NASA/LANGLEY MS(1)-0317 AIRFOIL (ms317-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: NASA/LANGLEY MS(1)-0317 AIRFOIL (ms317-il) Reynolds number: 50,000 Max Cl/Cd: 24.19 at α=9.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ms317-il-50000-n5.txt Download as CSV file: xf-ms317-il-50000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.000 -0.5564 0.10153 0.09323 -0.0528 1.0000 0.0778
-12.750 -0.6152 0.08684 0.07840 -0.0619 1.0000 0.0770
-12.500 -0.6641 0.07713 0.06850 -0.0669 1.0000 0.0763
-12.250 -0.6998 0.07067 0.06182 -0.0689 1.0000 0.0763
-12.000 -0.7270 0.06592 0.05686 -0.0691 1.0000 0.0766
-11.750 -0.7498 0.06217 0.05291 -0.0680 1.0000 0.0771
-11.500 -0.7710 0.05919 0.04973 -0.0656 1.0000 0.0778
-11.250 -0.7912 0.05672 0.04707 -0.0623 1.0000 0.0785
-11.000 -0.8068 0.05431 0.04440 -0.0589 1.0000 0.0793
-10.750 -0.8088 0.05250 0.04251 -0.0562 1.0000 0.0805
-10.500 -0.8063 0.05117 0.04119 -0.0537 1.0000 0.0821
-10.250 -0.8071 0.04980 0.03973 -0.0507 1.0000 0.0839
-10.000 -0.8084 0.04830 0.03807 -0.0477 1.0000 0.0860
-9.750 -0.8091 0.04665 0.03614 -0.0447 1.0000 0.0883
-9.500 -0.8024 0.04534 0.03478 -0.0423 1.0000 0.0905
-9.250 -0.7941 0.04427 0.03371 -0.0401 1.0000 0.0931
-9.000 -0.7861 0.04309 0.03240 -0.0378 1.0000 0.0964
-8.750 -0.7765 0.04186 0.03096 -0.0357 1.0000 0.1002
-8.500 -0.7645 0.04098 0.03016 -0.0338 1.0000 0.1037
-8.250 -0.7493 0.03998 0.02905 -0.0324 0.9993 0.1087
-8.000 -0.7189 0.03890 0.02798 -0.0336 0.9947 0.1155
-7.750 -0.6884 0.03792 0.02684 -0.0345 0.9901 0.1243
-7.500 -0.6594 0.03707 0.02606 -0.0354 0.9852 0.1334
-7.250 -0.6289 0.03622 0.02524 -0.0366 0.9807 0.1448
-7.000 -0.6031 0.03539 0.02443 -0.0370 0.9750 0.1574
-6.750 -0.5756 0.03454 0.02364 -0.0379 0.9697 0.1729
-6.250 -0.5268 0.03277 0.02208 -0.0389 0.9584 0.2131
-6.000 -0.5008 0.03175 0.02128 -0.0401 0.9533 0.2430
-5.750 -0.4789 0.03069 0.02053 -0.0406 0.9478 0.2824
-5.500 -0.4593 0.02966 0.01996 -0.0405 0.9417 0.3391
-5.250 -0.4355 0.02937 0.02041 -0.0395 0.9371 0.4272
-5.000 -0.4103 0.03050 0.02197 -0.0364 0.9324 0.5051
-4.750 -0.3891 0.03127 0.02271 -0.0343 0.9256 0.5556
-4.500 -0.3602 0.03205 0.02333 -0.0339 0.9204 0.5945
-4.000 -0.3123 0.03354 0.02452 -0.0314 0.9088 0.6482
-3.750 -0.2869 0.03438 0.02524 -0.0299 0.9035 0.6685
-3.500 -0.2567 0.03513 0.02585 -0.0292 0.8995 0.6877
-3.250 -0.2377 0.03559 0.02621 -0.0273 0.8934 0.7044
-3.000 -0.2182 0.03600 0.02652 -0.0255 0.8870 0.7203
-2.750 -0.1907 0.03659 0.02703 -0.0240 0.8827 0.7328
-2.500 -0.1596 0.03690 0.02724 -0.0240 0.8792 0.7472
-2.250 -0.1508 0.03706 0.02733 -0.0212 0.8714 0.7613
-2.000 -0.1269 0.03732 0.02753 -0.0197 0.8659 0.7713
-1.750 -0.0975 0.03732 0.02742 -0.0202 0.8616 0.7826
-1.500 -0.0737 0.03738 0.02742 -0.0196 0.8564 0.7911
-1.250 -0.0614 0.03735 0.02734 -0.0179 0.8485 0.7999
-1.000 -0.0321 0.03731 0.02723 -0.0183 0.8437 0.8056
-0.750 0.0025 0.03720 0.02704 -0.0201 0.8400 0.8121
-0.500 0.0085 0.03729 0.02710 -0.0175 0.8308 0.8188
-0.250 0.0356 0.03726 0.02704 -0.0177 0.8251 0.8238
