LOCKHEED C-141 BL761.11 AIRFOIL (c141e-il) Xfoil prediction polar at RE=100,000 Ncrit=9
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Airfoil: LOCKHEED C-141 BL761.11 AIRFOIL (c141e-il) Reynolds number: 100,000 Max Cl/Cd: 49.24 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-c141e-il-100000.txt Download as CSV file: xf-c141e-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: LOCKHEED C-141 BL761.11 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
------ -------- --------- --------- -------- -------- --------
-9.750 -0.4636 0.10657 0.10100 -0.0318 1.0000 0.1170
-9.500 -0.4899 0.10377 0.09832 -0.0356 1.0000 0.1207
-9.250 -0.5320 0.10085 0.09556 -0.0397 1.0000 0.1214
-9.000 -0.5054 0.09587 0.09057 -0.0360 1.0000 0.1237
-8.750 -0.4861 0.09332 0.08800 -0.0328 1.0000 0.1271
-8.500 -0.4908 0.09064 0.08538 -0.0319 1.0000 0.1309
-8.250 -0.5131 0.08777 0.08261 -0.0317 1.0000 0.1337
-8.000 -0.5488 0.08460 0.07952 -0.0322 1.0000 0.1357
-7.500 -0.5758 0.07713 0.07207 -0.0304 1.0000 0.1407
-7.250 -0.5655 0.07505 0.07005 -0.0274 1.0000 0.1454
-7.000 -0.6035 0.07297 0.06756 -0.0285 1.0000 0.1541
-6.500 -0.5806 0.06561 0.06051 -0.0238 1.0000 0.1618
-6.250 -0.5905 0.06222 0.05685 -0.0236 1.0000 0.1731
-6.000 -0.5785 0.05955 0.05428 -0.0213 1.0000 0.1773
-5.750 -0.5771 0.05667 0.05122 -0.0205 1.0000 0.1907
-5.500 -0.5711 0.05451 0.04889 -0.0192 1.0000 0.2062
-5.250 -0.5575 0.05193 0.04648 -0.0169 1.0000 0.2136
-5.000 -0.5277 0.03797 0.03017 -0.0202 1.0000 0.1043
-4.750 -0.5080 0.03492 0.02681 -0.0193 1.0000 0.1015
-4.500 -0.4866 0.03268 0.02418 -0.0184 1.0000 0.1020
-4.250 -0.4634 0.03075 0.02186 -0.0176 1.0000 0.1030
-4.000 -0.4392 0.02898 0.01971 -0.0169 1.0000 0.1037
-3.750 -0.4151 0.02789 0.01821 -0.0160 1.0000 0.1062
-3.500 -0.3910 0.02616 0.01642 -0.0158 1.0000 0.1102
-3.250 -0.3670 0.02516 0.01534 -0.0152 1.0000 0.1140
-3.000 -0.3428 0.02440 0.01439 -0.0145 1.0000 0.1194
-2.750 -0.3183 0.02339 0.01336 -0.0140 1.0000 0.1257
-2.500 -0.2943 0.02274 0.01270 -0.0135 1.0000 0.1332
-2.250 -0.2700 0.02201 0.01201 -0.0131 1.0000 0.1427
-2.000 -0.2461 0.02159 0.01156 -0.0125 1.0000 0.1542
-1.750 -0.2219 0.02095 0.01111 -0.0122 1.0000 0.1690
-1.500 -0.1978 0.02045 0.01078 -0.0119 1.0000 0.1886
-1.250 -0.1731 0.01996 0.01053 -0.0117 1.0000 0.2210
-1.000 -0.1326 0.01739 0.01107 -0.0116 1.0000 0.9971
-0.750 -0.1134 0.01761 0.01101 -0.0106 1.0000 1.0000
-0.500 -0.0940 0.01788 0.01109 -0.0098 1.0000 1.0000
-0.250 -0.0742 0.01820 0.01125 -0.0091 1.0000 1.0000
