NASA/LANGLEY MS(1)-0313 AIRFOIL (ms313-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: NASA/LANGLEY MS(1)-0313 AIRFOIL (ms313-il) Reynolds number: 100,000 Max Cl/Cd: 39.46 at α=3.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ms313-il-100000-n5.txt Download as CSV file: xf-ms313-il-100000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.500 -0.5512 0.08856 0.08310 -0.0462 1.0000 0.0332
-11.250 -0.5908 0.07501 0.06947 -0.0563 1.0000 0.0325
-11.000 -0.6254 0.06676 0.06105 -0.0617 1.0000 0.0321
-10.750 -0.6540 0.06127 0.05540 -0.0636 1.0000 0.0319
-10.500 -0.6806 0.05753 0.05151 -0.0626 1.0000 0.0318
-10.250 -0.7025 0.05438 0.04820 -0.0603 1.0000 0.0318
-10.000 -0.7194 0.05154 0.04515 -0.0574 1.0000 0.0319
-9.750 -0.7321 0.04890 0.04228 -0.0542 1.0000 0.0320
-9.500 -0.7402 0.04640 0.03951 -0.0511 1.0000 0.0325
-9.250 -0.7440 0.04388 0.03665 -0.0484 1.0000 0.0332
-9.000 -0.7412 0.04099 0.03327 -0.0466 0.9993 0.0342
-8.750 -0.7172 0.03818 0.03007 -0.0483 0.9952 0.0353
-8.500 -0.6904 0.03628 0.02800 -0.0497 0.9914 0.0363
-8.250 -0.6628 0.03427 0.02575 -0.0510 0.9874 0.0374
-8.000 -0.6332 0.03231 0.02349 -0.0524 0.9840 0.0388
-7.750 -0.6040 0.03062 0.02137 -0.0534 0.9804 0.0410
-7.500 -0.5762 0.02934 0.02011 -0.0544 0.9764 0.0429
-7.250 -0.5458 0.02814 0.01881 -0.0555 0.9731 0.0449
-7.000 -0.5136 0.02688 0.01738 -0.0568 0.9705 0.0472
-6.750 -0.4856 0.02583 0.01627 -0.0574 0.9663 0.0500
-6.500 -0.4567 0.02498 0.01544 -0.0582 0.9621 0.0534
-6.250 -0.4256 0.02410 0.01445 -0.0592 0.9590 0.0571
-6.000 -0.3934 0.02320 0.01360 -0.0608 0.9565 0.0617
-5.750 -0.3635 0.02253 0.01286 -0.0617 0.9528 0.0677
-5.500 -0.3359 0.02179 0.01218 -0.0623 0.9481 0.0742
-5.250 -0.3042 0.02109 0.01149 -0.0637 0.9447 0.0841
-5.000 -0.2713 0.02041 0.01087 -0.0653 0.9420 0.0988
-4.750 -0.2373 0.01968 0.01027 -0.0672 0.9397 0.1254
-4.500 -0.2123 0.01892 0.00984 -0.0676 0.9342 0.1798
-4.250 -0.1821 0.01765 0.00934 -0.0696 0.9305 0.3264
-4.000 -0.1540 0.01691 0.00960 -0.0699 0.9274 0.5203
-3.750 -0.1241 0.01713 0.00999 -0.0696 0.9246 0.5995
-3.500 -0.0976 0.01743 0.01024 -0.0690 0.9198 0.6394
-3.250 -0.0722 0.01778 0.01056 -0.0680 0.9147 0.6673
-3.000 -0.0442 0.01820 0.01093 -0.0673 0.9110 0.6948
-2.750 -0.0173 0.01867 0.01138 -0.0660 0.9079 0.7162
-2.500 0.0052 0.01898 0.01164 -0.0645 0.9024 0.7304
-2.250 0.0324 0.01914 0.01170 -0.0644 0.8976 0.7422
-2.000 0.0586 0.01932 0.01186 -0.0634 0.8938 0.7509
-1.750 0.0906 0.01938 0.01184 -0.0640 0.8910 0.7615
-1.500 0.1117 0.01955 0.01199 -0.0626 0.8849 0.7678
-1.250 0.1418 0.01955 0.01193 -0.0634 0.8801 0.7747
-1.000 0.1724 0.01953 0.01187 -0.0639 0.8764 0.7792
-0.750 0.2047 0.01947 0.01178 -0.0646 0.8735 0.7838
-0.500 0.2277 0.01960 0.01189 -0.0641 0.8657 0.7895
-0.250 0.2591 0.01954 0.01181 -0.0648 0.8608 0.7943
0.000 0.2918 0.01939 0.01165 -0.0653 0.8569 0.7981
0.250 0.3154 0.01939 0.01166 -0.0645 0.8466 0.8030
0.500 0.3523 0.01900 0.01123 -0.0657 0.8389 0.8080
0.750 0.3801 0.01858 0.01081 -0.0647 0.8250 0.8117
