NASA/LANGLEY LS(1)-0421MOD AIRFOIL (ls421mod-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: NASA/LANGLEY LS(1)-0421MOD AIRFOIL (ls421mod-il) Reynolds number: 200,000 Max Cl/Cd: 51.9 at α=7° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ls421mod-il-200000.txt Download as CSV file: xf-ls421mod-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: NASA/LANGLEY LS(1)-0421MOD 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
------ -------- --------- --------- -------- -------- --------
-17.500 -0.7269 0.11013 0.10526 -0.0511 1.0000 0.0514
-17.250 -0.7755 0.09748 0.09239 -0.0587 1.0000 0.0509
-17.000 -0.8195 0.08694 0.08156 -0.0649 1.0000 0.0506
-16.750 -0.8553 0.07871 0.07306 -0.0691 1.0000 0.0504
-16.500 -0.8838 0.07217 0.06626 -0.0719 1.0000 0.0503
-16.250 -0.9069 0.06683 0.06066 -0.0737 1.0000 0.0504
-16.000 -0.9250 0.06234 0.05593 -0.0746 1.0000 0.0505
-15.750 -0.9390 0.05846 0.05181 -0.0751 1.0000 0.0506
-15.500 -0.9500 0.05505 0.04816 -0.0751 1.0000 0.0509
-15.250 -0.9593 0.05200 0.04486 -0.0748 1.0000 0.0512
-15.000 -0.9671 0.04930 0.04191 -0.0742 1.0000 0.0514
-14.750 -0.9469 0.04762 0.04027 -0.0739 1.0000 0.0521
-14.500 -0.9330 0.04613 0.03878 -0.0735 1.0000 0.0527
-14.250 -0.9220 0.04464 0.03725 -0.0730 1.0000 0.0535
-14.000 -0.9113 0.04319 0.03576 -0.0724 1.0000 0.0543
-13.750 -0.9030 0.04168 0.03414 -0.0715 1.0000 0.0552
-13.500 -0.8974 0.04015 0.03245 -0.0704 1.0000 0.0561
-13.250 -0.8956 0.03871 0.03083 -0.0687 1.0000 0.0569
-13.000 -0.8709 0.03771 0.02995 -0.0682 1.0000 0.0581
-12.750 -0.8581 0.03687 0.02916 -0.0668 1.0000 0.0591
-12.500 -0.8531 0.03612 0.02841 -0.0643 1.0000 0.0601
-12.250 -0.8606 0.03570 0.02798 -0.0599 1.0000 0.0608
-12.000 -0.8825 0.03567 0.02794 -0.0534 1.0000 0.0611
-11.750 -0.8531 0.03439 0.02647 -0.0555 0.9956 0.0629
-11.500 -0.8131 0.03335 0.02559 -0.0579 0.9929 0.0649
-11.250 -0.7787 0.03227 0.02451 -0.0604 0.9883 0.0675
-11.000 -0.7439 0.03113 0.02333 -0.0628 0.9830 0.0703
-10.750 -0.7065 0.03008 0.02238 -0.0657 0.9791 0.0736
-10.500 -0.6704 0.02898 0.02124 -0.0683 0.9749 0.0773
-10.250 -0.6385 0.02794 0.02030 -0.0703 0.9678 0.0813
-10.000 -0.6043 0.02680 0.01920 -0.0728 0.9624 0.0865
-9.750 -0.5771 0.02588 0.01824 -0.0740 0.9526 0.0924
-9.500 -0.5499 0.02477 0.01724 -0.0752 0.9445 0.0992
-9.250 -0.5322 0.02385 0.01638 -0.0747 0.9320 0.1062
-9.000 -0.5146 0.02296 0.01553 -0.0740 0.9217 0.1149
-8.750 -0.5017 0.02222 0.01481 -0.0724 0.9093 0.1243
-8.500 -0.4862 0.02144 0.01408 -0.0714 0.8988 0.1359
-8.250 -0.4700 0.02065 0.01336 -0.0705 0.8880 0.1494
-8.000 -0.4520 0.01990 0.01269 -0.0700 0.8786 0.1660
-7.750 -0.4325 0.01916 0.01203 -0.0698 0.8685 0.1860
-7.500 -0.4106 0.01839 0.01133 -0.0699 0.8611 0.2100
-7.250 -0.3887 0.01766 0.01078 -0.0702 0.8508 0.2395
