NASA/LANGLEY MS(1)-0313 AIRFOIL (ms313-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: NASA/LANGLEY MS(1)-0313 AIRFOIL (ms313-il) Reynolds number: 1,000,000 Max Cl/Cd: 87.09 at α=8.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ms313-il-1000000-n5.txt Download as CSV file: xf-ms313-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-18.250 -0.9770 0.11413 0.11160 -0.0215 1.0000 0.0086
-18.000 -1.0483 0.09596 0.09317 -0.0314 1.0000 0.0084
-17.750 -1.1105 0.07973 0.07670 -0.0410 1.0000 0.0084
-17.500 -1.1454 0.06904 0.06579 -0.0478 1.0000 0.0084
-17.250 -1.1673 0.06138 0.05797 -0.0526 1.0000 0.0084
-17.000 -1.1816 0.05553 0.05196 -0.0560 1.0000 0.0084
-16.750 -1.1915 0.05080 0.04709 -0.0584 1.0000 0.0084
-16.500 -1.1976 0.04683 0.04300 -0.0602 1.0000 0.0084
-16.250 -1.2043 0.04303 0.03908 -0.0617 1.0000 0.0085
-16.000 -1.2086 0.03969 0.03562 -0.0627 1.0000 0.0086
-15.750 -1.2093 0.03690 0.03272 -0.0633 1.0000 0.0087
-15.500 -1.2071 0.03450 0.03023 -0.0636 1.0000 0.0088
-15.250 -1.2022 0.03245 0.02809 -0.0638 1.0000 0.0089
-15.000 -1.1952 0.03065 0.02621 -0.0637 1.0000 0.0089
-14.750 -1.1864 0.02907 0.02456 -0.0635 1.0000 0.0091
-14.500 -1.1764 0.02766 0.02307 -0.0632 1.0000 0.0092
-14.250 -1.1654 0.02639 0.02173 -0.0628 1.0000 0.0093
-14.000 -1.1545 0.02522 0.02050 -0.0621 1.0000 0.0094
-13.750 -1.1441 0.02417 0.01939 -0.0612 1.0000 0.0095
-13.500 -1.1293 0.02321 0.01837 -0.0608 1.0000 0.0096
-13.250 -1.1121 0.02237 0.01747 -0.0604 1.0000 0.0098
-13.000 -1.0872 0.02154 0.01658 -0.0614 0.9925 0.0100
-12.750 -1.0610 0.02075 0.01572 -0.0624 0.9841 0.0102
-12.500 -1.0349 0.02001 0.01491 -0.0632 0.9751 0.0104
-12.250 -1.0096 0.01932 0.01415 -0.0637 0.9657 0.0106
-11.750 -0.9624 0.01814 0.01280 -0.0637 0.9450 0.0108
-11.500 -0.9399 0.01745 0.01204 -0.0634 0.9362 0.0111
-11.250 -0.9164 0.01685 0.01137 -0.0633 0.9279 0.0114
-11.000 -0.8920 0.01635 0.01082 -0.0632 0.9208 0.0117
-10.750 -0.8668 0.01588 0.01030 -0.0632 0.9135 0.0120
-10.500 -0.8415 0.01546 0.00981 -0.0632 0.9068 0.0123
-10.250 -0.8153 0.01504 0.00934 -0.0633 0.9007 0.0126
-10.000 -0.7890 0.01464 0.00889 -0.0634 0.8948 0.0129
-9.750 -0.7624 0.01426 0.00844 -0.0635 0.8897 0.0132
-9.500 -0.7352 0.01390 0.00803 -0.0638 0.8848 0.0135
-9.250 -0.7081 0.01348 0.00758 -0.0640 0.8796 0.0139
-9.000 -0.6810 0.01310 0.00716 -0.0642 0.8745 0.0145
-8.750 -0.6532 0.01277 0.00680 -0.0645 0.8700 0.0150
-8.500 -0.6251 0.01246 0.00647 -0.0648 0.8654 0.0156
-8.250 -0.5969 0.01218 0.00615 -0.0651 0.8610 0.0162
-7.750 -0.5400 0.01160 0.00551 -0.0658 0.8530 0.0176
-7.500 -0.5113 0.01132 0.00523 -0.0662 0.8486 0.0184
-7.250 -0.4824 0.01108 0.00496 -0.0666 0.8442 0.0193
-6.750 -0.4243 0.01060 0.00444 -0.0674 0.8369 0.0213