0.000 0.0718 0.03715 0.02687 -0.0196 0.8209 0.8290
0.250 0.0807 0.03729 0.02700 -0.0177 0.8110 0.8353
0.500 0.1102 0.03722 0.02692 -0.0182 0.8048 0.8394
0.750 0.1493 0.03707 0.02673 -0.0203 0.8006 0.8436
1.000 0.1551 0.03732 0.02700 -0.0178 0.7890 0.8496
1.250 0.1919 0.03715 0.02682 -0.0195 0.7832 0.8536
1.500 0.2073 0.03728 0.02697 -0.0180 0.7726 0.8581
1.750 0.2413 0.03708 0.02678 -0.0191 0.7650 0.8622
2.000 0.2642 0.03709 0.02681 -0.0189 0.7544 0.8671
2.250 0.2998 0.03669 0.02644 -0.0198 0.7453 0.8707
2.500 0.3213 0.03652 0.02631 -0.0188 0.7323 0.8750
2.750 0.3688 0.03550 0.02531 -0.0206 0.7235 0.8784
3.000 0.3901 0.03521 0.02506 -0.0195 0.7076 0.8831
3.250 0.4156 0.03468 0.02459 -0.0186 0.6923 0.8869
3.500 0.4462 0.03391 0.02386 -0.0181 0.6779 0.8907
3.750 0.4866 0.03272 0.02270 -0.0186 0.6653 0.8944
4.000 0.5097 0.03225 0.02230 -0.0175 0.6477 0.8992
4.250 0.5330 0.03168 0.02180 -0.0162 0.6290 0.9033
4.500 0.5510 0.03133 0.02153 -0.0144 0.6074 0.9079
4.750 0.5672 0.03113 0.02140 -0.0125 0.5825 0.9132
5.000 0.5922 0.03050 0.02081 -0.0114 0.5555 0.9180
5.250 0.6126 0.03017 0.02048 -0.0098 0.5215 0.9233
5.500 0.6403 0.02961 0.01978 -0.0089 0.4790 0.9281
5.750 0.6678 0.02921 0.01903 -0.0079 0.4282 0.9328
6.000 0.6865 0.02953 0.01898 -0.0065 0.3817 0.9386
6.250 0.7014 0.03027 0.01941 -0.0051 0.3443 0.9450
6.500 0.7160 0.03115 0.02002 -0.0040 0.3151 0.9517
6.750 0.7327 0.03207 0.02079 -0.0034 0.2915 0.9586
7.000 0.7513 0.03299 0.02157 -0.0031 0.2727 0.9660
7.250 0.7718 0.03389 0.02236 -0.0032 0.2572 0.9748
7.500 0.7925 0.03468 0.02309 -0.0032 0.2441 0.9886
7.750 0.8146 0.03544 0.02385 -0.0033 0.2330 1.0000
8.000 0.8412 0.03636 0.02462 -0.0041 0.2237 1.0000
8.250 0.8688 0.03729 0.02564 -0.0050 0.2142 1.0000
8.500 0.9009 0.03814 0.02633 -0.0062 0.2069 1.0000
8.750 0.9315 0.03915 0.02752 -0.0074 0.1999 1.0000
9.000 0.9632 0.04013 0.02848 -0.0087 0.1937 1.0000
9.250 0.9965 0.04119 0.02951 -0.0102 0.1883 1.0000
9.500 1.0230 0.04250 0.03101 -0.0111 0.1830 1.0000
9.750 1.0523 0.04375 0.03233 -0.0123 0.1785 1.0000
10.000 1.0876 0.04497 0.03347 -0.0141 0.1747 1.0000
10.250 1.1104 0.04664 0.03535 -0.0147 0.1712 1.0000
10.500 1.1282 0.04844 0.03740 -0.0148 0.1676 1.0000
10.750 1.1475 0.05017 0.03928 -0.0151 0.1642 1.0000
11.000 1.1705 0.05181 0.04099 -0.0157 0.1613 1.0000
11.250 1.2009 0.05341 0.04255 -0.0170 0.1587 1.0000
11.500 1.2047 0.05592 0.04539 -0.0161 0.1566 1.0000
11.750 1.2027 0.05874 0.04856 -0.0149 0.1544 1.0000
12.000 1.1999 0.06172 0.05183 -0.0139 0.1523 1.0000
12.250 1.1960 0.06486 0.05521 -0.0132 0.1503 1.0000
12.500 1.1925 0.06809 0.05865 -0.0128 0.1484 1.0000
12.750 1.1901 0.07137 0.06210 -0.0125 0.1468 1.0000
13.000 1.1953 0.07417 0.06500 -0.0126 0.1451 1.0000
13.250 1.1979 0.07734 0.06825 -0.0127 0.1435 1.0000
13.500 1.1453 0.08544 0.07677 -0.0136 0.1430 1.0000
13.750 1.0483 0.10112 0.09292 -0.0196 0.1429 1.0000
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Polar data table (+)
Polar graphs
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