LOCKHEED C-141 BL610.61 AIRFOIL (c141d-il) Xfoil prediction polar at RE=50,000 Ncrit=5
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Airfoil: LOCKHEED C-141 BL610.61 AIRFOIL (c141d-il) Reynolds number: 50,000 Max Cl/Cd: 30.92 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-c141d-il-50000-n5.txt Download as CSV file: xf-c141d-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: LOCKHEED C-141 BL610.61 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.5053 0.10057 0.09266 -0.0395 1.0000 0.0605
-9.750 -0.5123 0.09586 0.08803 -0.0413 1.0000 0.0602
-9.500 -0.5220 0.09086 0.08309 -0.0435 1.0000 0.0599
-9.250 -0.5371 0.08533 0.07764 -0.0463 1.0000 0.0592
-9.000 -0.5600 0.08053 0.07290 -0.0471 1.0000 0.0584
-8.750 -0.5843 0.07629 0.06867 -0.0459 1.0000 0.0577
-8.500 -0.6040 0.07212 0.06444 -0.0445 1.0000 0.0574
-8.250 -0.6195 0.06822 0.06042 -0.0426 1.0000 0.0573
-8.000 -0.6305 0.06452 0.05657 -0.0405 1.0000 0.0574
-7.750 -0.6378 0.06092 0.05276 -0.0382 1.0000 0.0577
-7.500 -0.6417 0.05735 0.04894 -0.0359 1.0000 0.0580
-7.250 -0.6423 0.05385 0.04513 -0.0336 1.0000 0.0584
-7.000 -0.6394 0.05052 0.04145 -0.0314 1.0000 0.0591
-6.750 -0.6336 0.04741 0.03794 -0.0292 1.0000 0.0606
-6.500 -0.6260 0.04418 0.03411 -0.0270 1.0000 0.0627
-6.250 -0.6130 0.04191 0.03160 -0.0253 1.0000 0.0649
-6.000 -0.5977 0.04002 0.02952 -0.0238 1.0000 0.0672
-5.750 -0.5814 0.03793 0.02704 -0.0222 1.0000 0.0706
-5.500 -0.5635 0.03584 0.02450 -0.0208 1.0000 0.0745
-5.250 -0.5443 0.03441 0.02300 -0.0197 1.0000 0.0785
-5.000 -0.5235 0.03289 0.02105 -0.0184 1.0000 0.0841
-4.750 -0.5024 0.03148 0.01958 -0.0175 1.0000 0.0891
-4.500 -0.4803 0.03032 0.01823 -0.0165 1.0000 0.0957
-4.250 -0.4576 0.02917 0.01701 -0.0156 1.0000 0.1022
-4.000 -0.4344 0.02827 0.01596 -0.0147 1.0000 0.1101
-3.750 -0.4114 0.02740 0.01511 -0.0139 1.0000 0.1184
-3.500 -0.3879 0.02667 0.01426 -0.0130 1.0000 0.1283
-3.250 -0.3649 0.02599 0.01355 -0.0123 1.0000 0.1402
-3.000 -0.3420 0.02531 0.01289 -0.0116 1.0000 0.1543
-2.750 -0.3203 0.02467 0.01228 -0.0108 1.0000 0.1733
-2.500 -0.2986 0.02395 0.01175 -0.0101 1.0000 0.2027
-2.250 -0.2769 0.02291 0.01123 -0.0097 1.0000 0.2775
-2.000 -0.2634 0.02107 0.01135 -0.0065 1.0000 0.6281
-1.750 -0.2374 0.02103 0.01187 -0.0035 1.0000 0.8526
-1.500 -0.1449 0.02171 0.01224 -0.0151 1.0000 0.9999
-1.250 -0.1359 0.02167 0.01201 -0.0125 1.0000 1.0000
-1.000 -0.1249 0.02169 0.01184 -0.0103 1.0000 1.0000
-0.750 -0.1067 0.02181 0.01177 -0.0094 0.9984 1.0000
-0.500 -0.0723 0.02212 0.01188 -0.0115 0.9922 1.0000
-0.250 -0.0382 0.02245 0.01204 -0.0136 0.9856 1.0000
0.000 -0.0055 0.02277 0.01220 -0.0154 0.9786 1.0000
0.250 0.0300 0.02316 0.01247 -0.0176 0.9724 1.0000
