.0000
12.750 1.1048 0.03727 0.02967 0.0268 0.0514 1.0000
13.000 1.1078 0.03924 0.03169 0.0275 0.0484 1.0000
13.250 1.1108 0.04127 0.03378 0.0280 0.0453 1.0000
13.500 1.1110 0.04360 0.03614 0.0284 0.0431 1.0000
13.750 1.1134 0.04579 0.03843 0.0287 0.0412 1.0000
14.000 1.1149 0.04813 0.04085 0.0289 0.0393 1.0000
14.250 1.1150 0.05069 0.04347 0.0289 0.0380 1.0000
14.500 1.1127 0.05359 0.04641 0.0288 0.0366 1.0000
14.750 1.1135 0.05624 0.04918 0.0286 0.0355 1.0000
15.000 1.1136 0.05905 0.05209 0.0283 0.0344 1.0000
15.250 1.1128 0.06206 0.05518 0.0278 0.0332 1.0000
15.500 1.1105 0.06531 0.05851 0.0271 0.0323 1.0000
15.750 1.1067 0.06882 0.06207 0.0263 0.0316 1.0000
16.000 1.1046 0.07220 0.06555 0.0255 0.0309 1.0000
16.250 1.1033 0.07556 0.06905 0.0246 0.0301 1.0000
16.500 1.1015 0.07907 0.07266 0.0236 0.0293 1.0000
16.750 1.0987 0.08277 0.07646 0.0224 0.0287 1.0000
17.000 1.0951 0.08668 0.08046 0.0210 0.0280 1.0000
17.250 1.0915 0.09065 0.08452 0.0195 0.0275 1.0000
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