-7.000 -0.3642 0.01685 0.01014 -0.0708 0.8425 0.2772
-6.750 -0.3380 0.01607 0.00960 -0.0718 0.8345 0.3258
-6.500 -0.3098 0.01534 0.00915 -0.0730 0.8255 0.3843
-6.250 -0.2801 0.01475 0.00887 -0.0740 0.8183 0.4484
-6.000 -0.2509 0.01460 0.00897 -0.0743 0.8099 0.5030
-5.750 -0.2213 0.01470 0.00916 -0.0743 0.8011 0.5416
-5.500 -0.1913 0.01489 0.00931 -0.0741 0.7942 0.5676
-5.250 -0.1619 0.01516 0.00957 -0.0741 0.7851 0.5874
-5.000 -0.1309 0.01537 0.00968 -0.0743 0.7768 0.6046
-4.750 -0.1051 0.01590 0.01018 -0.0726 0.7700 0.6141
-4.500 -0.0754 0.01619 0.01044 -0.0726 0.7605 0.6271
-4.250 -0.0505 0.01680 0.01103 -0.0706 0.7527 0.6344
-4.000 -0.0192 0.01704 0.01114 -0.0711 0.7458 0.6464
-3.750 0.0044 0.01761 0.01175 -0.0690 0.7370 0.6505
-3.500 0.0304 0.01808 0.01217 -0.0674 0.7295 0.6563
-3.250 0.0624 0.01820 0.01216 -0.0683 0.7223 0.6673
-3.000 0.0851 0.01875 0.01274 -0.0660 0.7138 0.6705
-2.750 0.1104 0.01918 0.01312 -0.0643 0.7070 0.6744
-2.500 0.1375 0.01953 0.01341 -0.0635 0.7000 0.6807
-2.250 0.1671 0.01960 0.01344 -0.0639 0.6913 0.6896
-2.000 0.1897 0.02014 0.01393 -0.0613 0.6844 0.6929
-1.750 0.2132 0.02064 0.01441 -0.0592 0.6774 0.6968
-1.500 0.2420 0.02071 0.01446 -0.0594 0.6691 0.7043
-1.250 0.2735 0.02055 0.01417 -0.0605 0.6621 0.7113
-1.000 0.2968 0.02082 0.01443 -0.0587 0.6547 0.7138
-0.750 0.3213 0.02097 0.01458 -0.0574 0.6464 0.7168
-0.500 0.3492 0.02099 0.01451 -0.0571 0.6395 0.7210
-0.250 0.3858 0.02072 0.01417 -0.0602 0.6309 0.7295
0.000 0.4128 0.02063 0.01404 -0.0600 0.6226 0.7330
0.250 0.4368 0.02078 0.01409 -0.0583 0.6160 0.7354
0.500 0.4591 0.02094 0.01432 -0.0567 0.6075 0.7388
0.750 0.4860 0.02098 0.01432 -0.0563 0.5997 0.7434
1.000 0.5206 0.02086 0.01408 -0.0584 0.5924 0.7490
1.250 0.5534 0.02067 0.01389 -0.0603 0.5832 0.7539
1.500 0.5775 0.02067 0.01384 -0.0590 0.5760 0.7559
1.750 0.6023 0.02072 0.01389 -0.0583 0.5679 0.7581
2.000 0.6280 0.02072 0.01388 -0.0577 0.5591 0.7610
2.250 0.6573 0.02072 0.01376 -0.0581 0.5508 0.7646
2.500 0.6878 0.02061 0.01368 -0.0592 0.5401 0.7686
2.750 0.7280 0.02052 0.01341 -0.0627 0.5311 0.7730
3.000 0.7512 0.02047 0.01345 -0.0618 0.5217 0.7754
3.250 0.7747 0.02048 0.01342 -0.0607 0.5135 0.7775
3.500 0.7997 0.02053 0.01347 -0.0602 0.5048 0.7798
3.750 0.8261 0.02053 0.01347 -0.0601 0.4955 0.7825
4.000 0.8548 0.02059 0.01347 -0.0605 0.4868 0.7858
4.250 0.8850 0.02060 0.01350 -0.0615 0.4764 0.7896
4.500 0.9214 0.02067 0.01347 -0.0640 0.4670 0.7931
4.750 0.9453 0.02067 0.01352 -0.0635 0.4567 0.7954
5.000 0.9677 0.02078 0.01354 -0.0624 0.4481 0.7976
5.250 0.9890 0.02085 0.01371 -0.0612 0.4376 0.8002
5.500 1.0146 0.02100 0.01376 -0.0611 0.4281 0.8029
5.750 1.0397 0.02110 0.01394 -0.0610 0.4167 0.8058
6.000 1.0675 0.02129 0.01406 -0.0616 0.4060 0.8089
