NASA/LANGLEY LS(1)-0421MOD AIRFOIL (ls421mod-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: NASA/LANGLEY LS(1)-0421MOD AIRFOIL (ls421mod-il) Reynolds number: 100,000 Max Cl/Cd: 38.35 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ls421mod-il-100000-n5.txt Download as CSV file: xf-ls421mod-il-100000-n5.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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.500 -0.7468 0.09044 0.08318 -0.0610 1.0000 0.0486
-16.250 -0.7727 0.08281 0.07528 -0.0651 1.0000 0.0488
-16.000 -0.7893 0.07705 0.06930 -0.0678 1.0000 0.0492
-15.750 -0.8015 0.07222 0.06426 -0.0698 1.0000 0.0497
-15.500 -0.8110 0.06795 0.05978 -0.0713 1.0000 0.0503
-15.250 -0.8190 0.06407 0.05566 -0.0723 1.0000 0.0510
-15.000 -0.8213 0.06100 0.05243 -0.0728 1.0000 0.0517
-14.750 -0.8137 0.05909 0.05054 -0.0729 1.0000 0.0524
-14.500 -0.8083 0.05703 0.04843 -0.0730 1.0000 0.0532
-14.250 -0.8034 0.05492 0.04626 -0.0730 1.0000 0.0541
-14.000 -0.7984 0.05283 0.04406 -0.0728 1.0000 0.0552
-13.750 -0.7925 0.05082 0.04190 -0.0725 1.0000 0.0563
-13.500 -0.7842 0.04908 0.04008 -0.0720 1.0000 0.0573
-13.250 -0.7735 0.04770 0.03873 -0.0715 1.0000 0.0583
-13.000 -0.7643 0.04629 0.03732 -0.0709 1.0000 0.0595
-12.750 -0.7557 0.04490 0.03589 -0.0701 1.0000 0.0609
-12.500 -0.7474 0.04357 0.03445 -0.0690 1.0000 0.0627
-12.250 -0.7398 0.04244 0.03338 -0.0677 1.0000 0.0641
-12.000 -0.7352 0.04143 0.03241 -0.0660 1.0000 0.0655
-11.750 -0.7343 0.04058 0.03157 -0.0635 1.0000 0.0671
-11.500 -0.7381 0.03994 0.03090 -0.0601 1.0000 0.0685
-11.250 -0.7187 0.03874 0.02972 -0.0609 0.9936 0.0708
-11.000 -0.6922 0.03740 0.02837 -0.0629 0.9849 0.0739
-10.750 -0.6635 0.03609 0.02704 -0.0652 0.9775 0.0778
-10.500 -0.6388 0.03487 0.02582 -0.0668 0.9672 0.0819
-10.250 -0.6127 0.03366 0.02461 -0.0684 0.9586 0.0864
-10.000 -0.5886 0.03258 0.02350 -0.0695 0.9479 0.0921
-9.750 -0.5666 0.03147 0.02244 -0.0704 0.9374 0.0977
-9.500 -0.5443 0.03042 0.02141 -0.0710 0.9271 0.1046
-9.250 -0.5249 0.02953 0.02051 -0.0709 0.9157 0.1123
-9.000 -0.5044 0.02862 0.01959 -0.0709 0.9059 0.1216
-8.750 -0.4907 0.02781 0.01884 -0.0698 0.8939 0.1306
-8.500 -0.4733 0.02700 0.01806 -0.0692 0.8844 0.1419
-8.250 -0.4580 0.02629 0.01740 -0.0682 0.8729 0.1546
-8.000 -0.4389 0.02554 0.01668 -0.0677 0.8638 0.1704
-7.750 -0.4213 0.02485 0.01605 -0.0671 0.8540 0.1879
-7.500 -0.4027 0.02413 0.01541 -0.0666 0.8443 0.2082
-7.250 -0.3830 0.02335 0.01475 -0.0663 0.8365 0.2328
-7.000 -0.3642 0.02270 0.01423 -0.0659 0.8262 0.2614
-6.750 -0.3430 0.02194 0.01365 -0.0657 0.8185 0.2963
