KC-135 BL52.44 AIRFOIL (kc135a-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: KC-135 BL52.44 AIRFOIL (kc135a-il) Reynolds number: 1,000,000 Max Cl/Cd: 97.79 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-kc135a-il-1000000.txt Download as CSV file: xf-kc135a-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.750 -0.8239 0.08024 0.07796 -0.0455 1.0000 0.0145
-15.500 -0.8770 0.06810 0.06554 -0.0525 1.0000 0.0144
-15.250 -0.8979 0.06208 0.05934 -0.0555 1.0000 0.0145
-15.000 -0.9356 0.05438 0.05138 -0.0584 1.0000 0.0143
-14.750 -0.9631 0.04845 0.04519 -0.0598 1.0000 0.0143
-14.500 -0.9756 0.04454 0.04109 -0.0603 1.0000 0.0143
-14.250 -0.9866 0.04096 0.03731 -0.0603 1.0000 0.0144
-14.000 -0.9926 0.03805 0.03421 -0.0598 1.0000 0.0145
-13.750 -0.9973 0.03532 0.03129 -0.0589 1.0000 0.0146
-13.500 -0.9955 0.03334 0.02918 -0.0579 1.0000 0.0146
-13.250 -0.9924 0.03160 0.02730 -0.0566 1.0000 0.0147
-13.000 -0.9882 0.02990 0.02548 -0.0551 1.0000 0.0147
-12.750 -0.9818 0.02859 0.02405 -0.0536 1.0000 0.0149
-12.500 -0.9751 0.02715 0.02248 -0.0518 1.0000 0.0149
-12.250 -0.9664 0.02617 0.02141 -0.0500 1.0000 0.0150
-12.000 -0.9573 0.02531 0.02045 -0.0479 1.0000 0.0151
-11.750 -0.9515 0.02333 0.01833 -0.0456 1.0000 0.0154
-11.500 -0.9426 0.02232 0.01727 -0.0433 1.0000 0.0156
-11.250 -0.9335 0.02147 0.01638 -0.0408 1.0000 0.0157
-11.000 -0.9253 0.02079 0.01566 -0.0379 1.0000 0.0158
-10.750 -0.9193 0.02027 0.01511 -0.0344 1.0000 0.0160
-10.500 -0.9165 0.01976 0.01456 -0.0301 1.0000 0.0161
-10.250 -0.8831 0.01900 0.01377 -0.0320 0.9954 0.0164
-10.000 -0.8538 0.01820 0.01292 -0.0331 0.9852 0.0167
-9.750 -0.8198 0.01737 0.01205 -0.0351 0.9745 0.0170
-9.500 -0.7769 0.01653 0.01114 -0.0390 0.9634 0.0173
-9.250 -0.7269 0.01560 0.01013 -0.0444 0.9449 0.0176
-9.000 -0.6881 0.01498 0.00936 -0.0472 0.9045 0.0180
-8.750 -0.6702 0.01472 0.00890 -0.0454 0.8600 0.0182
-8.500 -0.6599 0.01415 0.00817 -0.0424 0.8269 0.0185
-8.250 -0.6456 0.01373 0.00764 -0.0400 0.8034 0.0191
-8.000 -0.6276 0.01341 0.00723 -0.0382 0.7856 0.0194
-7.750 -0.6078 0.01315 0.00689 -0.0368 0.7711 0.0199
-7.500 -0.5869 0.01288 0.00657 -0.0356 0.7591 0.0205
-7.250 -0.5650 0.01265 0.00626 -0.0345 0.7489 0.0213
-7.000 -0.5454 0.01228 0.00582 -0.0330 0.7391 0.0221
-6.750 -0.5241 0.01196 0.00548 -0.0319 0.7311 0.0232
-6.500 -0.5011 0.01174 0.00522 -0.0310 0.7232 0.0242
-6.250 -0.4769 0.01157 0.00499 -0.0303 0.7164 0.0255
-6.000 -0.4552 0.01121 0.00462 -0.0292 0.7096 0.0273
-5.750 -0.4311 0.01104 0.00442 -0.0285 0.7030 0.0291
-5.500 -0.4063 0.01085 0.00419 -0.0279 0.6972 0.0305