6.250 1.0975 0.02152 0.01426 -0.0630 0.3936 0.8126
6.500 1.1167 0.02169 0.01446 -0.0616 0.3824 0.8151
6.750 1.1342 0.02195 0.01464 -0.0599 0.3714 0.8176
7.000 1.1521 0.02220 0.01496 -0.0585 0.3591 0.8202
7.250 1.1705 0.02256 0.01528 -0.0574 0.3471 0.8231
7.500 1.1885 0.02298 0.01565 -0.0564 0.3343 0.8263
7.750 1.2061 0.02343 0.01612 -0.0555 0.3209 0.8297
8.000 1.2193 0.02397 0.01662 -0.0540 0.3085 0.8327
8.250 1.2266 0.02460 0.01720 -0.0511 0.2969 0.8354
8.500 1.2369 0.02532 0.01795 -0.0490 0.2845 0.8386
8.750 1.2481 0.02623 0.01882 -0.0475 0.2731 0.8423
9.000 1.2603 0.02730 0.01981 -0.0465 0.2620 0.8460
9.250 1.2765 0.02840 0.02092 -0.0464 0.2507 0.8493
9.500 1.2848 0.02952 0.02197 -0.0447 0.2420 0.8519
9.750 1.2943 0.03059 0.02310 -0.0433 0.2333 0.8547
10.000 1.3036 0.03185 0.02428 -0.0420 0.2258 0.8579
10.250 1.3156 0.03308 0.02558 -0.0414 0.2181 0.8612
10.500 1.3280 0.03449 0.02687 -0.0410 0.2114 0.8646
10.750 1.3401 0.03582 0.02831 -0.0406 0.2051 0.8677
11.000 1.3475 0.03711 0.02961 -0.0392 0.1997 0.8709
11.250 1.3577 0.03843 0.03088 -0.0382 0.1946 0.8746
11.500 1.3683 0.03990 0.03245 -0.0377 0.1895 0.8783
11.750 1.3807 0.04143 0.03397 -0.0377 0.1849 0.8817
12.000 1.3928 0.04266 0.03513 -0.0369 0.1806 0.8846
12.250 1.3996 0.04425 0.03686 -0.0361 0.1766 0.8879
12.500 1.4087 0.04582 0.03847 -0.0356 0.1727 0.8914
12.750 1.4220 0.04718 0.03976 -0.0353 0.1690 0.8949
13.000 1.4339 0.04875 0.04138 -0.0351 0.1655 0.8984
13.250 1.4391 0.05044 0.04319 -0.0342 0.1624 0.9021
13.500 1.4476 0.05204 0.04485 -0.0337 0.1593 0.9064
13.750 1.4609 0.05344 0.04621 -0.0336 0.1563 0.9105
14.000 1.4743 0.05467 0.04743 -0.0330 0.1533 0.9142
14.250 1.4764 0.05691 0.04983 -0.0326 0.1508 0.9181
14.500 1.4830 0.05891 0.05193 -0.0325 0.1480 0.9223
14.750 1.4932 0.06067 0.05371 -0.0326 0.1455 0.9264
15.000 1.5062 0.06161 0.05459 -0.0317 0.1431 0.9315
15.250 1.5158 0.06328 0.05632 -0.0313 0.1408 0.9369
15.500 1.5154 0.06599 0.05922 -0.0313 0.1389 0.9420
15.750 1.5175 0.06831 0.06166 -0.0310 0.1368 0.9479
16.000 1.5239 0.07036 0.06378 -0.0311 0.1348 0.9539
16.250 1.5325 0.07176 0.06519 -0.0306 0.1329 0.9619
16.500 1.5511 0.07206 0.06539 -0.0297 0.1309 0.9743
16.750 1.5496 0.07500 0.06850 -0.0302 0.1292 1.0000
17.000 1.5443 0.07911 0.07283 -0.0317 0.1276 1.0000
17.250 1.5433 0.08279 0.07667 -0.0332 0.1258 1.0000
17.500 1.5470 0.08590 0.07988 -0.0345 0.1241 1.0000
17.750 1.5568 0.08822 0.08223 -0.0355 0.1226 1.0000
18.000 1.5746 0.08949 0.08347 -0.0362 0.1210 1.0000
18.250 1.5964 0.09028 0.08419 -0.0362 0.1194 1.0000
18.500 1.5773 0.09624 0.09045 -0.0387 0.1184 1.0000
18.750 1.5580 0.10248 0.09695 -0.0415 0.1172 1.0000
19.000 1.5391 0.10887 0.10358 -0.0446 0.1159 1.0000
|
Polar data table (+)
Polar graphs
<< Back to NASA/LANGLEY LS(1)-0421MOD AIRFOIL (ls421mod-il)