-6.500 -0.3949 0.01038 0.00422 -0.0679 0.8330 0.0228
-6.250 -0.3655 0.01018 0.00401 -0.0684 0.8290 0.0242
-6.000 -0.3361 0.00997 0.00378 -0.0688 0.8251 0.0259
-5.750 -0.3065 0.00978 0.00359 -0.0693 0.8216 0.0279
-5.500 -0.2767 0.00959 0.00340 -0.0698 0.8180 0.0301
-5.250 -0.2469 0.00940 0.00322 -0.0703 0.8144 0.0332
-5.000 -0.2171 0.00923 0.00306 -0.0708 0.8108 0.0364
-4.500 -0.1572 0.00890 0.00275 -0.0719 0.8039 0.0462
-4.250 -0.1270 0.00872 0.00261 -0.0725 0.8005 0.0543
-4.000 -0.0968 0.00855 0.00248 -0.0731 0.7970 0.0647
-3.750 -0.0666 0.00838 0.00235 -0.0737 0.7934 0.0788
-3.500 -0.0362 0.00817 0.00222 -0.0744 0.7902 0.1025
-3.250 -0.0053 0.00790 0.00210 -0.0752 0.7870 0.1388
-3.000 0.0258 0.00759 0.00197 -0.0762 0.7835 0.1890
-2.750 0.0572 0.00724 0.00185 -0.0772 0.7799 0.2530
-2.500 0.0885 0.00694 0.00174 -0.0782 0.7764 0.3154
-2.250 0.1210 0.00645 0.00159 -0.0797 0.7715 0.4190
-2.000 0.1527 0.00609 0.00149 -0.0808 0.7590 0.5141
-1.750 0.1829 0.00598 0.00144 -0.0814 0.7375 0.5607
-1.500 0.2129 0.00594 0.00143 -0.0818 0.7145 0.5990
-1.250 0.2428 0.00596 0.00145 -0.0822 0.6984 0.6262
-1.000 0.2725 0.00600 0.00146 -0.0825 0.6818 0.6364
-0.750 0.3017 0.00611 0.00146 -0.0827 0.6566 0.6437
-0.500 0.3304 0.00628 0.00150 -0.0829 0.6159 0.6528
-0.250 0.3584 0.00658 0.00159 -0.0830 0.5599 0.6620
0.000 0.3858 0.00698 0.00172 -0.0830 0.4950 0.6691
0.250 0.4129 0.00742 0.00187 -0.0830 0.4274 0.6733
0.500 0.4400 0.00785 0.00202 -0.0831 0.3634 0.6763
0.750 0.4676 0.00818 0.00216 -0.0832 0.3161 0.6794
1.000 0.4955 0.00846 0.00228 -0.0833 0.2787 0.6825
1.250 0.5235 0.00873 0.00241 -0.0834 0.2465 0.6857
1.500 0.5514 0.00898 0.00253 -0.0835 0.2199 0.6889
1.750 0.5796 0.00921 0.00265 -0.0837 0.1986 0.6917
2.000 0.6076 0.00942 0.00278 -0.0838 0.1791 0.6944
2.250 0.6356 0.00963 0.00292 -0.0839 0.1630 0.6973
2.500 0.6638 0.00981 0.00305 -0.0840 0.1514 0.7004
2.750 0.6918 0.01001 0.00319 -0.0841 0.1411 0.7034
3.000 0.7199 0.01019 0.00333 -0.0842 0.1329 0.7063
3.250 0.7479 0.01037 0.00346 -0.0843 0.1259 0.7090
3.500 0.7759 0.01054 0.00362 -0.0844 0.1198 0.7118
3.750 0.8036 0.01074 0.00379 -0.0844 0.1134 0.7146
4.000 0.8314 0.01091 0.00395 -0.0845 0.1089 0.7177
4.250 0.8590 0.01111 0.00413 -0.0845 0.1043 0.7208
4.500 0.8865 0.01131 0.00430 -0.0845 0.1003 0.7237
4.750 0.9142 0.01148 0.00448 -0.0845 0.0981 0.7264
5.000 0.9416 0.01166 0.00467 -0.0845 0.0954 0.7293
5.250 0.9686 0.01187 0.00488 -0.0845 0.0926 0.7323
5.500 0.9955 0.01210 0.00509 -0.0844 0.0897 0.7354
5.750 1.0224 0.01231 0.00532 -0.0843 0.0877 0.7386
6.000 1.0495 0.01251 0.00553 -0.0842 0.0864 0.7416
6.500 1.1026 0.01294 0.00600 -0.0839 0.0828 0.7474
6.750 1.1288 0.01318 0.00625 -0.0837 0.0811 0.7507
