LOCKHEED L-188 TIP AIRFOIL (l188tip-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: LOCKHEED L-188 TIP AIRFOIL (l188tip-il) Reynolds number: 200,000 Max Cl/Cd: 79.26 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-l188tip-il-200000.txt Download as CSV file: xf-l188tip-il-200000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.4239 0.10388 0.10024 -0.0418 1.0000 0.0617
-9.750 -0.4361 0.10128 0.09769 -0.0410 1.0000 0.0634
-9.500 -0.4613 0.09788 0.09438 -0.0417 1.0000 0.0653
-9.250 -0.4155 0.09142 0.08828 -0.0361 1.0000 0.0678
-9.000 -0.4141 0.08949 0.08637 -0.0338 1.0000 0.0687
-8.750 -0.4069 0.08590 0.08278 -0.0349 0.9984 0.0703
-8.500 -0.4041 0.08096 0.07784 -0.0380 0.9960 0.0723
-8.250 -0.4106 0.07462 0.07150 -0.0429 0.9933 0.0745
-8.000 -0.5630 0.07384 0.07049 -0.0465 0.9947 0.0686
-7.750 -0.5460 0.07084 0.06747 -0.0484 0.9911 0.0704
-7.500 -0.5335 0.06570 0.06218 -0.0533 0.9861 0.0733
-7.250 -0.5676 0.04163 0.03633 -0.0600 0.9762 0.0485
-7.000 -0.5430 0.03726 0.03146 -0.0613 0.9732 0.0466
-6.750 -0.5177 0.03408 0.02761 -0.0621 0.9698 0.0474
-6.500 -0.4979 0.03078 0.02389 -0.0618 0.9650 0.0479
-6.250 -0.4692 0.02824 0.02110 -0.0629 0.9619 0.0488
-6.000 -0.4356 0.02674 0.01944 -0.0646 0.9595 0.0504
-5.750 -0.3990 0.02565 0.01816 -0.0667 0.9576 0.0533
-5.500 -0.3770 0.02470 0.01692 -0.0656 0.9517 0.0554
-5.250 -0.3461 0.02311 0.01516 -0.0665 0.9484 0.0577
-5.000 -0.3114 0.02229 0.01434 -0.0682 0.9456 0.0612
-4.750 -0.2734 0.02173 0.01361 -0.0702 0.9435 0.0659
-4.500 -0.2421 0.02066 0.01259 -0.0712 0.9404 0.0705
-4.250 -0.2190 0.02028 0.01218 -0.0704 0.9340 0.0760
-4.000 -0.1853 0.01949 0.01144 -0.0718 0.9308 0.0831
-3.750 -0.1482 0.01891 0.01085 -0.0738 0.9286 0.0932
-3.500 -0.1092 0.01833 0.01033 -0.0763 0.9269 0.1072
-3.250 -0.0928 0.01807 0.01011 -0.0742 0.9186 0.1206
-3.000 -0.0592 0.01747 0.00967 -0.0756 0.9152 0.1499
-2.750 -0.0229 0.01660 0.00925 -0.0779 0.9130 0.2296
-2.500 0.0093 0.01506 0.00913 -0.0795 0.9114 0.5547
-2.250 0.0236 0.01501 0.00939 -0.0766 0.9030 0.6556
-2.000 0.0544 0.01493 0.00944 -0.0767 0.8992 0.7180
-1.750 0.0886 0.01483 0.00938 -0.0774 0.8968 0.7611
-1.500 0.1222 0.01470 0.00927 -0.0779 0.8947 0.7946
-1.250 0.1362 0.01482 0.00946 -0.0750 0.8854 0.8200
-1.000 0.1665 0.01466 0.00934 -0.0748 0.8821 0.8479
-0.750 0.1982 0.01448 0.00920 -0.0748 0.8797 0.8763
-0.500 0.2194 0.01461 0.00938 -0.0730 0.8727 0.9067
-0.250 0.2602 0.01463 0.00942 -0.0748 0.8695 0.9450
0.000 0.3180 0.01464 0.00940 -0.0804 0.8685 0.9725
0.250 0.3690 0.01452 0.00924 -0.0852 0.8666 0.9823
0.500 0.4204 0.01433 0.00901 -0.0901 0.8648 0.9888
0.750 0.4706 0.01411 0.00876 -0.0948 0.8631 0.9960
1.000 0.4878 0.01421 0.00886 -0.0937 0.8533 1.0000
1.250 0.5127 0.01398 0.00859 -0.0932 0.8488 1.0000
1.500 0.5275 0.01409 0.00868 -0.0910 0.8404 1.0000
1.750 0.5547 0.01392 0.00848 -0.0907 0.8348 1.0000
2.000 0.5876 0.01346 0.00799 -0.0911 0.8293 1.0000
2.250 0.6144 0.01292 0.00743 -0.0900 0.8180 1.0000