1.000 0.4070 0.01818 0.01040 -0.0636 0.8095 0.8157
1.250 0.4347 0.01786 0.01006 -0.0629 0.7944 0.8205
1.500 0.4633 0.01762 0.00983 -0.0627 0.7802 0.8254
1.750 0.4885 0.01740 0.00963 -0.0616 0.7655 0.8291
2.000 0.5148 0.01719 0.00945 -0.0608 0.7493 0.8336
2.250 0.5426 0.01701 0.00928 -0.0605 0.7303 0.8386
2.500 0.5696 0.01681 0.00907 -0.0598 0.7087 0.8428
2.750 0.5932 0.01669 0.00898 -0.0586 0.6804 0.8472
3.000 0.6192 0.01657 0.00880 -0.0578 0.6399 0.8522
3.250 0.6467 0.01651 0.00846 -0.0571 0.5703 0.8570
3.500 0.6661 0.01688 0.00826 -0.0549 0.4756 0.8612
3.750 0.6835 0.01763 0.00851 -0.0531 0.3936 0.8665
4.250 0.7219 0.01900 0.00927 -0.0506 0.2871 0.8769
4.500 0.7423 0.01960 0.00967 -0.0496 0.2533 0.8826
4.750 0.7645 0.02015 0.01010 -0.0490 0.2280 0.8885
5.000 0.7846 0.02064 0.01049 -0.0478 0.2101 0.8943
5.250 0.8068 0.02115 0.01095 -0.0471 0.1965 0.9006
5.500 0.8273 0.02165 0.01140 -0.0460 0.1862 0.9071
5.750 0.8485 0.02214 0.01189 -0.0451 0.1768 0.9147
6.000 0.8691 0.02263 0.01237 -0.0440 0.1691 0.9225
6.250 0.8906 0.02313 0.01288 -0.0432 0.1619 0.9313
6.500 0.9106 0.02367 0.01341 -0.0421 0.1564 0.9419
6.750 0.9336 0.02417 0.01398 -0.0416 0.1512 0.9555
7.000 0.9578 0.02474 0.01458 -0.0414 0.1466 0.9808
7.250 0.9838 0.02555 0.01533 -0.0419 0.1425 1.0000
7.500 1.0114 0.02629 0.01617 -0.0425 0.1381 1.0000
7.750 1.0381 0.02707 0.01700 -0.0429 0.1339 1.0000
8.000 1.0642 0.02792 0.01785 -0.0433 0.1304 1.0000
8.250 1.0913 0.02894 0.01882 -0.0439 0.1277 1.0000
8.500 1.1180 0.02984 0.01989 -0.0442 0.1248 1.0000
8.750 1.1436 0.03078 0.02095 -0.0445 0.1216 1.0000
9.000 1.1683 0.03172 0.02196 -0.0446 0.1186 1.0000
9.250 1.1927 0.03270 0.02294 -0.0447 0.1160 1.0000
9.500 1.2187 0.03393 0.02416 -0.0451 0.1137 1.0000
9.750 1.2407 0.03506 0.02557 -0.0447 0.1113 1.0000
10.000 1.2616 0.03622 0.02694 -0.0442 0.1085 1.0000
10.250 1.2814 0.03733 0.02818 -0.0437 0.1057 1.0000
10.500 1.3012 0.03841 0.02932 -0.0432 0.1034 1.0000
10.750 1.3227 0.03958 0.03047 -0.0430 0.1011 1.0000
11.000 1.3366 0.04103 0.03219 -0.0417 0.0987 1.0000
11.250 1.3479 0.04251 0.03397 -0.0401 0.0962 1.0000
11.500 1.3573 0.04387 0.03554 -0.0382 0.0939 1.0000
11.750 1.3673 0.04511 0.03690 -0.0366 0.0917 1.0000
12.000 1.3795 0.04629 0.03814 -0.0353 0.0898 1.0000
12.250 1.3943 0.04769 0.03952 -0.0344 0.0880 1.0000
12.500 1.3900 0.04990 0.04214 -0.0316 0.0862 1.0000
12.750 1.3859 0.05226 0.04483 -0.0293 0.0842 1.0000
13.000 1.3829 0.05460 0.04744 -0.0275 0.0824 1.0000
13.250 1.3811 0.05687 0.04990 -0.0259 0.0807 1.0000
13.500 1.3820 0.05892 0.05207 -0.0248 0.0791 1.0000
13.750 1.3885 0.06055 0.05374 -0.0239 0.0776 1.0000
14.000 1.3896 0.06289 0.05615 -0.0231 0.0762 1.0000
14.250 1.3656 0.06774 0.06141 -0.0223 0.0752 1.0000
14.500 1.3383 0.07343 0.06747 -0.0225 0.0742 1.0000
14.750 1.3059 0.08036 0.07474 -0.0240 0.0734 1.0000
15.000 1.2620 0.08981 0.08452 -0.0278 0.0731 1.0000
|
Polar data table (+)
Polar graphs
<< Back to NASA/LANGLEY MS(1)-0313 AIRFOIL (ms313-il)