NASA/LANGLEY LS(1)-0417MOD AIRFOIL (ls417mod-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: NASA/LANGLEY LS(1)-0417MOD AIRFOIL (ls417mod-il) Reynolds number: 100,000 Max Cl/Cd: 41.13 at α=9° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ls417mod-il-100000-n5.txt Download as CSV file: xf-ls417mod-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NASA/LANGLEY LS(1)-0417MOD 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
------ -------- --------- --------- -------- -------- --------
-13.750 -0.4620 0.13187 0.12596 -0.0313 1.0000 0.0373
-13.500 -0.4705 0.12472 0.11883 -0.0347 1.0000 0.0378
-13.250 -0.6861 0.07375 0.06701 -0.0669 1.0000 0.0349
-12.750 -0.7251 0.06399 0.05689 -0.0704 1.0000 0.0351
-12.500 -0.7327 0.06088 0.05369 -0.0706 1.0000 0.0353
-12.250 -0.7408 0.05798 0.05069 -0.0704 1.0000 0.0356
-12.000 -0.7500 0.05525 0.04783 -0.0696 1.0000 0.0359
-11.750 -0.7598 0.05278 0.04523 -0.0681 1.0000 0.0362
-11.500 -0.7709 0.05061 0.04293 -0.0657 1.0000 0.0364
-11.250 -0.7841 0.04877 0.04097 -0.0624 1.0000 0.0367
-11.000 -0.7946 0.04701 0.03907 -0.0591 1.0000 0.0369
-10.750 -0.8008 0.04526 0.03716 -0.0561 1.0000 0.0372
-10.500 -0.8048 0.04364 0.03537 -0.0529 1.0000 0.0376
-10.250 -0.8068 0.04209 0.03364 -0.0498 1.0000 0.0380
-10.000 -0.8062 0.04058 0.03192 -0.0468 1.0000 0.0385
-9.750 -0.8031 0.03912 0.03020 -0.0440 1.0000 0.0391
-9.500 -0.7825 0.03790 0.02900 -0.0441 0.9976 0.0399
-9.250 -0.7544 0.03658 0.02761 -0.0456 0.9936 0.0412
-9.000 -0.7268 0.03513 0.02596 -0.0467 0.9894 0.0429
-8.750 -0.6987 0.03385 0.02459 -0.0477 0.9850 0.0442
-8.500 -0.6691 0.03273 0.02346 -0.0489 0.9813 0.0455
-8.250 -0.6408 0.03162 0.02227 -0.0497 0.9776 0.0470
-8.000 -0.6145 0.03060 0.02117 -0.0500 0.9729 0.0486
-7.750 -0.5861 0.02971 0.02032 -0.0511 0.9690 0.0507
-7.500 -0.5551 0.02882 0.01935 -0.0523 0.9660 0.0535
-7.250 -0.5305 0.02798 0.01857 -0.0526 0.9604 0.0557
-7.000 -0.5002 0.02712 0.01765 -0.0537 0.9553 0.0586
-6.750 -0.4644 0.02617 0.01675 -0.0561 0.9512 0.0625
-6.500 -0.4355 0.02535 0.01595 -0.0570 0.9439 0.0674
-6.250 -0.3999 0.02444 0.01507 -0.0592 0.9379 0.0744
-6.000 -0.3609 0.02350 0.01417 -0.0619 0.9339 0.0854
-5.750 -0.3349 0.02274 0.01353 -0.0622 0.9255 0.1002
-5.500 -0.3012 0.02183 0.01282 -0.0640 0.9195 0.1284
-5.250 -0.2642 0.02080 0.01210 -0.0665 0.9151 0.1783
-5.000 -0.2397 0.01993 0.01162 -0.0668 0.9057 0.2446
-4.750 -0.2059 0.01882 0.01105 -0.0690 0.8996 0.3476
-4.500 -0.1737 0.01810 0.01099 -0.0699 0.8942 0.4599
-4.250 -0.1540 0.01849 0.01182 -0.0667 0.8840 0.5364
-4.000 -0.1198 0.01872 0.01204 -0.0669 0.8770 0.5894
-3.750 -0.0924 0.01905 0.01231 -0.0659 0.8674 0.6161
-3.500 -0.0610 0.01924 0.01239 -0.0656 0.8575 0.6363
-3.250 -0.0308 0.01935 0.01237 -0.0654 0.8466 0.6532
-3.000 -0.0048 0.01970 0.01267 -0.0637 0.8358 0.6653
-2.750 0.0218 0.01998 0.01287 -0.0623 0.8254 0.6781
-2.500 0.0486 0.02018 0.01299 -0.0611 0.8133 0.6904
-2.250 0.0745 0.02027 0.01302 -0.0599 0.8004 0.6985
-2.000 0.1016 0.02029 0.01295 -0.0587 0.7870 0.7044
-1.750 0.1297 0.02017 0.01272 -0.0587 0.7695 0.7129
-1.500 0.1564 0.02009 0.01255 -0.0580 0.7506 0.7190
-1.250 0.1800 0.02011 0.01250 -0.0562 0.7282 0.7238
-1.000 0.2062 0.02004 0.01231 -0.0554 0.6994 0.7302
-0.750 0.2373 0.01986 0.01192 -0.0561 0.6555 0.7384
-0.500 0.2598 0.01993 0.01169 -0.0540 0.5962 0.7421
-0.250 0.2822 0.02017 0.01151 -0.0523 0.5425 0.7466
0.000 0.3065 0.02043 0.01144 -0.0515 0.5083 0.7519
0.250 0.3355 0.02064 0.01136 -0.0522 0.4848 0.7578