-6.500 -0.3218 0.02131 0.01322 -0.0656 0.8101 0.3367
-6.250 -0.2991 0.02079 0.01291 -0.0653 0.8014 0.3806
-6.000 -0.2740 0.02046 0.01282 -0.0648 0.7946 0.4271
-5.750 -0.2497 0.02052 0.01309 -0.0638 0.7860 0.4690
-5.500 -0.2235 0.02074 0.01341 -0.0628 0.7777 0.5043
-5.250 -0.1955 0.02110 0.01379 -0.0617 0.7713 0.5312
-5.000 -0.1688 0.02136 0.01402 -0.0613 0.7624 0.5542
-4.750 -0.1408 0.02156 0.01414 -0.0609 0.7542 0.5727
-4.500 -0.1112 0.02166 0.01412 -0.0609 0.7479 0.5885
-4.250 -0.0834 0.02173 0.01409 -0.0614 0.7384 0.6045
-4.000 -0.0573 0.02230 0.01464 -0.0596 0.7305 0.6116
-3.750 -0.0269 0.02224 0.01442 -0.0603 0.7238 0.6254
-3.500 -0.0026 0.02278 0.01495 -0.0586 0.7146 0.6305
-3.250 0.0255 0.02299 0.01506 -0.0581 0.7071 0.6403
-3.000 0.0529 0.02326 0.01525 -0.0575 0.7001 0.6490
-2.750 0.0774 0.02375 0.01573 -0.0559 0.6914 0.6555
-2.500 0.1081 0.02357 0.01541 -0.0570 0.6844 0.6671
-2.250 0.1329 0.02394 0.01573 -0.0554 0.6774 0.6707
-2.000 0.1579 0.02418 0.01596 -0.0543 0.6689 0.6756
-1.750 0.1876 0.02405 0.01571 -0.0550 0.6621 0.6832
-1.500 0.2167 0.02394 0.01552 -0.0556 0.6552 0.6893
-1.250 0.2410 0.02412 0.01570 -0.0545 0.6469 0.6923
-1.000 0.2679 0.02418 0.01568 -0.0539 0.6401 0.6963
-0.750 0.2954 0.02420 0.01565 -0.0540 0.6328 0.7019
-0.500 0.3267 0.02404 0.01543 -0.0556 0.6245 0.7099
-0.250 0.3519 0.02414 0.01547 -0.0545 0.6180 0.7126
0.000 0.3768 0.02425 0.01557 -0.0537 0.6104 0.7158
0.250 0.4030 0.02429 0.01559 -0.0534 0.6021 0.7196
0.500 0.4331 0.02418 0.01538 -0.0540 0.5956 0.7240
0.750 0.4653 0.02407 0.01523 -0.0559 0.5867 0.7299
1.000 0.4917 0.02408 0.01521 -0.0556 0.5786 0.7328
1.250 0.5184 0.02409 0.01515 -0.0551 0.5720 0.7351
1.500 0.5425 0.02420 0.01531 -0.0546 0.5628 0.7379
1.750 0.5700 0.02421 0.01527 -0.0545 0.5553 0.7412
2.000 0.5983 0.02425 0.01528 -0.0549 0.5477 0.7450
2.250 0.6282 0.02427 0.01529 -0.0560 0.5387 0.7490
2.500 0.6619 0.02420 0.01510 -0.0576 0.5314 0.7530
2.750 0.6835 0.02437 0.01536 -0.0565 0.5222 0.7553
3.000 0.7086 0.02444 0.01540 -0.0559 0.5138 0.7577
3.250 0.7338 0.02453 0.01549 -0.0556 0.5046 0.7603
3.500 0.7592 0.02461 0.01556 -0.0554 0.4943 0.7635
3.750 0.7864 0.02470 0.01562 -0.0556 0.4845 0.7671
4.000 0.8150 0.02479 0.01569 -0.0563 0.4739 0.7708
4.250 0.8446 0.02490 0.01577 -0.0573 0.4642 0.7739
4.500 0.8663 0.02506 0.01596 -0.0563 0.4543 0.7760
4.750 0.8889 0.02523 0.01611 -0.0554 0.4453 0.7785
5.000 0.9104 0.02545 0.01638 -0.0546 0.4348 0.7815
5.250 0.9341 0.02566 0.01656 -0.0542 0.4250 0.7847
5.500 0.9578 0.02591 0.01682 -0.0541 0.4140 0.7879
