LOCKHEED L-188 TIP AIRFOIL (l188tip-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: LOCKHEED L-188 TIP AIRFOIL (l188tip-il) Reynolds number: 200,000 Max Cl/Cd: 72.86 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-l188tip-il-200000-n5.txt Download as CSV file: xf-l188tip-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: LOCKHEED L-188 TIP AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.4879 0.08859 0.08485 -0.0510 1.0000 0.0227
-10.250 -0.5143 0.08232 0.07865 -0.0523 0.9995 0.0227
-10.000 -0.6276 0.04774 0.04341 -0.0824 0.9825 0.0217
-9.750 -0.6418 0.04053 0.03559 -0.0842 0.9746 0.0220
-9.500 -0.6345 0.03523 0.02960 -0.0859 0.9713 0.0226
-9.250 -0.6276 0.03190 0.02573 -0.0847 0.9651 0.0232
-9.000 -0.6094 0.02907 0.02235 -0.0849 0.9616 0.0239
-8.750 -0.5825 0.02802 0.02125 -0.0859 0.9594 0.0246
-8.500 -0.5542 0.02705 0.02016 -0.0870 0.9577 0.0256
-8.250 -0.5349 0.02595 0.01884 -0.0861 0.9530 0.0266
-8.000 -0.5119 0.02457 0.01718 -0.0859 0.9492 0.0276
-7.750 -0.4857 0.02323 0.01556 -0.0861 0.9465 0.0286
-7.500 -0.4573 0.02228 0.01459 -0.0869 0.9443 0.0295
-7.250 -0.4276 0.02155 0.01377 -0.0877 0.9424 0.0308
-7.000 -0.4069 0.02093 0.01302 -0.0866 0.9375 0.0324
-6.750 -0.3818 0.02016 0.01210 -0.0863 0.9336 0.0340
-6.500 -0.3546 0.01944 0.01138 -0.0866 0.9307 0.0354
-6.250 -0.3257 0.01881 0.01069 -0.0871 0.9283 0.0372
-6.000 -0.2958 0.01822 0.00998 -0.0877 0.9263 0.0397
-5.750 -0.2765 0.01776 0.00953 -0.0862 0.9203 0.0418
-5.500 -0.2502 0.01730 0.00905 -0.0861 0.9165 0.0446
-5.250 -0.2222 0.01682 0.00849 -0.0862 0.9136 0.0476
-5.000 -0.1935 0.01632 0.00800 -0.0866 0.9112 0.0516
-4.750 -0.1701 0.01601 0.00764 -0.0858 0.9062 0.0557
-4.500 -0.1455 0.01561 0.00727 -0.0853 0.9016 0.0605
-4.250 -0.1178 0.01526 0.00688 -0.0854 0.8982 0.0669
-4.000 -0.0892 0.01486 0.00650 -0.0856 0.8955 0.0749
-3.750 -0.0646 0.01457 0.00624 -0.0851 0.8908 0.0845
-3.500 -0.0397 0.01429 0.00600 -0.0846 0.8857 0.0970
-3.250 -0.0122 0.01396 0.00571 -0.0846 0.8820 0.1151
-3.000 0.0163 0.01359 0.00543 -0.0848 0.8792 0.1418
-2.750 0.0401 0.01330 0.00529 -0.0841 0.8737 0.1790
-2.500 0.0648 0.01287 0.00510 -0.0838 0.8686 0.2418
-2.250 0.0899 0.01218 0.00487 -0.0836 0.8649 0.3600
-2.000 0.1132 0.01151 0.00481 -0.0828 0.8612 0.5246
-1.750 0.1352 0.01133 0.00489 -0.0815 0.8547 0.6042
-1.500 0.1615 0.01118 0.00486 -0.0809 0.8504 0.6555
-1.250 0.1897 0.01104 0.00478 -0.0806 0.8471 0.6932
-1.000 0.2134 0.01103 0.00483 -0.0796 0.8406 0.7219
-0.750 0.2398 0.01096 0.00480 -0.0790 0.8355 0.7489
-0.500 0.2669 0.01082 0.00472 -0.0784 0.8318 0.7817
-0.250 0.2892 0.01075 0.00479 -0.0769 0.8252 0.8188
0.000 0.3147 0.01064 0.00476 -0.0759 0.8198 0.8477
0.250 0.3445 0.01053 0.00466 -0.0760 0.8160 0.8640
0.500 0.3720 0.01055 0.00471 -0.0759 0.8091 0.8811
0.750 0.4041 0.01051 0.00468 -0.0765 0.8039 0.8994
1.000 0.4403 0.01044 0.00460 -0.0781 0.8001 0.9184
1.250 0.4749 0.01049 0.00469 -0.0796 0.7930 0.9404
1.500 0.5132 0.01046 0.00466 -0.0818 0.7878 0.9601
1.750 0.5511 0.01045 0.00464 -0.0839 0.7823 0.9792
2.000 0.5888 0.01043 0.00462 -0.0861 0.7733 0.9955
2.250 0.6182 0.01030 0.00440 -0.0862 0.7562 1.0000
2.500 0.6419 0.01023 0.00423 -0.0850 0.7353 1.0000
2.750 0.6659 0.01026 0.00419 -0.0841 0.7180 1.0000
3.000 0.6902 0.01033 0.00421 -0.0833 0.7019 1.0000