0.000 -0.0541 0.01855 0.01148 -0.0085 1.0000 1.0000
0.250 -0.0161 0.01914 0.01193 -0.0114 0.9951 1.0000
0.500 0.0250 0.01973 0.01241 -0.0148 0.9876 1.0000
0.750 0.0657 0.02033 0.01292 -0.0181 0.9800 1.0000
1.000 0.1082 0.02096 0.01348 -0.0217 0.9728 1.0000
1.250 0.1432 0.02140 0.01389 -0.0239 0.9631 1.0000
1.500 0.1823 0.02190 0.01436 -0.0267 0.9541 1.0000
1.750 0.2329 0.02229 0.01476 -0.0313 0.9428 1.0000
2.000 0.2834 0.02215 0.01463 -0.0352 0.9228 1.0000
2.250 0.3354 0.02189 0.01442 -0.0392 0.9060 1.0000
2.500 0.3847 0.02177 0.01436 -0.0429 0.8961 1.0000
2.750 0.4257 0.02158 0.01426 -0.0450 0.8839 1.0000
3.000 0.4678 0.02115 0.01393 -0.0469 0.8698 1.0000
3.250 0.5286 0.01980 0.01274 -0.0509 0.8530 1.0000
3.500 0.5877 0.01815 0.01124 -0.0542 0.8354 1.0000
3.750 0.6232 0.01726 0.01047 -0.0538 0.8143 1.0000
4.000 0.6606 0.01629 0.00962 -0.0537 0.7881 1.0000
4.250 0.6927 0.01553 0.00893 -0.0525 0.7504 1.0000
4.500 0.7236 0.01495 0.00828 -0.0511 0.6834 1.0000
4.750 0.7475 0.01518 0.00772 -0.0483 0.5164 1.0000
5.000 0.7488 0.01683 0.00816 -0.0430 0.3498 1.0000
5.250 0.7565 0.01836 0.00899 -0.0394 0.2689 1.0000
5.500 0.7699 0.01966 0.00985 -0.0368 0.2224 1.0000
5.750 0.7870 0.02081 0.01069 -0.0350 0.1921 1.0000
6.000 0.8068 0.02176 0.01157 -0.0335 0.1688 1.0000
6.250 0.8275 0.02278 0.01246 -0.0323 0.1509 1.0000
6.500 0.8494 0.02386 0.01347 -0.0312 0.1361 1.0000
6.750 0.8729 0.02507 0.01462 -0.0304 0.1240 1.0000
7.000 0.8989 0.02656 0.01597 -0.0302 0.1150 1.0000
7.250 0.9229 0.02774 0.01724 -0.0295 0.1070 1.0000
7.500 0.9502 0.02956 0.01905 -0.0294 0.1012 1.0000
7.750 0.9751 0.03117 0.02087 -0.0287 0.0968 1.0000
8.000 0.9991 0.03278 0.02250 -0.0283 0.0926 1.0000
8.250 1.0217 0.03510 0.02500 -0.0276 0.0893 1.0000
8.500 1.0398 0.03718 0.02750 -0.0258 0.0872 1.0000
8.750 1.0561 0.03959 0.03030 -0.0240 0.0856 1.0000
9.000 1.0704 0.04200 0.03304 -0.0220 0.0839 1.0000
9.250 1.0851 0.04421 0.03547 -0.0203 0.0819 1.0000
9.500 1.1027 0.04661 0.03792 -0.0193 0.0800 1.0000
9.750 1.1113 0.04990 0.04153 -0.0171 0.0796 1.0000
10.000 1.1084 0.05355 0.04573 -0.0133 0.0802 1.0000
10.250 1.0768 0.05952 0.05256 -0.0068 0.0832 1.0000
10.500 1.0548 0.06463 0.05809 -0.0025 0.0853 1.0000
10.750 1.0329 0.06907 0.06278 0.0013 0.0869 1.0000
11.000 1.0136 0.07341 0.06729 0.0041 0.0882 1.0000
11.250 1.0016 0.07799 0.07196 0.0056 0.0893 1.0000
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Polar data table (+)
Polar graphs
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