0.500 0.0602 0.02345 0.01267 -0.0188 0.9642 1.0000
0.750 0.0953 0.02385 0.01298 -0.0209 0.9576 1.0000
1.000 0.1254 0.02415 0.01324 -0.0220 0.9488 1.0000
1.250 0.1581 0.02450 0.01356 -0.0236 0.9409 1.0000
1.500 0.1910 0.02485 0.01389 -0.0251 0.9325 1.0000
1.750 0.2206 0.02516 0.01421 -0.0260 0.9230 1.0000
2.000 0.2578 0.02551 0.01459 -0.0283 0.9152 1.0000
2.250 0.2851 0.02578 0.01490 -0.0286 0.9038 1.0000
2.500 0.3181 0.02603 0.01522 -0.0298 0.8930 1.0000
2.750 0.3580 0.02616 0.01545 -0.0321 0.8820 1.0000
3.000 0.3974 0.02608 0.01549 -0.0339 0.8673 1.0000
3.250 0.4305 0.02581 0.01535 -0.0342 0.8468 1.0000
3.500 0.4694 0.02528 0.01497 -0.0350 0.8250 1.0000
3.750 0.5153 0.02426 0.01414 -0.0363 0.8003 1.0000
4.000 0.5480 0.02336 0.01336 -0.0351 0.7680 1.0000
4.250 0.5735 0.02274 0.01286 -0.0329 0.7306 1.0000
4.500 0.6039 0.02215 0.01237 -0.0316 0.6869 1.0000
4.750 0.6343 0.02169 0.01188 -0.0302 0.6220 1.0000
5.000 0.6675 0.02159 0.01126 -0.0291 0.4942 1.0000
5.250 0.6799 0.02272 0.01149 -0.0257 0.3624 1.0000
5.500 0.6886 0.02410 0.01227 -0.0226 0.2846 1.0000
5.750 0.7011 0.02539 0.01317 -0.0203 0.2380 1.0000
6.000 0.7167 0.02659 0.01410 -0.0185 0.2083 1.0000
6.250 0.7357 0.02767 0.01511 -0.0171 0.1862 1.0000
6.500 0.7567 0.02873 0.01612 -0.0161 0.1692 1.0000
6.750 0.7802 0.02980 0.01716 -0.0155 0.1551 1.0000
7.000 0.8058 0.03091 0.01824 -0.0152 0.1432 1.0000
7.250 0.8314 0.03204 0.01938 -0.0149 0.1324 1.0000
7.500 0.8587 0.03327 0.02075 -0.0148 0.1225 1.0000
7.750 0.8848 0.03464 0.02212 -0.0147 0.1143 1.0000
8.000 0.9093 0.03603 0.02366 -0.0143 0.1065 1.0000
8.250 0.9340 0.03770 0.02543 -0.0140 0.1001 1.0000
8.500 0.9556 0.03933 0.02726 -0.0132 0.0939 1.0000
8.750 0.9775 0.04117 0.02915 -0.0126 0.0892 1.0000
9.000 0.9943 0.04327 0.03168 -0.0111 0.0843 1.0000
9.250 1.0113 0.04510 0.03364 -0.0100 0.0803 1.0000
9.500 1.0266 0.04740 0.03612 -0.0087 0.0773 1.0000
9.750 1.0332 0.05013 0.03938 -0.0062 0.0741 1.0000
10.000 1.0408 0.05256 0.04211 -0.0041 0.0713 1.0000
10.250 1.0493 0.05489 0.04461 -0.0022 0.0692 1.0000
10.500 1.0580 0.05734 0.04714 -0.0007 0.0675 1.0000
10.750 1.0458 0.06090 0.05122 0.0031 0.0663 1.0000
11.000 1.0298 0.06438 0.05509 0.0068 0.0653 1.0000
11.250 1.0103 0.06797 0.05899 0.0102 0.0647 1.0000
11.500 0.9880 0.07202 0.06330 0.0126 0.0642 1.0000
11.750 0.9622 0.07678 0.06831 0.0137 0.0641 1.0000
12.000 0.9326 0.08261 0.07434 0.0132 0.0643 1.0000
12.250 0.8998 0.08994 0.08184 0.0105 0.0648 1.0000
12.500 0.8661 0.09915 0.09115 0.0053 0.0655 1.0000
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Polar data table (+)
Polar graphs
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