NASA/LANGLEY MS(1)-0313 AIRFOIL (ms313-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: NASA/LANGLEY MS(1)-0313 AIRFOIL (ms313-il) Reynolds number: 200,000 Max Cl/Cd: 55.55 at α=3.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ms313-il-200000.txt Download as CSV file: xf-ms313-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 -0.3624 0.09786 0.09436 -0.0427 1.0000 0.0737
-10.750 -0.5235 0.08941 0.08577 -0.0493 1.0000 0.0696
-10.500 -0.5066 0.08917 0.08554 -0.0459 1.0000 0.0706
-10.250 -0.5009 0.08635 0.08275 -0.0462 1.0000 0.0721
-10.000 -0.5099 0.08019 0.07663 -0.0506 1.0000 0.0736
-9.750 -0.5424 0.07206 0.06849 -0.0570 1.0000 0.0739
-9.500 -0.5850 0.06849 0.06494 -0.0554 1.0000 0.0734
-9.250 -0.6290 0.06692 0.06338 -0.0500 1.0000 0.0728
-9.000 -0.6562 0.06498 0.06139 -0.0459 1.0000 0.0731
-8.750 -0.7239 0.04782 0.04292 -0.0451 0.9974 0.0471
-8.500 -0.7044 0.04205 0.03669 -0.0479 0.9941 0.0454
-8.250 -0.6857 0.03503 0.02872 -0.0496 0.9904 0.0428
-8.000 -0.6578 0.03143 0.02455 -0.0511 0.9874 0.0426
-7.750 -0.6258 0.02941 0.02233 -0.0529 0.9850 0.0434
-7.500 -0.5915 0.02771 0.02045 -0.0549 0.9831 0.0448
-7.250 -0.5615 0.02642 0.01892 -0.0558 0.9793 0.0470
-7.000 -0.5289 0.02528 0.01746 -0.0570 0.9759 0.0486
-6.750 -0.4974 0.02331 0.01547 -0.0582 0.9737 0.0505
-6.500 -0.4628 0.02237 0.01452 -0.0600 0.9717 0.0533
-6.250 -0.4261 0.02165 0.01368 -0.0620 0.9700 0.0570
-6.000 -0.4005 0.02050 0.01256 -0.0619 0.9655 0.0600
-5.750 -0.3688 0.01977 0.01188 -0.0631 0.9620 0.0643
-5.500 -0.3346 0.01895 0.01106 -0.0648 0.9595 0.0704
-5.250 -0.2985 0.01827 0.01041 -0.0669 0.9575 0.0781
-5.000 -0.2608 0.01747 0.00969 -0.0695 0.9559 0.0900
-4.750 -0.2324 0.01687 0.00915 -0.0703 0.9514 0.1068
-4.500 -0.1986 0.01574 0.00844 -0.0727 0.9480 0.1650
-4.250 -0.1582 0.01350 0.00795 -0.0777 0.9470 0.5140
-4.000 -0.1245 0.01358 0.00832 -0.0785 0.9442 0.6134
-3.750 -0.0883 0.01385 0.00859 -0.0797 0.9420 0.6531
-3.500 -0.0522 0.01417 0.00887 -0.0808 0.9400 0.6789
-3.250 -0.0325 0.01461 0.00930 -0.0789 0.9335 0.6955
-3.000 -0.0031 0.01496 0.00962 -0.0787 0.9296 0.7113
-2.750 0.0291 0.01527 0.00990 -0.0790 0.9267 0.7264
-2.500 0.0588 0.01572 0.01036 -0.0783 0.9242 0.7417
-2.250 0.0725 0.01632 0.01101 -0.0746 0.9173 0.7533
-2.000 0.0995 0.01655 0.01122 -0.0739 0.9131 0.7635
-1.750 0.1305 0.01664 0.01129 -0.0741 0.9100 0.7711
-1.500 0.1635 0.01668 0.01129 -0.0747 0.9075 0.7792
-1.250 0.1802 0.01700 0.01163 -0.0723 0.8999 0.7873
-1.000 0.2109 0.01697 0.01158 -0.0727 0.8955 0.7950
-0.750 0.2434 0.01680 0.01139 -0.0729 0.8917 0.7994
-0.500 0.2702 0.01670 0.01128 -0.0725 0.8830 0.8049
-0.250 0.3079 0.01606 0.01057 -0.0734 0.8750 0.8098
0.000 0.3319 0.01565 0.01015 -0.0715 0.8623 0.8134
0.250 0.3595 0.01525 0.00972 -0.0704 0.8521 0.8178
0.500 0.3899 0.01493 0.00936 -0.0705 0.8431 0.8228
0.750 0.4170 0.01470 0.00913 -0.0700 0.8336 0.8269
1.000 0.4436 0.01440 0.00882 -0.0690 0.8251 0.8307
1.250 0.4702 0.01421 0.00865 -0.0684 0.8142 0.8351
1.500 0.5012 0.01394 0.00834 -0.0687 0.8041 0.8399
1.750 0.5271 0.01366 0.00806 -0.0677 0.7923 0.8436
2.000 0.5526 0.01344 0.00788 -0.0668 0.7788 0.8476
