NASA/LANGLEY MS(1)-0313 AIRFOIL (ms313-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: NASA/LANGLEY MS(1)-0313 AIRFOIL (ms313-il) Reynolds number: 100,000 Max Cl/Cd: 46.41 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ms313-il-100000.txt Download as CSV file: xf-ms313-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: NASA/LANGLEY MS(1)-0313 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.5181 0.09764 0.09269 -0.0451 1.0000 0.1528
-9.750 -0.4548 0.09688 0.09182 -0.0351 1.0000 0.1586
-9.500 -0.4787 0.09248 0.08755 -0.0396 1.0000 0.1673
-9.250 -0.4714 0.08884 0.08395 -0.0384 1.0000 0.1724
-9.000 -0.4656 0.08625 0.08140 -0.0374 1.0000 0.1790
-8.750 -0.5326 0.08201 0.07740 -0.0395 1.0000 0.1832
-8.500 -0.5056 0.07970 0.07510 -0.0360 1.0000 0.1901
-8.250 -0.5322 0.07770 0.07322 -0.0326 1.0000 0.1933
-8.000 -0.6871 0.05484 0.04882 -0.0410 1.0000 0.0947
-7.750 -0.6839 0.04898 0.04200 -0.0397 1.0000 0.0800
-7.500 -0.6717 0.04497 0.03783 -0.0389 1.0000 0.0791
-7.250 -0.6572 0.04147 0.03407 -0.0383 1.0000 0.0779
-7.000 -0.6397 0.03830 0.03054 -0.0378 1.0000 0.0769
-6.750 -0.6196 0.03559 0.02742 -0.0374 1.0000 0.0767
-6.500 -0.5978 0.03364 0.02502 -0.0369 1.0000 0.0786
-6.250 -0.5743 0.03193 0.02288 -0.0366 1.0000 0.0805
-6.000 -0.5502 0.02970 0.02058 -0.0365 1.0000 0.0827
-5.750 -0.5263 0.02838 0.01919 -0.0362 1.0000 0.0857
-5.500 -0.5021 0.02741 0.01805 -0.0358 1.0000 0.0907
-5.250 -0.4774 0.02613 0.01668 -0.0354 1.0000 0.0952
-5.000 -0.4534 0.02515 0.01578 -0.0351 1.0000 0.1012
-4.750 -0.4287 0.02427 0.01488 -0.0348 1.0000 0.1095
-4.500 -0.4038 0.02349 0.01419 -0.0347 1.0000 0.1201
-4.250 -0.3777 0.02267 0.01350 -0.0349 1.0000 0.1363
-4.000 -0.3488 0.02168 0.01282 -0.0359 1.0000 0.1669
-3.750 -0.3101 0.01912 0.01299 -0.0389 1.0000 0.5984
-3.500 -0.2948 0.02005 0.01392 -0.0355 1.0000 0.6759
-3.250 -0.2819 0.02093 0.01477 -0.0316 1.0000 0.7101
-3.000 -0.2721 0.02173 0.01556 -0.0269 1.0000 0.7338
-2.750 -0.2591 0.02241 0.01617 -0.0233 1.0000 0.7575
-2.500 -0.2426 0.02308 0.01680 -0.0201 0.9975 0.7787
-2.250 -0.2217 0.02378 0.01745 -0.0174 0.9931 0.8000
-2.000 -0.2026 0.02430 0.01790 -0.0147 0.9879 0.8249
-1.750 -0.1889 0.02473 0.01832 -0.0101 0.9830 0.8488
-1.500 -0.1733 0.02487 0.01840 -0.0071 0.9770 0.8718
-1.250 -0.1490 0.02495 0.01842 -0.0061 0.9716 0.8883
-1.000 -0.1278 0.02492 0.01832 -0.0049 0.9654 0.9035
-0.750 -0.1018 0.02490 0.01823 -0.0047 0.9590 0.9178
-0.500 -0.0701 0.02495 0.01820 -0.0059 0.9527 0.9274
-0.250 -0.0398 0.02494 0.01814 -0.0072 0.9449 0.9355
0.000 0.0013 0.02514 0.01827 -0.0104 0.9382 0.9428
0.250 0.0323 0.02513 0.01822 -0.0119 0.9286 0.9501
0.500 0.0740 0.02529 0.01833 -0.0151 0.9201 0.9568