-5.250 -0.3829 0.01058 0.00392 -0.0271 0.6911 0.0328
-5.000 -0.3579 0.01046 0.00375 -0.0266 0.6849 0.0347
-4.750 -0.3331 0.01023 0.00351 -0.0260 0.6794 0.0369
-4.500 -0.3079 0.01005 0.00333 -0.0255 0.6737 0.0394
-4.250 -0.2822 0.00995 0.00317 -0.0250 0.6681 0.0416
-4.000 -0.2571 0.00973 0.00297 -0.0245 0.6632 0.0459
-3.750 -0.2312 0.00958 0.00282 -0.0241 0.6579 0.0505
-3.500 -0.2059 0.00941 0.00265 -0.0236 0.6526 0.0580
-3.250 -0.1819 0.00913 0.00247 -0.0229 0.6475 0.0822
-3.000 -0.1742 0.00753 0.00187 -0.0197 0.6427 0.3417
-2.750 -0.1554 0.00690 0.00169 -0.0182 0.6373 0.4655
-2.500 -0.1300 0.00680 0.00165 -0.0177 0.6318 0.5023
-2.250 -0.1028 0.00672 0.00163 -0.0175 0.6272 0.5248
-2.000 -0.0752 0.00669 0.00160 -0.0173 0.6221 0.5398
-1.750 -0.0482 0.00668 0.00159 -0.0171 0.6168 0.5516
-1.500 -0.0207 0.00667 0.00158 -0.0170 0.6118 0.5634
-1.250 0.0074 0.00668 0.00157 -0.0170 0.6061 0.5731
-1.000 0.0347 0.00667 0.00155 -0.0168 0.6003 0.5799
-0.750 0.0625 0.00669 0.00156 -0.0167 0.5952 0.5886
-0.500 0.0902 0.00667 0.00155 -0.0167 0.5899 0.5968
-0.250 0.1178 0.00669 0.00155 -0.0166 0.5847 0.6028
0.000 0.1458 0.00672 0.00155 -0.0166 0.5798 0.6071
0.250 0.1740 0.00671 0.00153 -0.0166 0.5736 0.6109
0.750 0.2289 0.00672 0.00152 -0.0164 0.5584 0.6201
1.000 0.2567 0.00675 0.00153 -0.0164 0.5524 0.6245
1.250 0.2843 0.00678 0.00154 -0.0163 0.5469 0.6287
1.500 0.3121 0.00676 0.00156 -0.0163 0.5417 0.6337
1.750 0.3397 0.00679 0.00158 -0.0162 0.5364 0.6389
2.000 0.3671 0.00685 0.00162 -0.0161 0.5310 0.6439
2.250 0.3949 0.00683 0.00165 -0.0161 0.5257 0.6496
2.500 0.4222 0.00685 0.00168 -0.0160 0.5200 0.6556
2.750 0.4494 0.00691 0.00173 -0.0159 0.5140 0.6615
3.000 0.4768 0.00690 0.00177 -0.0158 0.5080 0.6686
3.250 0.5036 0.00694 0.00182 -0.0156 0.5010 0.6766
3.500 0.5306 0.00696 0.00188 -0.0155 0.4944 0.6849
3.750 0.5572 0.00699 0.00194 -0.0152 0.4862 0.6947
4.000 0.5835 0.00702 0.00200 -0.0150 0.4781 0.7057
4.250 0.6093 0.00707 0.00208 -0.0146 0.4676 0.7188
4.500 0.6351 0.00709 0.00215 -0.0142 0.4565 0.7350
4.750 0.6599 0.00713 0.00225 -0.0136 0.4445 0.7543
5.000 0.6838 0.00719 0.00235 -0.0129 0.4281 0.7776
5.250 0.7061 0.00729 0.00248 -0.0118 0.4049 0.8064
5.500 0.7266 0.00743 0.00264 -0.0104 0.3776 0.8415
5.750 0.7468 0.00764 0.00287 -0.0089 0.3502 0.8819
6.000 0.7713 0.00793 0.00315 -0.0085 0.3203 0.9206
6.250 0.8053 0.00838 0.00350 -0.0102 0.2856 0.9468
6.500 0.8427 0.00896 0.00390 -0.0129 0.2471 0.9620
6.750 0.8781 0.00944 0.00424 -0.0150 0.2202 0.9724
7.000 0.9132 0.00985 0.00457 -0.0171 0.2014 0.9788