2.250 0.5803 0.01323 0.00767 -0.0664 0.7641 0.8520
2.500 0.6101 0.01304 0.00747 -0.0666 0.7469 0.8568
2.750 0.6344 0.01281 0.00722 -0.0653 0.7265 0.8605
3.000 0.6597 0.01265 0.00705 -0.0644 0.6975 0.8647
3.250 0.6862 0.01257 0.00686 -0.0638 0.6526 0.8695
3.500 0.7082 0.01275 0.00663 -0.0622 0.5621 0.8739
3.750 0.7206 0.01364 0.00680 -0.0592 0.4371 0.8783
4.000 0.7353 0.01470 0.00727 -0.0573 0.3370 0.8835
4.250 0.7538 0.01559 0.00774 -0.0562 0.2714 0.8886
4.500 0.7712 0.01623 0.00814 -0.0545 0.2361 0.8933
4.750 0.7928 0.01679 0.00857 -0.0537 0.2128 0.8986
5.000 0.8153 0.01733 0.00901 -0.0530 0.1972 0.9039
5.250 0.8342 0.01783 0.00942 -0.0515 0.1865 0.9095
5.500 0.8575 0.01830 0.00986 -0.0510 0.1773 0.9154
5.750 0.8782 0.01881 0.01033 -0.0499 0.1701 0.9212
6.000 0.9000 0.01918 0.01072 -0.0489 0.1636 0.9282
6.250 0.9209 0.01987 0.01130 -0.0479 0.1578 0.9351
6.500 0.9435 0.02019 0.01172 -0.0471 0.1534 0.9430
6.750 0.9652 0.02058 0.01215 -0.0461 0.1492 0.9519
7.000 0.9875 0.02109 0.01263 -0.0453 0.1456 0.9632
7.250 1.0146 0.02192 0.01343 -0.0456 0.1420 0.9779
7.500 1.0441 0.02244 0.01408 -0.0464 0.1385 1.0000
7.750 1.0744 0.02314 0.01482 -0.0476 0.1348 1.0000
8.000 1.1051 0.02395 0.01562 -0.0488 0.1316 1.0000
8.250 1.1384 0.02539 0.01699 -0.0505 0.1284 1.0000
8.500 1.1671 0.02615 0.01791 -0.0513 0.1261 1.0000
8.750 1.1953 0.02695 0.01885 -0.0519 0.1232 1.0000
9.000 1.2230 0.02780 0.01979 -0.0526 0.1203 1.0000
9.250 1.2504 0.02864 0.02064 -0.0532 0.1174 1.0000
9.500 1.2810 0.03050 0.02244 -0.0546 0.1140 1.0000
9.750 1.3034 0.03117 0.02334 -0.0542 0.1119 1.0000
10.000 1.3260 0.03207 0.02443 -0.0539 0.1092 1.0000
10.250 1.3481 0.03296 0.02545 -0.0536 0.1064 1.0000
10.500 1.3708 0.03380 0.02630 -0.0534 0.1038 1.0000
10.750 1.3977 0.03588 0.02832 -0.0542 0.1007 1.0000
11.000 1.4120 0.03674 0.02947 -0.0526 0.0987 1.0000
11.250 1.4267 0.03777 0.03074 -0.0512 0.0961 1.0000
11.500 1.4418 0.03872 0.03183 -0.0499 0.0935 1.0000
11.750 1.4585 0.03950 0.03263 -0.0488 0.0911 1.0000
12.000 1.4816 0.04171 0.03476 -0.0492 0.0881 1.0000
12.250 1.4836 0.04270 0.03607 -0.0460 0.0864 1.0000
12.500 1.4844 0.04400 0.03763 -0.0428 0.0843 1.0000
12.750 1.4873 0.04524 0.03904 -0.0401 0.0822 1.0000
13.000 1.4921 0.04629 0.04018 -0.0378 0.0802 1.0000
13.250 1.5049 0.04709 0.04093 -0.0365 0.0783 1.0000
13.500 1.5105 0.04959 0.04352 -0.0351 0.0762 1.0000
13.750 1.4980 0.05182 0.04606 -0.0318 0.0749 1.0000
14.000 1.4866 0.05445 0.04898 -0.0292 0.0734 1.0000
14.250 1.4788 0.05700 0.05174 -0.0274 0.0718 1.0000
14.500 1.4733 0.05944 0.05433 -0.0260 0.0703 1.0000
14.750 1.4748 0.06123 0.05619 -0.0252 0.0688 1.0000
15.000 1.4891 0.06212 0.05698 -0.0247 0.0671 1.0000
15.250 1.4774 0.06617 0.06118 -0.0239 0.0659 1.0000
15.500 1.4509 0.07129 0.06663 -0.0236 0.0653 1.0000
15.750 1.4200 0.07759 0.07325 -0.0245 0.0648 1.0000
16.000 1.3829 0.08544 0.08141 -0.0269 0.0645 1.0000
16.250 1.3344 0.09630 0.09257 -0.0321 0.0646 1.0000
16.500 1.2567 0.11486 0.11147 -0.0436 0.0655 1.0000
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Polar data table (+)
Polar graphs
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