NASA/LANGLEY MS(1)-0317 AIRFOIL (ms317-il) Xfoil prediction polar at RE=50,000 Ncrit=9
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Airfoil: NASA/LANGLEY MS(1)-0317 AIRFOIL (ms317-il) Reynolds number: 50,000 Max Cl/Cd: 28.42 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ms317-il-50000.txt Download as CSV file: xf-ms317-il-50000.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 = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.5831 0.08341 0.07579 -0.0577 1.0000 0.1672
-10.500 -0.6039 0.07822 0.07065 -0.0577 1.0000 0.1655
-10.250 -0.6405 0.07384 0.06632 -0.0558 1.0000 0.1633
-10.000 -0.6899 0.07037 0.06287 -0.0516 1.0000 0.1604
-9.750 -0.7433 0.06662 0.05897 -0.0468 1.0000 0.1572
-9.500 -0.7911 0.06257 0.05451 -0.0423 1.0000 0.1543
-9.250 -0.8027 0.05947 0.05119 -0.0395 1.0000 0.1546
-9.000 -0.8012 0.05705 0.04869 -0.0373 1.0000 0.1569
-8.750 -0.8016 0.05447 0.04591 -0.0352 1.0000 0.1593
-8.500 -0.8004 0.05169 0.04283 -0.0334 1.0000 0.1619
-8.250 -0.7958 0.04882 0.03954 -0.0320 1.0000 0.1647
-8.000 -0.7878 0.04609 0.03624 -0.0309 1.0000 0.1682
-7.750 -0.7712 0.04420 0.03453 -0.0297 1.0000 0.1742
-7.500 -0.7557 0.04225 0.03229 -0.0289 1.0000 0.1809
-7.250 -0.7383 0.04028 0.03016 -0.0281 1.0000 0.1885
-7.000 -0.7194 0.03878 0.02853 -0.0273 1.0000 0.1987
-6.750 -0.6998 0.03729 0.02707 -0.0264 1.0000 0.2099
-6.500 -0.6795 0.03591 0.02564 -0.0256 1.0000 0.2240
-6.250 -0.6593 0.03472 0.02449 -0.0246 1.0000 0.2412
-6.000 -0.6395 0.03364 0.02357 -0.0235 1.0000 0.2618
-5.750 -0.6198 0.03259 0.02269 -0.0223 1.0000 0.2881
-5.500 -0.6008 0.03148 0.02191 -0.0209 1.0000 0.3225
-5.250 -0.5824 0.03019 0.02122 -0.0196 1.0000 0.3759
-5.000 -0.5698 0.02956 0.02176 -0.0157 1.0000 0.4703
-4.750 -0.5665 0.03173 0.02457 -0.0067 1.0000 0.5618
-4.500 -0.5588 0.03436 0.02715 0.0006 1.0000 0.6267
-4.250 -0.5516 0.03672 0.02942 0.0081 1.0000 0.6650
-4.000 -0.5442 0.03875 0.03135 0.0155 1.0000 0.6943
-3.750 -0.5353 0.04012 0.03259 0.0216 1.0000 0.7247
-3.500 -0.5249 0.04133 0.03369 0.0278 1.0000 0.7513
-3.250 -0.5148 0.04191 0.03414 0.0325 1.0000 0.7809
-3.000 -0.4979 0.04259 0.03469 0.0372 1.0000 0.8075
-2.750 -0.4820 0.04279 0.03475 0.0406 1.0000 0.8366
-2.500 -0.4525 0.04307 0.03486 0.0418 1.0000 0.8664
-2.250 -0.3965 0.04351 0.03509 0.0379 1.0000 0.8975
-2.000 -0.3080 0.04414 0.03544 0.0270 1.0000 0.9290
-1.750 -0.2210 0.04442 0.03548 0.0151 1.0000 0.9560
-1.500 -0.1480 0.04446 0.03536 0.0046 1.0000 0.9757
-1.250 -0.0929 0.04454 0.03531 -0.0031 1.0000 0.9906
-1.000 -0.0525 0.04467 0.03535 -0.0083 1.0000 1.0000