0.750 0.1165 0.02534 0.01836 -0.0185 0.9100 0.9629
1.000 0.1561 0.02541 0.01842 -0.0213 0.8990 0.9693
1.250 0.2130 0.02532 0.01832 -0.0265 0.8876 0.9734
1.500 0.2827 0.02475 0.01775 -0.0332 0.8736 0.9751
1.750 0.3390 0.02413 0.01716 -0.0376 0.8585 0.9780
2.000 0.3940 0.02346 0.01653 -0.0418 0.8445 0.9811
2.250 0.4490 0.02261 0.01573 -0.0457 0.8315 0.9838
2.500 0.5096 0.02142 0.01461 -0.0500 0.8198 0.9851
2.750 0.5676 0.02008 0.01332 -0.0537 0.8071 0.9869
3.000 0.6111 0.01909 0.01242 -0.0553 0.7889 0.9912
3.250 0.6501 0.01820 0.01161 -0.0563 0.7663 0.9960
3.500 0.6886 0.01714 0.01058 -0.0568 0.7405 1.0000
3.750 0.7036 0.01657 0.01004 -0.0537 0.7084 1.0000
4.000 0.7159 0.01609 0.00954 -0.0501 0.6603 1.0000
4.250 0.7301 0.01573 0.00869 -0.0463 0.5480 1.0000
4.500 0.7315 0.01673 0.00867 -0.0413 0.4132 1.0000
4.750 0.7396 0.01800 0.00926 -0.0386 0.3370 1.0000
5.000 0.7582 0.01908 0.00995 -0.0377 0.2936 1.0000
5.250 0.7821 0.02011 0.01066 -0.0378 0.2674 1.0000
5.500 0.8095 0.02105 0.01144 -0.0384 0.2479 1.0000
5.750 0.8385 0.02201 0.01225 -0.0393 0.2331 1.0000
6.000 0.8691 0.02305 0.01309 -0.0405 0.2212 1.0000
6.250 0.8997 0.02392 0.01404 -0.0415 0.2114 1.0000
6.500 0.9328 0.02513 0.01510 -0.0431 0.2039 1.0000
6.750 0.9632 0.02607 0.01618 -0.0440 0.1966 1.0000
7.000 0.9959 0.02729 0.01724 -0.0455 0.1901 1.0000
7.250 1.0261 0.02847 0.01861 -0.0465 0.1848 1.0000
7.500 1.0560 0.02967 0.01995 -0.0474 0.1800 1.0000
7.750 1.0868 0.03100 0.02126 -0.0485 0.1758 1.0000
8.000 1.1160 0.03267 0.02304 -0.0494 0.1718 1.0000
8.250 1.1412 0.03403 0.02470 -0.0495 0.1676 1.0000
8.500 1.1678 0.03556 0.02640 -0.0499 0.1641 1.0000
8.750 1.1944 0.03712 0.02806 -0.0504 0.1607 1.0000
9.000 1.2199 0.03940 0.03041 -0.0509 0.1573 1.0000
9.250 1.2362 0.04122 0.03270 -0.0498 0.1543 1.0000
9.500 1.2533 0.04328 0.03511 -0.0489 0.1510 1.0000
9.750 1.2737 0.04503 0.03701 -0.0486 0.1475 1.0000
10.000 1.2996 0.04694 0.03882 -0.0492 0.1438 1.0000
10.250 1.3068 0.04990 0.04221 -0.0473 0.1413 1.0000
10.500 1.3064 0.05283 0.04565 -0.0446 0.1388 1.0000
10.750 1.3057 0.05586 0.04907 -0.0421 0.1361 1.0000
11.000 1.3082 0.05862 0.05209 -0.0401 0.1336 1.0000
11.250 1.3441 0.05959 0.05282 -0.0415 0.1294 1.0000
11.500 1.3371 0.06373 0.05723 -0.0391 0.1275 1.0000
11.750 1.3098 0.06782 0.06177 -0.0347 0.1267 1.0000
12.000 1.2766 0.07209 0.06634 -0.0304 0.1264 1.0000
12.250 1.2396 0.07729 0.07182 -0.0276 0.1264 1.0000
12.500 1.1997 0.08374 0.07849 -0.0266 0.1268 1.0000
12.750 1.1589 0.09159 0.08651 -0.0277 0.1274 1.0000
13.000 1.1219 0.10071 0.09575 -0.0304 0.1280 1.0000
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Polar data table (+)
Polar graphs
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