NASA/LANGLEY MS(1)-0317 AIRFOIL (ms317-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: NASA/LANGLEY MS(1)-0317 AIRFOIL (ms317-il) Reynolds number: 100,000 Max Cl/Cd: 36.16 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ms317-il-100000.txt Download as CSV file: xf-ms317-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: NASA/LANGLEY MS(1)-0317 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
------ -------- --------- --------- -------- -------- --------
-12.750 -0.6573 0.08404 0.07815 -0.0662 1.0000 0.0889
-12.500 -0.6703 0.07843 0.07250 -0.0678 1.0000 0.0883
-12.250 -0.6941 0.07265 0.06663 -0.0693 1.0000 0.0875
-12.000 -0.7240 0.06736 0.06120 -0.0699 1.0000 0.0867
-11.750 -0.7560 0.06304 0.05673 -0.0687 1.0000 0.0860
-11.500 -0.7901 0.06006 0.05364 -0.0649 1.0000 0.0853
-11.250 -0.8200 0.05755 0.05099 -0.0604 1.0000 0.0849
-11.000 -0.8458 0.05534 0.04862 -0.0554 1.0000 0.0846
-10.750 -0.8672 0.05319 0.04628 -0.0506 1.0000 0.0845
-10.500 -0.8825 0.05095 0.04382 -0.0464 1.0000 0.0846
-10.250 -0.8918 0.04868 0.04129 -0.0428 1.0000 0.0850
-10.000 -0.8956 0.04646 0.03879 -0.0398 1.0000 0.0858
-9.750 -0.8957 0.04433 0.03631 -0.0372 1.0000 0.0872
-9.500 -0.8928 0.04230 0.03382 -0.0350 1.0000 0.0888
-9.250 -0.8810 0.04032 0.03176 -0.0336 1.0000 0.0907
-9.000 -0.8665 0.03904 0.03049 -0.0323 1.0000 0.0928
-8.750 -0.8519 0.03764 0.02894 -0.0310 1.0000 0.0951
-8.500 -0.8368 0.03626 0.02725 -0.0298 1.0000 0.0982
-8.250 -0.8196 0.03482 0.02571 -0.0289 1.0000 0.1015
-8.000 -0.8016 0.03386 0.02478 -0.0280 1.0000 0.1052
-7.750 -0.7794 0.03281 0.02351 -0.0277 0.9992 0.1099
-7.500 -0.7457 0.03158 0.02238 -0.0295 0.9957 0.1162
-7.250 -0.7094 0.03059 0.02122 -0.0317 0.9921 0.1246
-7.000 -0.6777 0.02967 0.02045 -0.0331 0.9877 0.1338
-6.750 -0.6442 0.02876 0.01964 -0.0348 0.9837 0.1452
-6.500 -0.6086 0.02797 0.01895 -0.0370 0.9806 0.1599
-6.250 -0.5807 0.02722 0.01832 -0.0378 0.9759 0.1759
-6.000 -0.5483 0.02650 0.01772 -0.0395 0.9714 0.1981
-5.750 -0.5121 0.02565 0.01719 -0.0420 0.9678 0.2296
-5.500 -0.4820 0.02471 0.01666 -0.0437 0.9637 0.2775
-5.250 -0.4525 0.02317 0.01614 -0.0458 0.9597 0.3921
-5.000 -0.4283 0.02368 0.01766 -0.0438 0.9549 0.5553
-4.750 -0.3960 0.02514 0.01911 -0.0430 0.9503 0.6129
-4.500 -0.3793 0.02625 0.02014 -0.0401 0.9436 0.6398
-4.250 -0.3526 0.02743 0.02121 -0.0389 0.9388 0.6633
-4.000 -0.3254 0.02895 0.02268 -0.0366 0.9348 0.6780
-3.750 -0.3154 0.02996 0.02366 -0.0321 0.9279 0.6899
-3.500 -0.2931 0.03084 0.02447 -0.0301 0.9225 0.7052
-3.250 -0.2631 0.03170 0.02523 -0.0297 0.9184 0.7217
-3.000 -0.2512 0.03273 0.02626 -0.0247 0.9128 0.7302
-2.750 -0.2362 0.03330 0.02678 -0.0219 0.9067 0.7446
-2.500 -0.2106 0.03392 0.02733 -0.0210 0.9020 0.7609
-2.250 -0.1833 0.03471 0.02810 -0.0183 0.8983 0.7720
-2.000 -0.1790 0.03496 0.02832 -0.0145 0.8912 0.7841
-1.750 -0.1576 0.03524 0.02853 -0.0137 0.8855 0.7981
-1.500 -0.1312 0.03554 0.02881 -0.0117 0.8811 0.8088
-1.250 -0.1123 0.03574 0.02897 -0.0100 0.8753 0.8215
-1.000 -0.0999 0.03588 0.02907 -0.0080 0.8676 0.8349
-0.750 -0.0705 0.03588 0.02904 -0.0071 0.8625 0.8449