-0.750 -0.0507 0.04459 0.03524 -0.0063 1.0000 1.0000
-0.500 -0.0488 0.04453 0.03515 -0.0043 1.0000 1.0000
-0.250 -0.0469 0.04449 0.03509 -0.0023 1.0000 1.0000
0.000 -0.0450 0.04447 0.03506 -0.0003 1.0000 1.0000
0.250 -0.0432 0.04448 0.03505 0.0017 1.0000 1.0000
0.500 -0.0415 0.04450 0.03506 0.0037 1.0000 1.0000
0.750 -0.0399 0.04454 0.03510 0.0057 1.0000 1.0000
1.000 0.0036 0.04533 0.03587 -0.0001 0.9869 1.0000
1.250 0.0442 0.04614 0.03667 -0.0052 0.9717 1.0000
1.500 0.0831 0.04693 0.03746 -0.0097 0.9549 1.0000
1.750 0.1228 0.04773 0.03827 -0.0140 0.9365 1.0000
2.000 0.1669 0.04859 0.03913 -0.0186 0.9166 1.0000
2.250 0.1971 0.04907 0.03964 -0.0207 0.8958 1.0000
2.500 0.2252 0.04946 0.04006 -0.0221 0.8736 1.0000
2.750 0.2567 0.04977 0.04041 -0.0236 0.8500 1.0000
3.000 0.2999 0.04991 0.04060 -0.0264 0.8250 1.0000
3.250 0.3649 0.04964 0.04038 -0.0316 0.7999 1.0000
3.500 0.3788 0.04950 0.04031 -0.0296 0.7749 1.0000
3.750 0.4153 0.04894 0.03982 -0.0301 0.7500 1.0000
4.000 0.4727 0.04762 0.03859 -0.0327 0.7262 1.0000
4.250 0.5612 0.04478 0.03591 -0.0382 0.7038 1.0000
4.500 0.5638 0.04424 0.03543 -0.0334 0.6774 1.0000
4.750 0.6510 0.03999 0.03136 -0.0371 0.6525 1.0000
5.000 0.7174 0.03584 0.02734 -0.0379 0.6226 1.0000
5.250 0.7715 0.03199 0.02350 -0.0370 0.5790 1.0000
5.500 0.8112 0.02944 0.02057 -0.0349 0.5154 1.0000
5.750 0.8283 0.02915 0.01970 -0.0315 0.4574 1.0000
6.000 0.8423 0.02973 0.01980 -0.0288 0.4154 1.0000
6.250 0.8596 0.03060 0.02030 -0.0270 0.3844 1.0000
6.500 0.8760 0.03155 0.02107 -0.0253 0.3613 1.0000
6.750 0.8947 0.03256 0.02193 -0.0242 0.3430 1.0000
7.000 0.9155 0.03364 0.02288 -0.0234 0.3278 1.0000
7.250 0.9441 0.03485 0.02388 -0.0239 0.3143 1.0000
7.500 0.9583 0.03617 0.02540 -0.0225 0.3043 1.0000
7.750 0.9892 0.03770 0.02680 -0.0236 0.2948 1.0000
8.000 1.0055 0.03931 0.02868 -0.0229 0.2867 1.0000
8.250 1.0400 0.04100 0.03019 -0.0247 0.2785 1.0000
8.500 1.0520 0.04309 0.03267 -0.0237 0.2732 1.0000
8.750 1.0695 0.04527 0.03510 -0.0236 0.2680 1.0000
9.000 1.0966 0.04731 0.03718 -0.0246 0.2626 1.0000
9.250 1.1144 0.04993 0.03997 -0.0248 0.2583 1.0000
9.500 1.1130 0.05300 0.04348 -0.0231 0.2554 1.0000
9.750 1.1090 0.05645 0.04732 -0.0216 0.2530 1.0000
10.000 1.0973 0.06048 0.05170 -0.0198 0.2517 1.0000
10.250 1.0665 0.06542 0.05698 -0.0171 0.2515 1.0000
10.500 0.9939 0.07427 0.06619 -0.0152 0.2540 1.0000
10.750 0.9049 0.08901 0.08114 -0.0190 0.2586 1.0000
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Polar data table (+)
Polar graphs
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