KC-135 BL351.6 AIRFOIL (kc135d-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: KC-135 BL351.6 AIRFOIL (kc135d-il) Reynolds number: 500,000 Max Cl/Cd: 83.95 at α=3.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-kc135d-il-500000-n5.txt Download as CSV file: xf-kc135d-il-500000-n5.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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.4506 0.08439 0.08213 -0.0293 1.0000 0.0073
-8.500 -0.4514 0.08105 0.07882 -0.0306 1.0000 0.0071
-8.250 -0.4556 0.07727 0.07508 -0.0329 1.0000 0.0069
-8.000 -0.4665 0.07348 0.07132 -0.0355 1.0000 0.0068
-7.750 -0.4715 0.06955 0.06738 -0.0370 1.0000 0.0067
-7.500 -0.4746 0.06596 0.06375 -0.0376 1.0000 0.0065
-7.250 -0.4602 0.06047 0.05815 -0.0426 0.9877 0.0063
-7.000 -0.4409 0.05478 0.05230 -0.0474 0.9763 0.0062
-6.750 -0.4193 0.04942 0.04673 -0.0512 0.9642 0.0062
-6.500 -0.3962 0.04445 0.04152 -0.0539 0.9516 0.0062
-6.250 -0.3742 0.03963 0.03641 -0.0553 0.9372 0.0065
-6.000 -0.3549 0.03518 0.03163 -0.0550 0.9219 0.0068
-5.750 -0.3372 0.03017 0.02617 -0.0533 0.9073 0.0076
-5.500 -0.3175 0.02790 0.02365 -0.0525 0.8952 0.0078
-5.250 -0.2961 0.02637 0.02192 -0.0518 0.8841 0.0081
-5.000 -0.2757 0.02358 0.01878 -0.0503 0.8731 0.0084
-4.750 -0.2540 0.02088 0.01573 -0.0488 0.8634 0.0087
-4.500 -0.2313 0.01781 0.01221 -0.0472 0.8549 0.0096
-4.250 -0.2070 0.01482 0.00875 -0.0457 0.8467 0.0107
-4.000 -0.1820 0.01430 0.00814 -0.0454 0.8388 0.0115
-3.750 -0.1562 0.01408 0.00785 -0.0452 0.8303 0.0125
-3.500 -0.1305 0.01314 0.00673 -0.0446 0.8229 0.0135
-3.250 -0.1050 0.01235 0.00581 -0.0440 0.8154 0.0146
-3.000 -0.0791 0.01187 0.00522 -0.0436 0.8086 0.0153
-2.750 -0.0548 0.01117 0.00447 -0.0430 0.8012 0.0169
-2.500 -0.0292 0.01083 0.00408 -0.0426 0.7943 0.0180
-2.250 -0.0039 0.01043 0.00363 -0.0421 0.7874 0.0190
-2.000 0.0214 0.01007 0.00321 -0.0416 0.7813 0.0199
-1.750 0.0473 0.00983 0.00293 -0.0413 0.7744 0.0213
-1.500 0.0731 0.00959 0.00262 -0.0409 0.7682 0.0222
-1.250 0.0991 0.00934 0.00234 -0.0406 0.7615 0.0227
-1.000 0.1242 0.00899 0.00189 -0.0400 0.7542 0.0249
-0.750 0.1505 0.00882 0.00170 -0.0397 0.7453 0.0270
-0.500 0.1768 0.00872 0.00154 -0.0394 0.7350 0.0300
-0.250 0.2032 0.00866 0.00141 -0.0391 0.7231 0.0331
0.000 0.2293 0.00857 0.00128 -0.0387 0.7104 0.0430
0.250 0.2436 0.00690 0.00115 -0.0369 0.6996 0.5933
0.500 0.2653 0.00655 0.00117 -0.0356 0.6896 0.7030
0.750 0.2884 0.00635 0.00119 -0.0344 0.6809 0.7713
1.000 0.3126 0.00623 0.00121 -0.0335 0.6705 0.8228
1.250 0.3406 0.00608 0.00131 -0.0332 0.6595 0.9103
1.500 0.3802 0.00614 0.00137 -0.0357 0.6461 0.9443
1.750 0.4141 0.00621 0.00140 -0.0371 0.6329 0.9559
2.000 0.4473 0.00630 0.00143 -0.0383 0.6190 0.9658
2.250 0.4815 0.00640 0.00149 -0.0399 0.6013 0.9726
2.500 0.5138 0.00652 0.00155 -0.0410 0.5822 0.9792