7.250 0.9447 0.01020 0.00486 -0.0182 0.1877 0.9855
7.500 0.9786 0.01056 0.00517 -0.0200 0.1743 0.9901
7.750 1.0110 0.01094 0.00550 -0.0214 0.1614 0.9946
8.000 1.0461 0.01133 0.00583 -0.0235 0.1482 0.9980
8.250 1.0782 0.01173 0.00617 -0.0250 0.1360 1.0000
8.500 1.0919 0.01203 0.00644 -0.0225 0.1273 1.0000
8.750 1.1057 0.01234 0.00673 -0.0201 0.1190 1.0000
9.000 1.1180 0.01271 0.00705 -0.0174 0.1101 1.0000
9.250 1.1309 0.01307 0.00738 -0.0148 0.1020 1.0000
9.500 1.1431 0.01345 0.00774 -0.0121 0.0940 1.0000
9.750 1.1510 0.01389 0.00813 -0.0087 0.0853 1.0000
10.000 1.1558 0.01435 0.00855 -0.0047 0.0767 1.0000
10.250 1.1635 0.01484 0.00901 -0.0015 0.0686 1.0000
10.500 1.1689 0.01552 0.00963 0.0019 0.0580 1.0000
10.750 1.1750 0.01628 0.01033 0.0048 0.0482 1.0000
11.000 1.1817 0.01711 0.01113 0.0075 0.0407 1.0000
11.250 1.1898 0.01798 0.01198 0.0097 0.0361 1.0000
11.500 1.1997 0.01883 0.01285 0.0115 0.0333 1.0000
11.750 1.2089 0.01980 0.01384 0.0131 0.0310 1.0000
12.000 1.2200 0.02073 0.01481 0.0144 0.0292 1.0000
12.250 1.2293 0.02184 0.01594 0.0157 0.0279 1.0000
12.500 1.2370 0.02314 0.01728 0.0169 0.0266 1.0000
12.750 1.2493 0.02416 0.01835 0.0177 0.0258 1.0000
13.000 1.2602 0.02533 0.01957 0.0185 0.0251 1.0000
13.250 1.2696 0.02665 0.02093 0.0192 0.0242 1.0000
13.500 1.2768 0.02817 0.02250 0.0200 0.0234 1.0000
13.750 1.2799 0.03010 0.02447 0.0208 0.0225 1.0000
14.000 1.2887 0.03158 0.02602 0.0213 0.0222 1.0000
14.250 1.2974 0.03307 0.02757 0.0217 0.0218 1.0000
14.500 1.3055 0.03465 0.02920 0.0221 0.0211 1.0000
14.750 1.3121 0.03639 0.03100 0.0224 0.0205 1.0000
15.000 1.3163 0.03837 0.03303 0.0227 0.0200 1.0000
15.250 1.3171 0.04073 0.03545 0.0230 0.0195 1.0000
15.500 1.3136 0.04361 0.03840 0.0231 0.0189 1.0000
15.750 1.3180 0.04576 0.04063 0.0231 0.0186 1.0000
16.000 1.3207 0.04814 0.04309 0.0230 0.0184 1.0000
16.250 1.3246 0.05045 0.04546 0.0228 0.0179 1.0000
16.500 1.3261 0.05308 0.04817 0.0225 0.0176 1.0000
16.750 1.3277 0.05575 0.05091 0.0221 0.0172 1.0000
17.000 1.3279 0.05861 0.05384 0.0216 0.0169 1.0000
17.250 1.3254 0.06189 0.05719 0.0210 0.0165 1.0000
17.500 1.3194 0.06567 0.06104 0.0201 0.0162 1.0000
17.750 1.3083 0.07015 0.06561 0.0190 0.0159 1.0000
18.000 1.2966 0.07485 0.07040 0.0177 0.0157 1.0000
18.250 1.2970 0.07804 0.07368 0.0167 0.0155 1.0000
18.500 1.2914 0.08206 0.07779 0.0154 0.0153 1.0000
18.750 1.2849 0.08629 0.08212 0.0140 0.0151 1.0000
19.000 1.2778 0.09069 0.08661 0.0125 0.0149 1.0000
19.250 1.2701 0.09526 0.09128 0.0108 0.0146 1.0000
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