7.000 1.1546 0.01344 0.00652 -0.0835 0.0793 0.7541
7.250 1.1801 0.01373 0.00682 -0.0831 0.0774 0.7574
7.500 1.2058 0.01400 0.00711 -0.0829 0.0762 0.7602
7.750 1.2316 0.01421 0.00737 -0.0826 0.0751 0.7632
8.000 1.2571 0.01445 0.00765 -0.0823 0.0735 0.7667
8.250 1.2820 0.01472 0.00794 -0.0819 0.0717 0.7705
8.500 1.3066 0.01502 0.00825 -0.0815 0.0702 0.7741
8.750 1.3308 0.01534 0.00858 -0.0810 0.0685 0.7772
9.000 1.3542 0.01570 0.00896 -0.0804 0.0664 0.7807
9.250 1.3783 0.01598 0.00930 -0.0798 0.0656 0.7844
9.500 1.4021 0.01627 0.00963 -0.0793 0.0646 0.7885
9.750 1.4254 0.01658 0.00998 -0.0787 0.0632 0.7923
10.000 1.4481 0.01691 0.01035 -0.0779 0.0617 0.7962
10.250 1.4700 0.01728 0.01074 -0.0771 0.0598 0.8004
10.500 1.4912 0.01769 0.01117 -0.0761 0.0579 0.8046
10.750 1.5118 0.01809 0.01161 -0.0751 0.0566 0.8086
11.000 1.5323 0.01844 0.01203 -0.0740 0.0554 0.8131
11.250 1.5515 0.01884 0.01247 -0.0727 0.0536 0.8183
11.500 1.5673 0.01928 0.01294 -0.0709 0.0517 0.8236
11.750 1.5835 0.01981 0.01350 -0.0692 0.0494 0.8289
12.000 1.6006 0.02031 0.01406 -0.0676 0.0476 0.8347
12.250 1.6170 0.02089 0.01467 -0.0661 0.0449 0.8404
12.500 1.6316 0.02160 0.01539 -0.0645 0.0416 0.8467
12.750 1.6470 0.02226 0.01610 -0.0629 0.0391 0.8540
13.000 1.6601 0.02309 0.01697 -0.0612 0.0360 0.8621
13.250 1.6733 0.02392 0.01784 -0.0595 0.0335 0.8719
13.500 1.6846 0.02487 0.01885 -0.0577 0.0309 0.8837
13.750 1.6962 0.02580 0.01985 -0.0559 0.0291 0.8989
14.000 1.7060 0.02669 0.02086 -0.0539 0.0276 0.9266
14.250 1.7126 0.02767 0.02193 -0.0514 0.0264 1.0000
14.500 1.7229 0.02887 0.02318 -0.0499 0.0251 1.0000
14.750 1.7341 0.03000 0.02437 -0.0486 0.0243 1.0000
15.000 1.7439 0.03126 0.02569 -0.0472 0.0233 1.0000
15.250 1.7522 0.03268 0.02715 -0.0458 0.0222 1.0000
15.500 1.7589 0.03425 0.02878 -0.0444 0.0213 1.0000
15.750 1.7664 0.03576 0.03037 -0.0431 0.0206 1.0000
16.000 1.7733 0.03737 0.03206 -0.0419 0.0199 1.0000
16.250 1.7786 0.03916 0.03392 -0.0408 0.0192 1.0000
16.500 1.7820 0.04116 0.03599 -0.0396 0.0184 1.0000
16.750 1.7835 0.04338 0.03829 -0.0385 0.0177 1.0000
17.000 1.7853 0.04565 0.04063 -0.0377 0.0171 1.0000
17.250 1.7867 0.04804 0.04311 -0.0369 0.0166 1.0000
17.500 1.7862 0.05071 0.04588 -0.0364 0.0160 1.0000
17.750 1.7833 0.05376 0.04902 -0.0360 0.0154 1.0000
18.000 1.7785 0.05718 0.05253 -0.0359 0.0148 1.0000
18.250 1.7721 0.06095 0.05640 -0.0361 0.0144 1.0000
18.500 1.7653 0.06492 0.06049 -0.0366 0.0140 1.0000
18.750 1.7567 0.06932 0.06501 -0.0375 0.0136 1.0000
19.000 1.7450 0.07436 0.07019 -0.0388 0.0133 1.0000
19.250 1.7295 0.08020 0.07617 -0.0408 0.0130 1.0000
|
Polar data table (+)
Polar graphs
<< Back to NASA/LANGLEY MS(1)-0313 AIRFOIL (ms313-il)