KC-135 BL200.76 AIRFOIL (kc135c-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: KC-135 BL200.76 AIRFOIL (kc135c-il) Reynolds number: 50,000 Max Cl/Cd: 34.12 at α=6.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-kc135c-il-50000.txt Download as CSV file: xf-kc135c-il-50000.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 = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.4767 0.11211 0.10517 -0.0131 1.0000 0.2548
-9.500 -0.4615 0.10846 0.10151 -0.0111 1.0000 0.2813
-9.250 -0.4755 0.10679 0.09996 -0.0113 1.0000 0.2993
-9.000 -0.4679 0.10398 0.09720 -0.0093 1.0000 0.3283
-8.750 -0.4380 0.10005 0.09323 -0.0059 1.0000 0.3692
-8.500 -0.4184 0.09687 0.09005 -0.0032 1.0000 0.4103
-8.250 -0.4035 0.09422 0.08743 -0.0004 1.0000 0.4553
-8.000 -0.3905 0.09191 0.08512 0.0024 1.0000 0.5002
-7.750 -0.3568 0.08794 0.08113 0.0043 1.0000 0.5547
-7.500 -0.3448 0.08581 0.07903 0.0068 1.0000 0.6015
-7.250 -0.3188 0.08195 0.07517 0.0074 1.0000 0.6445
-7.000 -0.3004 0.07802 0.07125 0.0069 1.0000 0.6648
-6.500 -0.2914 0.07227 0.06562 0.0069 1.0000 0.6698
-6.000 -0.3689 0.06779 0.06160 0.0068 1.0000 0.5562
-5.750 -0.4319 0.06451 0.05869 0.0070 1.0000 0.4932
-5.500 -0.4841 0.06131 0.05578 0.0080 1.0000 0.4632
-5.250 -0.5311 0.05714 0.05175 0.0069 1.0000 0.4330
-5.000 -0.5645 0.05032 0.04455 -0.0010 1.0000 0.3731
-4.750 -0.5461 0.04443 0.03726 -0.0094 1.0000 0.2696
-4.500 -0.5186 0.04157 0.03342 -0.0099 1.0000 0.2109
-4.250 -0.4955 0.03947 0.03062 -0.0085 1.0000 0.1821
-4.000 -0.4742 0.03747 0.02813 -0.0070 1.0000 0.1669
-3.750 -0.4520 0.03595 0.02600 -0.0052 1.0000 0.1533
-3.500 -0.4292 0.03395 0.02364 -0.0038 1.0000 0.1427
-3.250 -0.4063 0.03254 0.02188 -0.0024 1.0000 0.1360
-3.000 -0.3826 0.03105 0.02011 -0.0011 1.0000 0.1309
-2.750 -0.3591 0.02984 0.01863 0.0001 1.0000 0.1298
-2.500 -0.3353 0.02868 0.01735 0.0011 1.0000 0.1330
-2.250 -0.3108 0.02771 0.01625 0.0023 1.0000 0.1344
-2.000 -0.2869 0.02692 0.01535 0.0036 1.0000 0.1360
-1.750 -0.2642 0.02623 0.01454 0.0047 1.0000 0.1408
-1.500 -0.2460 0.02545 0.01376 0.0061 1.0000 0.1511
-1.250 -0.2282 0.02476 0.01299 0.0076 1.0000 0.1619
-1.000 -0.1008 0.02221 0.01357 -0.0041 1.0000 1.0000
-0.750 -0.1023 0.02208 0.01315 -0.0005 1.0000 1.0000
-0.500 -0.0986 0.02206 0.01284 0.0023 1.0000 1.0000
-0.250 -0.0910 0.02215 0.01261 0.0045 1.0000 1.0000
0.000 -0.0804 0.02233 0.01254 0.0063 1.0000 1.0000
0.250 -0.0677 0.02258 0.01256 0.0077 1.0000 1.0000
0.500 -0.0537 0.02289 0.01266 0.0088 1.0000 1.0000
