LOCKHEED C-141 BL610.61 AIRFOIL (c141d-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: LOCKHEED C-141 BL610.61 AIRFOIL (c141d-il) Reynolds number: 100,000 Max Cl/Cd: 44.52 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-c141d-il-100000-n5.txt Download as CSV file: xf-c141d-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.5246 0.09258 0.08695 -0.0419 1.0000 0.0333
-10.000 -0.5370 0.08663 0.08107 -0.0446 1.0000 0.0333
-9.750 -0.5554 0.07959 0.07410 -0.0486 1.0000 0.0330
-9.500 -0.5881 0.07175 0.06627 -0.0526 1.0000 0.0323
-9.250 -0.6283 0.06661 0.06108 -0.0504 1.0000 0.0317
-9.000 -0.6588 0.06171 0.05605 -0.0475 1.0000 0.0315
-8.750 -0.6786 0.05773 0.05189 -0.0443 1.0000 0.0316
-8.500 -0.6918 0.05411 0.04806 -0.0411 1.0000 0.0320
-8.250 -0.7010 0.05046 0.04415 -0.0380 1.0000 0.0324
-8.000 -0.7071 0.04666 0.03999 -0.0348 1.0000 0.0330
-7.750 -0.7097 0.04275 0.03562 -0.0317 1.0000 0.0336
-7.500 -0.7077 0.03895 0.03128 -0.0288 1.0000 0.0341
-7.250 -0.7011 0.03533 0.02700 -0.0261 1.0000 0.0349
-7.000 -0.6872 0.03356 0.02504 -0.0244 1.0000 0.0356
-6.750 -0.6713 0.03217 0.02349 -0.0228 1.0000 0.0366
-6.500 -0.6545 0.03080 0.02188 -0.0213 1.0000 0.0383
-6.250 -0.6363 0.02891 0.01951 -0.0198 1.0000 0.0408
-6.000 -0.6175 0.02811 0.01871 -0.0187 1.0000 0.0426
-5.500 -0.5615 0.02564 0.01581 -0.0194 0.9961 0.0484
-5.250 -0.5307 0.02495 0.01504 -0.0205 0.9936 0.0526
-5.000 -0.5010 0.02412 0.01412 -0.0212 0.9907 0.0570
-4.750 -0.4700 0.02348 0.01332 -0.0221 0.9877 0.0627
-4.500 -0.4384 0.02287 0.01275 -0.0233 0.9850 0.0683
-4.250 -0.4082 0.02224 0.01201 -0.0240 0.9820 0.0747
-4.000 -0.3789 0.02166 0.01145 -0.0247 0.9783 0.0812
-3.750 -0.3479 0.02106 0.01085 -0.0256 0.9752 0.0885
-3.500 -0.3151 0.02059 0.01034 -0.0269 0.9725 0.0974
-3.250 -0.2880 0.02007 0.00989 -0.0271 0.9680 0.1065
-3.000 -0.2583 0.01964 0.00951 -0.0278 0.9640 0.1187
-2.750 -0.2256 0.01925 0.00917 -0.0291 0.9607 0.1366
-2.500 -0.1951 0.01881 0.00887 -0.0300 0.9570 0.1658
-2.250 -0.1688 0.01817 0.00862 -0.0302 0.9519 0.2380
-2.000 -0.1428 0.01679 0.00853 -0.0305 0.9487 0.5130
-1.750 -0.1157 0.01629 0.00880 -0.0295 0.9457 0.7170
-1.500 -0.0900 0.01626 0.00900 -0.0280 0.9409 0.8057
-1.250 -0.0570 0.01641 0.00921 -0.0282 0.9367 0.8713
-1.000 -0.0094 0.01671 0.00950 -0.0313 0.9351 0.9337
-0.750 0.0727 0.01716 0.00986 -0.0419 0.9394 0.9858
-0.500 0.1320 0.01723 0.00983 -0.0487 0.9385 1.0000
-0.250 0.1629 0.01717 0.00970 -0.0498 0.9327 1.0000
0.000 0.1891 0.01713 0.00962 -0.0500 0.9255 1.0000
0.250 0.2174 0.01710 0.00954 -0.0505 0.9185 1.0000
0.500 0.2552 0.01704 0.00946 -0.0527 0.9147 1.0000
0.750 0.2731 0.01706 0.00945 -0.0510 0.9042 1.0000
1.000 0.3104 0.01699 0.00938 -0.0530 0.8998 1.0000