-0.500 -0.0404 0.03588 0.02899 -0.0080 0.8571 0.8543
-0.250 -0.0335 0.03588 0.02898 -0.0051 0.8482 0.8616
0.000 0.0048 0.03578 0.02883 -0.0078 0.8425 0.8680
0.250 0.0253 0.03571 0.02874 -0.0070 0.8346 0.8728
0.500 0.0499 0.03561 0.02862 -0.0071 0.8260 0.8782
0.750 0.0996 0.03534 0.02831 -0.0110 0.8210 0.8825
1.000 0.1059 0.03541 0.02839 -0.0085 0.8087 0.8876
1.250 0.1567 0.03486 0.02781 -0.0118 0.8024 0.8912
1.500 0.1720 0.03485 0.02782 -0.0105 0.7896 0.8958
1.750 0.2377 0.03371 0.02665 -0.0155 0.7826 0.8989
2.000 0.2582 0.03331 0.02627 -0.0143 0.7682 0.9028
2.250 0.3384 0.03133 0.02427 -0.0204 0.7631 0.9043
2.500 0.3553 0.03106 0.02403 -0.0187 0.7490 0.9088
2.750 0.4180 0.02927 0.02224 -0.0224 0.7439 0.9116
3.000 0.4383 0.02885 0.02185 -0.0211 0.7302 0.9154
3.250 0.4973 0.02693 0.01993 -0.0241 0.7239 0.9174
3.500 0.5213 0.02625 0.01929 -0.0229 0.7093 0.9214
3.750 0.5571 0.02514 0.01821 -0.0231 0.6970 0.9251
4.000 0.6013 0.02370 0.01674 -0.0244 0.6850 0.9281
4.250 0.6286 0.02284 0.01591 -0.0236 0.6671 0.9315
4.500 0.6604 0.02185 0.01493 -0.0233 0.6469 0.9353
4.750 0.6772 0.02134 0.01449 -0.0211 0.6196 0.9399
5.000 0.6995 0.02069 0.01380 -0.0196 0.5846 0.9436
5.250 0.7203 0.02017 0.01309 -0.0177 0.5269 0.9474
5.500 0.7329 0.02027 0.01259 -0.0146 0.4383 0.9524
5.750 0.7382 0.02113 0.01281 -0.0113 0.3696 0.9576
6.000 0.7506 0.02204 0.01332 -0.0094 0.3234 0.9623
6.250 0.7680 0.02291 0.01384 -0.0085 0.2941 0.9669
6.500 0.7919 0.02371 0.01444 -0.0086 0.2719 0.9713
6.750 0.8210 0.02454 0.01509 -0.0096 0.2549 0.9761
7.000 0.8529 0.02544 0.01576 -0.0111 0.2414 0.9811
7.250 0.8862 0.02621 0.01655 -0.0129 0.2297 0.9858
7.500 0.9230 0.02721 0.01746 -0.0153 0.2208 0.9905
7.750 0.9577 0.02808 0.01834 -0.0173 0.2131 0.9961
8.000 0.9929 0.02922 0.01927 -0.0193 0.2068 1.0000
8.250 1.0129 0.02998 0.02022 -0.0188 0.2020 1.0000
8.500 1.0399 0.03092 0.02122 -0.0196 0.1969 1.0000
8.750 1.0731 0.03209 0.02230 -0.0214 0.1924 1.0000
9.000 1.1063 0.03363 0.02387 -0.0232 0.1888 1.0000
9.250 1.1308 0.03483 0.02531 -0.0237 0.1854 1.0000
9.500 1.1573 0.03612 0.02676 -0.0246 0.1817 1.0000
9.750 1.1855 0.03746 0.02817 -0.0258 0.1783 1.0000
10.000 1.2186 0.03915 0.02982 -0.0277 0.1753 1.0000
10.250 1.2442 0.04123 0.03208 -0.0287 0.1728 1.0000
10.500 1.2604 0.04295 0.03416 -0.0283 0.1704 1.0000
10.750 1.2772 0.04487 0.03636 -0.0282 0.1679 1.0000
11.000 1.2952 0.04685 0.03858 -0.0282 0.1655 1.0000
11.250 1.3177 0.04869 0.04052 -0.0288 0.1629 1.0000
11.500 1.3427 0.05064 0.04249 -0.0299 0.1603 1.0000
11.750 1.3622 0.05376 0.04571 -0.0306 0.1581 1.0000
12.000 1.3552 0.05643 0.04882 -0.0280 0.1568 1.0000
12.250 1.3409 0.05943 0.05220 -0.0249 0.1557 1.0000
12.500 1.3195 0.06291 0.05604 -0.0217 0.1547 1.0000
12.750 1.2910 0.06720 0.06066 -0.0191 0.1540 1.0000
13.000 1.2513 0.07282 0.06661 -0.0173 0.1538 1.0000
13.250 1.1932 0.08103 0.07517 -0.0170 0.1544 1.0000
13.500 1.1068 0.09462 0.08911 -0.0205 0.1563 1.0000
13.750 1.0321 0.11124 0.10592 -0.0276 0.1580 1.0000
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Polar data table (+)
Polar graphs
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