0.500 0.3613 0.02081 0.01137 -0.0519 0.4678 0.7615
0.750 0.3857 0.02100 0.01144 -0.0510 0.4546 0.7646
1.000 0.4114 0.02120 0.01149 -0.0506 0.4429 0.7683
1.250 0.4394 0.02135 0.01154 -0.0508 0.4326 0.7720
1.500 0.4691 0.02151 0.01158 -0.0516 0.4228 0.7759
1.750 0.5014 0.02170 0.01162 -0.0530 0.4143 0.7798
2.000 0.5280 0.02182 0.01172 -0.0528 0.4061 0.7819
2.250 0.5541 0.02200 0.01183 -0.0525 0.3987 0.7844
2.500 0.5813 0.02223 0.01195 -0.0525 0.3921 0.7871
2.750 0.6095 0.02238 0.01212 -0.0528 0.3850 0.7899
3.000 0.6387 0.02257 0.01226 -0.0534 0.3782 0.7924
3.250 0.6686 0.02285 0.01242 -0.0541 0.3723 0.7955
3.500 0.6998 0.02307 0.01265 -0.0553 0.3658 0.7988
3.750 0.7274 0.02327 0.01287 -0.0555 0.3596 0.8011
4.000 0.7539 0.02349 0.01307 -0.0554 0.3541 0.8031
4.250 0.7813 0.02380 0.01329 -0.0555 0.3491 0.8052
4.500 0.8083 0.02402 0.01360 -0.0556 0.3433 0.8076
4.750 0.8356 0.02428 0.01389 -0.0558 0.3376 0.8105
5.000 0.8639 0.02458 0.01415 -0.0562 0.3325 0.8136
5.250 0.8935 0.02494 0.01447 -0.0570 0.3278 0.8166
5.500 0.9218 0.02525 0.01488 -0.0575 0.3221 0.8191
5.750 0.9467 0.02553 0.01521 -0.0572 0.3169 0.8211
6.000 0.9723 0.02582 0.01550 -0.0570 0.3123 0.8234
6.250 0.9985 0.02620 0.01586 -0.0570 0.3080 0.8259
6.500 1.0237 0.02656 0.01637 -0.0569 0.3025 0.8289
6.750 1.0500 0.02693 0.01679 -0.0570 0.2974 0.8322
7.000 1.0777 0.02731 0.01715 -0.0575 0.2929 0.8356
7.250 1.1025 0.02772 0.01761 -0.0573 0.2884 0.8383
7.500 1.1250 0.02813 0.01817 -0.0567 0.2832 0.8410
7.750 1.1485 0.02851 0.01861 -0.0563 0.2783 0.8438
8.000 1.1733 0.02889 0.01899 -0.0562 0.2742 0.8469
8.250 1.1971 0.02941 0.01961 -0.0560 0.2694 0.8502
8.500 1.2208 0.02994 0.02027 -0.0559 0.2641 0.8536
8.750 1.2420 0.03034 0.02073 -0.0551 0.2596 0.8567
9.000 1.2640 0.03073 0.02109 -0.0544 0.2559 0.8604
9.250 1.2823 0.03136 0.02195 -0.0534 0.2507 0.8647
9.500 1.3027 0.03193 0.02263 -0.0528 0.2457 0.8691
9.750 1.3223 0.03236 0.02309 -0.0519 0.2416 0.8730
10.000 1.3394 0.03295 0.02377 -0.0506 0.2373 0.8771
10.250 1.3548 0.03366 0.02467 -0.0493 0.2323 0.8816
10.500 1.3722 0.03426 0.02534 -0.0484 0.2278 0.8863
10.750 1.3874 0.03471 0.02576 -0.0468 0.2244 0.8909
11.000 1.3942 0.03563 0.02694 -0.0443 0.2196 0.8965
11.250 1.4057 0.03646 0.02791 -0.0426 0.2151 0.9024
11.500 1.4168 0.03709 0.02858 -0.0407 0.2114 0.9090
11.750 1.4258 0.03810 0.02973 -0.0390 0.2073 0.9166
12.000 1.4301 0.03922 0.03105 -0.0367 0.2029 0.9254
12.250 1.4371 0.04017 0.03210 -0.0348 0.1991 0.9358
12.500 1.4460 0.04102 0.03296 -0.0332 0.1957 0.9501
12.750 1.4435 0.04270 0.03493 -0.0312 0.1914 1.0000
13.000 1.4510 0.04443 0.03678 -0.0308 0.1871 1.0000
13.250 1.4623 0.04584 0.03820 -0.0306 0.1835 1.0000
13.500 1.4621 0.04840 0.04097 -0.0302 0.1793 1.0000
13.750 1.4631 0.05088 0.04360 -0.0300 0.1752 1.0000
14.000 1.4689 0.05288 0.04564 -0.0299 0.1718 1.0000
14.250 1.4653 0.05598 0.04889 -0.0299 0.1682 1.0000
14.500 1.4562 0.05980 0.05292 -0.0303 0.1644 1.0000
14.750 1.4539 0.06293 0.05613 -0.0307 0.1610 1.0000
15.000 1.4525 0.06604 0.05929 -0.0312 0.1580 1.0000
15.250 1.4263 0.07266 0.06620 -0.0332 0.1546 1.0000
15.500 1.4086 0.07852 0.07222 -0.0353 0.1512 1.0000
15.750 1.4123 0.08133 0.07502 -0.0363 0.1482 1.0000
16.000 1.3612 0.09313 0.08714 -0.0418 0.1448 1.0000
16.250 1.2919 0.10884 0.10314 -0.0497 0.1403 1.0000
16.500 1.3257 0.10659 0.10080 -0.0482 0.1379 1.0000
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Polar data table (+)
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