1.250 0.3306 0.01701 0.00941 -0.0517 0.8897 1.0000
1.750 0.3930 0.01673 0.00918 -0.0527 0.8727 1.0000
2.000 0.4300 0.01619 0.00867 -0.0536 0.8575 1.0000
2.250 0.4675 0.01553 0.00803 -0.0543 0.8383 1.0000
2.500 0.4979 0.01505 0.00756 -0.0538 0.8149 1.0000
2.750 0.5257 0.01469 0.00719 -0.0528 0.7872 1.0000
3.000 0.5501 0.01452 0.00701 -0.0515 0.7592 1.0000
3.250 0.5782 0.01434 0.00682 -0.0509 0.7267 1.0000
3.500 0.6071 0.01423 0.00661 -0.0503 0.6819 1.0000
3.750 0.6345 0.01429 0.00643 -0.0495 0.6147 1.0000
4.000 0.6549 0.01471 0.00638 -0.0474 0.5167 1.0000
4.250 0.6659 0.01558 0.00659 -0.0440 0.3994 1.0000
4.500 0.6758 0.01658 0.00701 -0.0407 0.3039 1.0000
4.750 0.6890 0.01745 0.00749 -0.0382 0.2388 1.0000
5.000 0.7043 0.01821 0.00801 -0.0361 0.1966 1.0000
5.250 0.7212 0.01889 0.00852 -0.0342 0.1688 1.0000
5.500 0.7386 0.01955 0.00906 -0.0324 0.1500 1.0000
5.750 0.7566 0.02018 0.00963 -0.0307 0.1361 1.0000
6.000 0.7748 0.02083 0.01025 -0.0290 0.1255 1.0000
6.250 0.7924 0.02155 0.01088 -0.0273 0.1166 1.0000
6.500 0.8118 0.02218 0.01156 -0.0259 0.1084 1.0000
6.750 0.8299 0.02296 0.01229 -0.0243 0.1016 1.0000
7.000 0.8496 0.02365 0.01304 -0.0230 0.0948 1.0000
7.250 0.8681 0.02451 0.01385 -0.0216 0.0892 1.0000
7.500 0.8885 0.02528 0.01471 -0.0204 0.0834 1.0000
7.750 0.9071 0.02618 0.01556 -0.0192 0.0786 1.0000
8.000 0.9281 0.02705 0.01658 -0.0181 0.0735 1.0000
8.250 0.9471 0.02791 0.01745 -0.0169 0.0692 1.0000
8.500 0.9673 0.02897 0.01860 -0.0159 0.0652 1.0000
8.750 0.9866 0.02992 0.01966 -0.0147 0.0612 1.0000
9.000 1.0047 0.03094 0.02061 -0.0136 0.0583 1.0000
9.250 1.0246 0.03218 0.02213 -0.0124 0.0548 1.0000
9.500 1.0417 0.03319 0.02324 -0.0111 0.0520 1.0000
9.750 1.0588 0.03439 0.02444 -0.0099 0.0499 1.0000
10.000 1.0762 0.03606 0.02644 -0.0085 0.0475 1.0000
10.250 1.0910 0.03741 0.02794 -0.0070 0.0454 1.0000
10.500 1.1046 0.03851 0.02908 -0.0054 0.0439 1.0000
10.750 1.1158 0.04031 0.03113 -0.0035 0.0423 1.0000
11.000 1.1237 0.04239 0.03355 -0.0011 0.0408 1.0000
11.250 1.1298 0.04440 0.03580 0.0013 0.0397 1.0000
11.500 1.1343 0.04632 0.03793 0.0037 0.0388 1.0000
11.750 1.1383 0.04810 0.03984 0.0060 0.0381 1.0000
12.000 1.1425 0.04985 0.04167 0.0080 0.0375 1.0000
12.250 1.1342 0.05284 0.04500 0.0109 0.0369 1.0000
12.500 1.1186 0.05647 0.04904 0.0137 0.0363 1.0000
12.750 1.1002 0.06045 0.05336 0.0158 0.0359 1.0000
13.000 1.0788 0.06497 0.05819 0.0169 0.0356 1.0000
13.250 1.0536 0.07034 0.06386 0.0168 0.0355 1.0000
13.500 1.0233 0.07708 0.07088 0.0149 0.0355 1.0000
13.750 0.9864 0.08603 0.08008 0.0104 0.0358 1.0000
14.000 0.9423 0.09853 0.09279 0.0023 0.0365 1.0000
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Polar data table (+)
Polar graphs
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