LOCKHEED C-141 BL426.57 AIRFOIL (c141c-il) Xfoil prediction polar at RE=50,000 Ncrit=9
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Airfoil: LOCKHEED C-141 BL426.57 AIRFOIL (c141c-il) Reynolds number: 50,000 Max Cl/Cd: 31.22 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-c141c-il-50000.txt Download as CSV file: xf-c141c-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: LOCKHEED C-141 BL426.57 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
------ -------- --------- --------- -------- -------- --------
-9.500 -0.4654 0.10977 0.10216 -0.0158 1.0000 0.3162
-9.250 -0.4622 0.10676 0.09918 -0.0149 1.0000 0.3317
-9.000 -0.4593 0.10377 0.09623 -0.0139 1.0000 0.3473
-8.750 -0.4568 0.10080 0.09331 -0.0128 1.0000 0.3627
-8.500 -0.4540 0.09783 0.09038 -0.0116 1.0000 0.3784
-8.250 -0.4480 0.09486 0.08744 -0.0100 1.0000 0.3964
-8.000 -0.4552 0.09296 0.08563 -0.0077 1.0000 0.4189
-7.750 -0.4451 0.08963 0.08233 -0.0058 1.0000 0.4395
-7.500 -0.4368 0.08653 0.07925 -0.0041 1.0000 0.4575
-7.250 -0.4385 0.08382 0.07659 -0.0021 1.0000 0.4721
-7.000 -0.6565 0.06133 0.05367 -0.0265 1.0000 0.1677
-6.750 -0.6662 0.05597 0.04760 -0.0246 1.0000 0.1547
-6.500 -0.6561 0.05219 0.04362 -0.0229 1.0000 0.1529
-6.250 -0.6460 0.04851 0.03968 -0.0212 1.0000 0.1506
-6.000 -0.6351 0.04506 0.03582 -0.0194 1.0000 0.1493
-5.750 -0.6222 0.04211 0.03236 -0.0176 1.0000 0.1512
-5.500 -0.6068 0.03942 0.02905 -0.0158 1.0000 0.1535
-5.250 -0.5876 0.03670 0.02598 -0.0146 1.0000 0.1561
-5.000 -0.5671 0.03473 0.02392 -0.0135 1.0000 0.1634
-4.750 -0.5453 0.03278 0.02144 -0.0122 1.0000 0.1705
-4.500 -0.5219 0.03096 0.01959 -0.0114 1.0000 0.1798
-4.250 -0.4982 0.02938 0.01788 -0.0105 1.0000 0.1929
-4.000 -0.4729 0.02791 0.01632 -0.0098 1.0000 0.2086
-3.750 -0.4469 0.02664 0.01495 -0.0090 1.0000 0.2320
-3.500 -0.4201 0.02524 0.01382 -0.0085 1.0000 0.2660
-3.250 -0.3948 0.02361 0.01268 -0.0079 1.0000 0.3289
-3.000 -0.1396 0.02415 0.01486 -0.0355 1.0000 1.0000
-2.750 -0.1408 0.02368 0.01426 -0.0322 1.0000 1.0000
-2.500 -0.1415 0.02327 0.01373 -0.0287 1.0000 1.0000
-2.250 -0.1417 0.02292 0.01326 -0.0252 1.0000 1.0000
-2.000 -0.1412 0.02262 0.01283 -0.0216 1.0000 1.0000
-1.750 -0.1397 0.02237 0.01246 -0.0181 1.0000 1.0000
-1.500 -0.1365 0.02218 0.01215 -0.0148 1.0000 1.0000
-1.250 -0.1313 0.02206 0.01190 -0.0117 1.0000 1.0000
-1.000 -0.1241 0.02200 0.01170 -0.0090 1.0000 1.0000
-0.750 -0.1150 0.02200 0.01158 -0.0065 1.0000 1.0000
-0.500 -0.1041 0.02206 0.01150 -0.0043 1.0000 1.0000
-0.250 -0.0914 0.02219 0.01151 -0.0025 1.0000 1.0000
0.000 -0.0772 0.02237 0.01158 -0.0009 1.0000 1.0000
0.250 -0.0619 0.02259 0.01171 0.0005 1.0000 1.0000
0.500 -0.0457 0.02287 0.01189 0.0017 1.0000 1.0000
0.750 -0.0289 0.02319 0.01214 0.0027 1.0000 1.0000
1.000 -0.0116 0.02355 0.01244 0.0036 1.0000 1.0000
1.250 0.0060 0.02396 0.01280 0.0044 1.0000 1.0000
1.500 0.0238 0.02442 0.01322 0.0051 1.0000 1.0000
1.750 0.0417 0.02492 0.01370 0.0057 1.0000 1.0000
2.000 0.0597 0.02546 0.01424 0.0062 1.0000 1.0000
2.250 0.0776 0.02606 0.01484 0.0067 1.0000 1.0000
2.500 0.0954 0.02670 0.01550 0.0070 1.0000 1.0000
2.750 0.1131 0.02740 0.01623 0.0073 1.0000 1.0000
3.000 0.1306 0.02816 0.01703 0.0076 1.0000 1.0000
3.250 0.1477 0.02899 0.01791 0.0077 1.0000 1.0000
3.500 0.1646 0.02988 0.01887 0.0078 1.0000 1.0000
3.750 0.2018 0.03131 0.02043 0.0039 0.9909 1.0000
4.000 0.2729 0.03326 0.02262 -0.0060 0.9611 1.0000
4.250 0.3495 0.03461 0.02428 -0.0156 0.9261 1.0000
4.500 0.4102 0.03492 0.02489 -0.0212 0.8884 1.0000
4.750 0.4875 0.03423 0.02463 -0.0276 0.8487 1.0000
5.000 0.5721 0.03172 0.02266 -0.0326 0.8052 1.0000
5.250 0.6413 0.02793 0.01946 -0.0329 0.7530 1.0000
5.500 0.7087 0.02270 0.01449 -0.0290 0.6192 1.0000
5.750 0.7241 0.02416 0.01381 -0.0226 0.3735 1.0000
6.000 0.7438 0.02649 0.01534 -0.0208 0.2918 1.0000
6.250 0.7755 0.02856 0.01704 -0.0211 0.2435 1.0000
6.750 0.8375 0.03269 0.02090 -0.0216 0.1913 1.0000
7.000 0.8644 0.03488 0.02318 -0.0211 0.1763 1.0000
7.250 0.8866 0.03713 0.02569 -0.0199 0.1648 1.0000
7.500 0.9094 0.03979 0.02852 -0.0190 0.1566 1.0000
7.750 0.9261 0.04214 0.03125 -0.0171 0.1488 1.0000
8.000 0.9472 0.04535 0.03449 -0.0162 0.1437 1.0000
8.250 0.9545 0.04829 0.03807 -0.0131 0.1411 1.0000
8.500 0.9599 0.05142 0.04170 -0.0101 0.1381 1.0000
8.750 0.9641 0.05478 0.04546 -0.0073 0.1360 1.0000
9.000 0.9628 0.05875 0.04986 -0.0042 0.1365 1.0000
9.250 0.9561 0.06305 0.05456 -0.0012 0.1381 1.0000
9.500 0.9474 0.06748 0.05929 0.0016 0.1399 1.0000
9.750 0.9383 0.07201 0.06405 0.0038 0.1415 1.0000
10.000 0.9317 0.07672 0.06892 0.0055 0.1430 1.0000
10.250 0.9334 0.08182 0.07413 0.0064 0.1443 1.0000
10.500 0.8482 0.08901 0.08157 0.0081 0.1574 1.0000
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Polar data table (+)
Polar graphs
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