2.750 0.5453 0.00668 0.00162 -0.0419 0.5559 0.9856
3.000 0.5775 0.00688 0.00171 -0.0431 0.5204 0.9909
3.250 0.6078 0.00724 0.00186 -0.0440 0.4641 0.9964
3.500 0.6350 0.00779 0.00208 -0.0444 0.3898 1.0000
4.000 0.6731 0.00882 0.00259 -0.0415 0.2742 1.0000
4.250 0.6942 0.00919 0.00284 -0.0404 0.2419 1.0000
4.500 0.7155 0.00955 0.00307 -0.0394 0.2127 1.0000
4.750 0.7372 0.00989 0.00331 -0.0384 0.1872 1.0000
5.000 0.7592 0.01021 0.00356 -0.0374 0.1637 1.0000
5.250 0.7800 0.01064 0.00384 -0.0363 0.1314 1.0000
5.500 0.7979 0.01134 0.00427 -0.0348 0.0788 1.0000
5.750 0.8155 0.01210 0.00479 -0.0332 0.0365 1.0000
6.000 0.8366 0.01256 0.00521 -0.0321 0.0260 1.0000
6.250 0.8585 0.01295 0.00563 -0.0312 0.0215 1.0000
6.500 0.8805 0.01334 0.00607 -0.0303 0.0186 1.0000
6.750 0.9011 0.01389 0.00666 -0.0291 0.0154 1.0000
7.000 0.9225 0.01435 0.00718 -0.0281 0.0141 1.0000
7.250 0.9440 0.01480 0.00769 -0.0272 0.0125 1.0000
7.500 0.9651 0.01528 0.00820 -0.0262 0.0113 1.0000
7.750 0.9838 0.01600 0.00900 -0.0249 0.0102 1.0000
8.000 1.0027 0.01670 0.00979 -0.0235 0.0096 1.0000
8.250 1.0216 0.01736 0.01054 -0.0222 0.0092 1.0000
8.500 1.0398 0.01809 0.01136 -0.0209 0.0088 1.0000
8.750 1.0571 0.01888 0.01225 -0.0194 0.0085 1.0000
9.000 1.0738 0.01970 0.01316 -0.0178 0.0081 1.0000
9.250 1.0902 0.02053 0.01410 -0.0163 0.0078 1.0000
9.500 1.1064 0.02132 0.01496 -0.0148 0.0074 1.0000
9.750 1.1210 0.02224 0.01596 -0.0131 0.0071 1.0000
10.000 1.1306 0.02351 0.01733 -0.0108 0.0067 1.0000
10.250 1.1382 0.02488 0.01884 -0.0080 0.0065 1.0000
10.500 1.1487 0.02592 0.02001 -0.0058 0.0064 1.0000
10.750 1.1580 0.02708 0.02133 -0.0036 0.0062 1.0000
11.000 1.1641 0.02867 0.02308 -0.0011 0.0061 1.0000
11.250 1.1713 0.03005 0.02463 0.0010 0.0060 1.0000
11.500 1.1752 0.03184 0.02663 0.0032 0.0059 1.0000
11.750 1.1788 0.03359 0.02856 0.0052 0.0057 1.0000
12.000 1.1791 0.03575 0.03092 0.0072 0.0056 1.0000
12.250 1.1767 0.03822 0.03361 0.0090 0.0055 1.0000
12.500 1.1738 0.04073 0.03632 0.0104 0.0054 1.0000
12.750 1.1672 0.04381 0.03961 0.0115 0.0053 1.0000
13.000 1.1582 0.04727 0.04328 0.0122 0.0053 1.0000
13.250 1.1496 0.05087 0.04707 0.0122 0.0053 1.0000
13.500 1.1375 0.05514 0.05154 0.0116 0.0052 1.0000
13.750 1.1255 0.05971 0.05629 0.0103 0.0051 1.0000
14.000 1.1098 0.06525 0.06201 0.0082 0.0051 1.0000
14.250 1.0900 0.07204 0.06899 0.0049 0.0051 1.0000
14.500 1.0693 0.07982 0.07697 0.0004 0.0051 1.0000
14.750 1.0422 0.08995 0.08730 -0.0058 0.0053 1.0000
15.000 1.0209 0.09983 0.09732 -0.0120 0.0052 1.0000
15.250 0.9924 0.11208 0.10972 -0.0192 0.0053 1.0000
15.500 0.9549 0.12733 0.12508 -0.0277 0.0054 1.0000
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Polar data table (+)
Polar graphs
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