0.750 -0.0387 0.02325 0.01284 0.0098 1.0000 1.0000
1.000 -0.0231 0.02366 0.01307 0.0107 1.0000 1.0000
1.250 -0.0070 0.02411 0.01338 0.0114 1.0000 1.0000
1.500 0.0093 0.02461 0.01376 0.0120 1.0000 1.0000
1.750 0.0258 0.02515 0.01420 0.0126 1.0000 1.0000
2.000 0.0424 0.02573 0.01470 0.0131 1.0000 1.0000
2.250 0.0763 0.02682 0.01571 0.0100 0.9928 1.0000
2.500 0.1223 0.02818 0.01705 0.0047 0.9780 1.0000
2.750 0.1680 0.02950 0.01838 -0.0003 0.9616 1.0000
3.000 0.2166 0.03082 0.01974 -0.0057 0.9435 1.0000
3.250 0.2618 0.03190 0.02089 -0.0100 0.9221 1.0000
3.500 0.3213 0.03298 0.02211 -0.0162 0.8973 1.0000
3.750 0.3612 0.03363 0.02288 -0.0188 0.8725 1.0000
4.000 0.4065 0.03427 0.02370 -0.0219 0.8488 1.0000
4.250 0.4629 0.03465 0.02435 -0.0263 0.8250 1.0000
4.500 0.5008 0.03495 0.02487 -0.0275 0.7992 1.0000
4.750 0.5496 0.03483 0.02504 -0.0297 0.7718 1.0000
5.000 0.6098 0.03396 0.02460 -0.0326 0.7426 1.0000
5.250 0.6692 0.03233 0.02337 -0.0338 0.7118 1.0000
5.500 0.7226 0.03028 0.02173 -0.0332 0.6774 1.0000
5.750 0.7668 0.02824 0.01997 -0.0312 0.6372 1.0000
6.000 0.7998 0.02675 0.01865 -0.0281 0.5907 1.0000
6.250 0.8269 0.02575 0.01766 -0.0248 0.5399 1.0000
6.500 0.8465 0.02498 0.01664 -0.0207 0.4813 1.0000
6.750 0.8567 0.02511 0.01635 -0.0162 0.4177 1.0000
7.000 0.8652 0.02614 0.01699 -0.0124 0.3559 1.0000
7.250 0.8694 0.02790 0.01827 -0.0083 0.2847 1.0000
7.500 0.8745 0.03053 0.02021 -0.0045 0.2091 1.0000
7.750 0.8931 0.03300 0.02238 -0.0027 0.1668 1.0000
8.000 0.9149 0.03522 0.02460 -0.0014 0.1437 1.0000
8.250 0.9398 0.03780 0.02728 -0.0007 0.1293 1.0000
8.500 0.9616 0.04061 0.03026 0.0003 0.1196 1.0000
8.750 0.9830 0.04332 0.03302 0.0011 0.1107 1.0000
9.000 0.9953 0.04695 0.03721 0.0031 0.1080 1.0000
9.250 1.0020 0.05065 0.04146 0.0055 0.1064 1.0000
9.500 1.0030 0.05439 0.04568 0.0080 0.1047 1.0000
9.750 1.0004 0.05808 0.04976 0.0105 0.1032 1.0000
10.000 0.9934 0.06191 0.05393 0.0130 0.1022 1.0000
10.250 0.9790 0.06600 0.05834 0.0155 0.1026 1.0000
10.500 0.9574 0.07008 0.06266 0.0181 0.1035 1.0000
10.750 0.9311 0.07444 0.06718 0.0200 0.1054 1.0000
11.000 0.9070 0.07928 0.07214 0.0202 0.1070 1.0000
11.250 0.8865 0.08475 0.07767 0.0192 0.1084 1.0000
11.500 0.8734 0.09045 0.08341 0.0178 0.1095 1.0000
11.750 0.7707 0.11207 0.10485 -0.0007 0.1306 1.0000
12.000 0.7711 0.11834 0.11110 -0.0024 0.1354 1.0000
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Polar data table (+)
Polar graphs
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