3.250 0.7144 0.01042 0.00424 -0.0824 0.6846 1.0000
3.500 0.7384 0.01054 0.00430 -0.0816 0.6658 1.0000
4.000 0.7853 0.01085 0.00447 -0.0796 0.6200 1.0000
4.250 0.8073 0.01108 0.00459 -0.0783 0.5901 1.0000
4.500 0.8278 0.01139 0.00473 -0.0768 0.5518 1.0000
4.750 0.8453 0.01183 0.00494 -0.0747 0.5001 1.0000
5.000 0.8578 0.01252 0.00525 -0.0719 0.4269 1.0000
5.250 0.8673 0.01342 0.00573 -0.0686 0.3520 1.0000
5.500 0.8793 0.01427 0.00625 -0.0660 0.2933 1.0000
5.750 0.8932 0.01505 0.00678 -0.0638 0.2466 1.0000
6.000 0.9090 0.01573 0.00727 -0.0619 0.2109 1.0000
6.250 0.9255 0.01638 0.00777 -0.0601 0.1825 1.0000
6.500 0.9424 0.01699 0.00827 -0.0584 0.1598 1.0000
6.750 0.9588 0.01759 0.00879 -0.0567 0.1419 1.0000
7.000 0.9752 0.01817 0.00930 -0.0549 0.1271 1.0000
7.250 0.9917 0.01876 0.00984 -0.0531 0.1146 1.0000
7.500 1.0088 0.01933 0.01040 -0.0515 0.1040 1.0000
7.750 1.0256 0.01995 0.01101 -0.0500 0.0953 1.0000
8.000 1.0413 0.02064 0.01166 -0.0483 0.0876 1.0000
8.250 1.0588 0.02124 0.01231 -0.0468 0.0810 1.0000
8.500 1.0739 0.02200 0.01304 -0.0451 0.0754 1.0000
8.750 1.0910 0.02265 0.01376 -0.0437 0.0704 1.0000
9.000 1.1060 0.02344 0.01454 -0.0421 0.0659 1.0000
9.250 1.1216 0.02421 0.01536 -0.0406 0.0621 1.0000
9.500 1.1371 0.02499 0.01620 -0.0391 0.0585 1.0000
9.750 1.1502 0.02594 0.01714 -0.0374 0.0554 1.0000
10.000 1.1652 0.02678 0.01807 -0.0360 0.0526 1.0000
10.250 1.1797 0.02767 0.01903 -0.0345 0.0500 1.0000
10.500 1.1925 0.02868 0.02006 -0.0329 0.0478 1.0000
10.750 1.2045 0.02979 0.02122 -0.0313 0.0458 1.0000
11.000 1.2181 0.03078 0.02233 -0.0299 0.0437 1.0000
11.250 1.2308 0.03185 0.02347 -0.0284 0.0419 1.0000
11.500 1.2419 0.03304 0.02471 -0.0270 0.0404 1.0000
11.750 1.2509 0.03445 0.02615 -0.0253 0.0390 1.0000
12.000 1.2629 0.03565 0.02750 -0.0239 0.0376 1.0000
12.250 1.2737 0.03695 0.02891 -0.0226 0.0362 1.0000
12.500 1.2835 0.03831 0.03035 -0.0212 0.0349 1.0000
12.750 1.2920 0.03979 0.03190 -0.0199 0.0339 1.0000
13.000 1.2984 0.04151 0.03366 -0.0185 0.0330 1.0000
13.250 1.3065 0.04318 0.03548 -0.0172 0.0322 1.0000
13.500 1.3139 0.04490 0.03737 -0.0160 0.0312 1.0000
13.750 1.3202 0.04673 0.03933 -0.0149 0.0303 1.0000
14.000 1.3256 0.04864 0.04137 -0.0138 0.0294 1.0000
14.250 1.3299 0.05067 0.04349 -0.0129 0.0287 1.0000
14.500 1.3328 0.05287 0.04577 -0.0121 0.0281 1.0000
14.750 1.3343 0.05529 0.04827 -0.0113 0.0275 1.0000
15.000 1.3356 0.05790 0.05107 -0.0106 0.0270 1.0000
15.250 1.3355 0.06074 0.05411 -0.0100 0.0265 1.0000
15.500 1.3339 0.06380 0.05737 -0.0097 0.0260 1.0000
15.750 1.3312 0.06709 0.06084 -0.0096 0.0255 1.0000
16.000 1.3274 0.07061 0.06453 -0.0099 0.0250 1.0000
16.250 1.3229 0.07433 0.06841 -0.0104 0.0246 1.0000
16.500 1.3174 0.07830 0.07252 -0.0111 0.0242 1.0000
16.750 1.3114 0.08248 0.07683 -0.0122 0.0238 1.0000
17.000 1.3049 0.08687 0.08134 -0.0136 0.0235 1.0000
17.250 1.2976 0.09149 0.08609 -0.0152 0.0232 1.0000
17.500 1.2894 0.09637 0.09107 -0.0171 0.0230 1.0000
17.750 1.2765 0.10233 0.09720 -0.0197 0.0228 1.0000
18.000 1.2590 0.10956 0.10467 -0.0233 0.0226 1.0000
18.250 1.2392 0.11761 0.11295 -0.0278 0.0225 1.0000
18.500 1.2162 0.12677 0.12234 -0.0333 0.0224 1.0000
18.750 1.1883 0.13761 0.13341 -0.0401 0.0224 1.0000
19.000 1.1480 0.15244 0.14850 -0.0497 0.0225 1.0000
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