5.750 0.9830 0.02619 0.01710 -0.0543 0.4033 0.7911
6.000 1.0076 0.02648 0.01735 -0.0545 0.3923 0.7941
6.250 1.0244 0.02682 0.01774 -0.0529 0.3817 0.7963
6.500 1.0416 0.02716 0.01805 -0.0514 0.3716 0.7989
6.750 1.0570 0.02762 0.01857 -0.0498 0.3604 0.8021
7.000 1.0732 0.02807 0.01896 -0.0485 0.3503 0.8057
7.250 1.0872 0.02863 0.01959 -0.0471 0.3388 0.8095
7.500 1.1039 0.02929 0.02023 -0.0465 0.3278 0.8130
7.750 1.1147 0.02999 0.02095 -0.0445 0.3169 0.8154
8.000 1.1261 0.03080 0.02180 -0.0429 0.3062 0.8181
8.500 1.1494 0.03275 0.02376 -0.0405 0.2847 0.8244
8.750 1.1615 0.03389 0.02488 -0.0398 0.2747 0.8280
9.000 1.1745 0.03518 0.02616 -0.0395 0.2644 0.8318
9.250 1.1818 0.03641 0.02742 -0.0379 0.2557 0.8347
9.500 1.1890 0.03778 0.02880 -0.0367 0.2470 0.8379
9.750 1.1978 0.03923 0.03028 -0.0358 0.2389 0.8413
10.000 1.2069 0.04081 0.03186 -0.0353 0.2310 0.8447
10.250 1.2172 0.04245 0.03350 -0.0352 0.2239 0.8480
10.500 1.2255 0.04416 0.03527 -0.0347 0.2168 0.8509
10.750 1.2312 0.04581 0.03687 -0.0338 0.2112 0.8538
11.000 1.2385 0.04758 0.03875 -0.0332 0.2049 0.8572
11.250 1.2453 0.04945 0.04064 -0.0328 0.1995 0.8609
11.500 1.2540 0.05129 0.04247 -0.0327 0.1945 0.8647
11.750 1.2606 0.05330 0.04459 -0.0325 0.1893 0.8680
12.000 1.2656 0.05522 0.04654 -0.0319 0.1848 0.8713
12.250 1.2735 0.05698 0.04825 -0.0315 0.1809 0.8748
12.500 1.2795 0.05923 0.05065 -0.0316 0.1765 0.8782
12.750 1.2864 0.06148 0.05296 -0.0318 0.1724 0.8817
13.000 1.2933 0.06334 0.05481 -0.0315 0.1689 0.8853
13.250 1.2991 0.06541 0.05693 -0.0312 0.1656 0.8892
13.500 1.3032 0.06792 0.05957 -0.0314 0.1621 0.8933
13.750 1.3095 0.07032 0.06204 -0.0318 0.1587 0.8973
14.000 1.3160 0.07221 0.06394 -0.0315 0.1559 0.9012
14.250 1.3232 0.07422 0.06597 -0.0314 0.1532 0.9053
14.500 1.3236 0.07737 0.06930 -0.0320 0.1502 0.9091
14.750 1.3262 0.08020 0.07224 -0.0325 0.1474 0.9132
15.000 1.3303 0.08248 0.07458 -0.0325 0.1449 0.9179
15.250 1.3397 0.08421 0.07629 -0.0325 0.1427 0.9234
15.500 1.3397 0.08728 0.07948 -0.0330 0.1404 0.9285
15.750 1.3328 0.09131 0.08372 -0.0339 0.1380 0.9339
16.000 1.3304 0.09489 0.08744 -0.0349 0.1356 0.9396
16.250 1.3309 0.09775 0.09039 -0.0354 0.1335 0.9467
16.500 1.3386 0.09962 0.09227 -0.0357 0.1317 0.9560
16.750 1.3460 0.10124 0.09388 -0.0359 0.1300 0.9745
17.000 1.3224 0.10829 0.10128 -0.0392 0.1279 1.0000
17.250 1.3014 0.11571 0.10895 -0.0430 0.1256 1.0000
17.500 1.2886 0.12195 0.11537 -0.0465 0.1234 1.0000
17.750 1.2937 0.12522 0.11867 -0.0485 0.1216 1.0000
18.000 1.3153 0.12563 0.11902 -0.0491 0.1201 1.0000
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