NASA/LANGLEY MS(1)-0313 AIRFOIL (ms313-il) Xfoil prediction polar at RE=50,000 Ncrit=9
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Airfoil: NASA/LANGLEY MS(1)-0313 AIRFOIL (ms313-il) Reynolds number: 50,000 Max Cl/Cd: 31.58 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ms313-il-50000.txt Download as CSV file: xf-ms313-il-50000.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 = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.4055 0.10478 0.09770 -0.0144 1.0000 0.3823
-8.750 -0.3771 0.09970 0.09258 -0.0143 1.0000 0.3893
-8.500 -0.5275 0.08083 0.07417 -0.0376 1.0000 0.1948
-8.250 -0.5787 0.07408 0.06746 -0.0398 1.0000 0.1765
-8.000 -0.6152 0.06818 0.06139 -0.0402 1.0000 0.1625
-7.750 -0.6402 0.06218 0.05492 -0.0407 1.0000 0.1502
-7.500 -0.6393 0.05778 0.05029 -0.0399 1.0000 0.1448
-7.250 -0.6406 0.05254 0.04411 -0.0404 1.0000 0.1364
-7.000 -0.6277 0.04894 0.04022 -0.0398 1.0000 0.1352
-6.750 -0.6127 0.04567 0.03646 -0.0395 1.0000 0.1357
-6.500 -0.5940 0.04281 0.03303 -0.0393 1.0000 0.1371
-6.250 -0.5733 0.03984 0.02980 -0.0390 1.0000 0.1388
-6.000 -0.5518 0.03752 0.02738 -0.0385 1.0000 0.1421
-5.750 -0.5289 0.03566 0.02526 -0.0380 1.0000 0.1484
-5.500 -0.5041 0.03376 0.02295 -0.0376 1.0000 0.1542
-5.250 -0.4809 0.03218 0.02142 -0.0367 1.0000 0.1631
-5.000 -0.4568 0.03075 0.01995 -0.0358 1.0000 0.1745
-4.750 -0.4333 0.02952 0.01876 -0.0346 1.0000 0.1897
-4.500 -0.4106 0.02838 0.01775 -0.0332 1.0000 0.2120
-4.250 -0.3873 0.02700 0.01667 -0.0323 1.0000 0.2512
-4.000 -0.3684 0.02389 0.01616 -0.0304 1.0000 0.4985
-3.750 -0.3796 0.02630 0.01900 -0.0166 1.0000 0.6971
-3.500 -0.3829 0.02783 0.02041 -0.0063 1.0000 0.7519
-3.250 -0.3831 0.02865 0.02111 0.0023 1.0000 0.7948
-3.000 -0.3825 0.02901 0.02135 0.0105 1.0000 0.8323
-2.750 -0.3780 0.02900 0.02119 0.0172 1.0000 0.8717
-2.500 -0.1211 0.03052 0.02157 -0.0162 1.0000 0.9883
-2.250 -0.0747 0.03013 0.02095 -0.0220 1.0000 1.0000
-2.000 -0.0745 0.02985 0.02061 -0.0194 1.0000 1.0000
-1.750 -0.0740 0.02959 0.02029 -0.0167 1.0000 1.0000
-1.500 -0.0735 0.02934 0.01998 -0.0140 1.0000 1.0000
-1.250 -0.0728 0.02910 0.01968 -0.0113 1.0000 1.0000
-1.000 -0.0721 0.02886 0.01940 -0.0086 1.0000 1.0000
-0.750 -0.0714 0.02862 0.01912 -0.0059 1.0000 1.0000
-0.500 -0.0704 0.02838 0.01884 -0.0032 1.0000 1.0000
-0.250 -0.0691 0.02815 0.01858 -0.0006 1.0000 1.0000
0.000 -0.0671 0.02794 0.01834 0.0018 1.0000 1.0000
0.250 -0.0628 0.02778 0.01816 0.0039 1.0000 1.0000
0.500 -0.0528 0.02779 0.01814 0.0048 1.0000 1.0000
0.750 -0.0372 0.02799 0.01830 0.0048 1.0000 1.0000
1.000 -0.0178 0.02835 0.01863 0.0040 1.0000 1.0000
1.250 0.0042 0.02886 0.01912 0.0027 1.0000 1.0000
1.500 0.0277 0.02949 0.01973 0.0011 1.0000 1.0000
1.750 0.0520 0.03024 0.02048 -0.0007 1.0000 1.0000
2.000 0.0765 0.03110 0.02136 -0.0027 1.0000 1.0000
2.250 0.1146 0.03241 0.02269 -0.0073 0.9944 1.0000
2.500 0.1897 0.03438 0.02470 -0.0179 0.9647 1.0000
2.750 0.2579 0.03574 0.02613 -0.0262 0.9321 1.0000
3.000 0.3230 0.03654 0.02703 -0.0330 0.8985 1.0000
3.250 0.3848 0.03677 0.02738 -0.0383 0.8655 1.0000
3.500 0.4452 0.03639 0.02715 -0.0423 0.8330 1.0000
3.750 0.5053 0.03531 0.02626 -0.0452 0.8011 1.0000
4.000 0.5661 0.03340 0.02457 -0.0469 0.7690 1.0000
4.250 0.6239 0.03069 0.02209 -0.0470 0.7341 1.0000
4.500 0.6770 0.02731 0.01893 -0.0452 0.6887 1.0000
4.750 0.7216 0.02400 0.01550 -0.0416 0.5951 1.0000
5.000 0.7555 0.02392 0.01413 -0.0390 0.4648 1.0000
5.250 0.7822 0.02551 0.01498 -0.0385 0.4010 1.0000
5.500 0.8133 0.02700 0.01616 -0.0392 0.3622 1.0000
5.750 0.8472 0.02844 0.01729 -0.0404 0.3353 1.0000
6.000 0.8786 0.02987 0.01867 -0.0413 0.3152 1.0000
6.250 0.9120 0.03144 0.02015 -0.0425 0.3007 1.0000
6.500 0.9419 0.03299 0.02178 -0.0433 0.2881 1.0000
6.750 0.9692 0.03467 0.02362 -0.0438 0.2773 1.0000
7.000 0.9997 0.03648 0.02538 -0.0447 0.2685 1.0000
7.250 1.0233 0.03851 0.02781 -0.0447 0.2619 1.0000
7.500 1.0511 0.04049 0.02984 -0.0453 0.2554 1.0000
7.750 1.0714 0.04285 0.03252 -0.0450 0.2497 1.0000
8.000 1.0892 0.04524 0.03526 -0.0445 0.2441 1.0000
8.250 1.1110 0.04775 0.03796 -0.0445 0.2401 1.0000
8.500 1.1329 0.05068 0.04100 -0.0446 0.2367 1.0000
8.750 1.1358 0.05414 0.04503 -0.0428 0.2343 1.0000
9.000 1.1344 0.05795 0.04930 -0.0411 0.2318 1.0000
9.250 1.1292 0.06213 0.05387 -0.0393 0.2299 1.0000
9.500 1.1136 0.06717 0.05928 -0.0374 0.2301 1.0000
9.750 1.0849 0.07320 0.06561 -0.0355 0.2319 1.0000
10.000 1.0505 0.07967 0.07225 -0.0342 0.2342 1.0000
10.250 1.0286 0.08643 0.07911 -0.0346 0.2363 1.0000
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Polar data table (+)
Polar graphs
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