2.500 0.6402 0.01249 0.00696 -0.0889 0.8062 1.0000
2.750 0.6700 0.01209 0.00654 -0.0886 0.7974 1.0000
3.000 0.6968 0.01185 0.00629 -0.0879 0.7871 1.0000
3.250 0.7215 0.01172 0.00617 -0.0869 0.7755 1.0000
3.500 0.7485 0.01156 0.00599 -0.0863 0.7641 1.0000
3.750 0.7761 0.01140 0.00582 -0.0858 0.7518 1.0000
4.000 0.8025 0.01131 0.00571 -0.0851 0.7375 1.0000
4.250 0.8269 0.01129 0.00568 -0.0840 0.7208 1.0000
4.500 0.8505 0.01131 0.00570 -0.0829 0.7015 1.0000
4.750 0.8744 0.01135 0.00572 -0.0817 0.6797 1.0000
5.000 0.8972 0.01144 0.00576 -0.0804 0.6539 1.0000
5.250 0.9186 0.01159 0.00583 -0.0788 0.6217 1.0000
5.500 0.9377 0.01185 0.00594 -0.0768 0.5781 1.0000
5.750 0.9525 0.01232 0.00613 -0.0740 0.5134 1.0000
6.000 0.9580 0.01325 0.00652 -0.0698 0.4153 1.0000
6.250 0.9597 0.01451 0.00721 -0.0652 0.3250 1.0000
6.500 0.9656 0.01567 0.00796 -0.0616 0.2585 1.0000
6.750 0.9747 0.01671 0.00869 -0.0587 0.2124 1.0000
7.000 0.9851 0.01762 0.00940 -0.0559 0.1814 1.0000
7.250 0.9961 0.01851 0.01013 -0.0532 0.1592 1.0000
7.500 1.0079 0.01944 0.01092 -0.0508 0.1422 1.0000
7.750 1.0216 0.02030 0.01172 -0.0487 0.1285 1.0000
8.000 1.0371 0.02108 0.01249 -0.0469 0.1172 1.0000
8.250 1.0518 0.02197 0.01337 -0.0450 0.1080 1.0000
8.500 1.0649 0.02307 0.01435 -0.0430 0.1002 1.0000
8.750 1.0824 0.02377 0.01516 -0.0416 0.0934 1.0000
9.000 1.0969 0.02497 0.01625 -0.0399 0.0874 1.0000
9.250 1.1145 0.02572 0.01712 -0.0386 0.0823 1.0000
9.500 1.1305 0.02667 0.01804 -0.0371 0.0777 1.0000
9.750 1.1490 0.02784 0.01925 -0.0360 0.0735 1.0000
10.000 1.1664 0.02876 0.02025 -0.0347 0.0697 1.0000
10.250 1.1840 0.02983 0.02127 -0.0336 0.0663 1.0000
10.500 1.2048 0.03116 0.02268 -0.0328 0.0630 1.0000
10.750 1.2223 0.03224 0.02390 -0.0316 0.0603 1.0000
11.000 1.2394 0.03332 0.02502 -0.0305 0.0578 1.0000
11.250 1.2666 0.03523 0.02687 -0.0308 0.0549 1.0000
11.500 1.2779 0.03636 0.02825 -0.0288 0.0532 1.0000
11.750 1.2925 0.03776 0.02984 -0.0274 0.0513 1.0000
12.000 1.3064 0.03919 0.03139 -0.0260 0.0497 1.0000
12.250 1.3212 0.04058 0.03281 -0.0248 0.0481 1.0000
12.500 1.3422 0.04325 0.03556 -0.0247 0.0463 1.0000
12.750 1.3427 0.04494 0.03755 -0.0218 0.0454 1.0000
13.000 1.3443 0.04704 0.03994 -0.0193 0.0444 1.0000
13.250 1.3453 0.04939 0.04256 -0.0170 0.0435 1.0000
13.500 1.3448 0.05184 0.04524 -0.0148 0.0427 1.0000
13.750 1.3442 0.05424 0.04782 -0.0129 0.0420 1.0000
14.000 1.3439 0.05657 0.05028 -0.0111 0.0412 1.0000
14.250 1.3430 0.05893 0.05276 -0.0096 0.0405 1.0000
14.500 1.3437 0.06171 0.05561 -0.0084 0.0398 1.0000
15.000 1.3116 0.07049 0.06487 -0.0056 0.0391 1.0000
15.250 1.2886 0.07513 0.06978 -0.0049 0.0390 1.0000
15.500 1.2639 0.08044 0.07536 -0.0051 0.0389 1.0000
15.750 1.2378 0.08642 0.08159 -0.0062 0.0389 1.0000
16.000 1.2106 0.09320 0.08859 -0.0082 0.0389 1.0000
16.250 1.1822 0.10084 0.09645 -0.0114 0.0390 1.0000
|
Polar data table (+)
Polar graphs
<< Back to LOCKHEED L-188 TIP AIRFOIL (l188tip-il)