NASA/LANGLEY MS(1)-0313 AIRFOIL (ms313-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: NASA/LANGLEY MS(1)-0313 AIRFOIL (ms313-il) Reynolds number: 500,000 Max Cl/Cd: 74.38 at α=2.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ms313-il-500000.txt Download as CSV file: xf-ms313-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.000 -0.6729 0.08134 0.07874 -0.0447 1.0000 0.0200
-12.750 -0.7111 0.06851 0.06576 -0.0551 1.0000 0.0196
-12.500 -0.7468 0.05917 0.05621 -0.0620 1.0000 0.0193
-12.250 -0.7803 0.05184 0.04862 -0.0659 1.0000 0.0191
-12.000 -0.8093 0.04609 0.04259 -0.0673 1.0000 0.0190
-11.750 -0.8322 0.04195 0.03821 -0.0666 1.0000 0.0190
-11.500 -0.8506 0.03883 0.03484 -0.0643 1.0000 0.0191
-11.250 -0.8673 0.03666 0.03246 -0.0599 1.0000 0.0192
-11.000 -0.8690 0.03386 0.02934 -0.0582 0.9980 0.0195
-10.750 -0.8480 0.03052 0.02558 -0.0604 0.9948 0.0198
-10.500 -0.8227 0.02818 0.02289 -0.0621 0.9918 0.0201
-10.250 -0.7966 0.02585 0.02026 -0.0637 0.9885 0.0205
-10.000 -0.7677 0.02389 0.01821 -0.0654 0.9862 0.0211
-9.750 -0.7351 0.02279 0.01705 -0.0674 0.9844 0.0217
-9.250 -0.6734 0.02079 0.01485 -0.0702 0.9778 0.0230
-9.000 -0.6425 0.01985 0.01378 -0.0714 0.9741 0.0238
-8.750 -0.6113 0.01897 0.01276 -0.0726 0.9709 0.0247
-8.500 -0.5846 0.01790 0.01172 -0.0731 0.9656 0.0258
-8.250 -0.5568 0.01732 0.01112 -0.0735 0.9600 0.0268
-8.000 -0.5288 0.01671 0.01044 -0.0739 0.9555 0.0278
-7.750 -0.5032 0.01619 0.00985 -0.0737 0.9490 0.0288
-7.500 -0.4785 0.01532 0.00894 -0.0735 0.9434 0.0300
-7.250 -0.4524 0.01481 0.00843 -0.0735 0.9385 0.0315
-7.000 -0.4259 0.01442 0.00802 -0.0735 0.9326 0.0332
-6.750 -0.3990 0.01412 0.00764 -0.0734 0.9273 0.0347
-6.500 -0.3733 0.01336 0.00690 -0.0735 0.9228 0.0371
-6.250 -0.3455 0.01300 0.00653 -0.0737 0.9176 0.0395
-6.000 -0.3178 0.01255 0.00605 -0.0739 0.9129 0.0425
-5.750 -0.2900 0.01219 0.00569 -0.0741 0.9087 0.0462
-5.500 -0.2615 0.01182 0.00529 -0.0745 0.9044 0.0507
-5.250 -0.2326 0.01150 0.00499 -0.0749 0.8997 0.0566
-5.000 -0.2036 0.01113 0.00465 -0.0754 0.8955 0.0660
-4.750 -0.1745 0.01079 0.00435 -0.0758 0.8919 0.0810
-4.500 -0.1448 0.01033 0.00407 -0.0766 0.8881 0.1165
-4.250 -0.1144 0.00962 0.00376 -0.0779 0.8838 0.2073
-4.000 -0.0828 0.00875 0.00343 -0.0797 0.8800 0.3445
-3.750 -0.0502 0.00790 0.00322 -0.0815 0.8768 0.5124
-3.500 -0.0200 0.00774 0.00325 -0.0820 0.8735 0.5807
-3.250 0.0102 0.00772 0.00330 -0.0824 0.8695 0.6139
-3.000 0.0401 0.00775 0.00334 -0.0827 0.8655 0.6356
-2.750 0.0697 0.00780 0.00338 -0.0829 0.8618 0.6525
-2.500 0.0991 0.00787 0.00343 -0.0830 0.8584 0.6662
-2.250 0.1288 0.00796 0.00349 -0.0833 0.8549 0.6780
-2.000 0.1584 0.00807 0.00360 -0.0835 0.8507 0.6912
-1.750 0.1867 0.00819 0.00376 -0.0833 0.8464 0.7036
-1.500 0.2155 0.00822 0.00372 -0.0832 0.8405 0.7109
-1.250 0.2429 0.00815 0.00363 -0.0826 0.8285 0.7160
-1.000 0.2706 0.00812 0.00354 -0.0821 0.8149 0.7234
-0.750 0.2986 0.00813 0.00352 -0.0818 0.8058 0.7301
-0.500 0.3272 0.00814 0.00354 -0.0817 0.7973 0.7352
-0.250 0.3566 0.00815 0.00349 -0.0819 0.7899 0.7394
0.000 0.3866 0.00813 0.00344 -0.0823 0.7805 0.7432
0.250 0.4152 0.00811 0.00341 -0.0822 0.7719 0.7461
0.500 0.4441 0.00810 0.00341 -0.0823 0.7620 0.7493
0.750 0.4733 0.00811 0.00340 -0.0824 0.7526 0.7527
1.000 0.5026 0.00813 0.00338 -0.0826 0.7412 0.7564
1.250 0.5321 0.00815 0.00336 -0.0829 0.7264 0.7599
1.500 0.5603 0.00816 0.00334 -0.0828 0.7086 0.7626
1.750 0.5885 0.00820 0.00336 -0.0827 0.6862 0.7656
2.000 0.6161 0.00831 0.00338 -0.0825 0.6527 0.7689
2.250 0.6419 0.00863 0.00341 -0.0821 0.5875 0.7725
2.500 0.6641 0.00942 0.00365 -0.0812 0.4782 0.7758
2.750 0.6858 0.01020 0.00399 -0.0804 0.3840 0.7788
3.000 0.7090 0.01085 0.00430 -0.0798 0.3126 0.7818
3.250 0.7333 0.01140 0.00458 -0.0794 0.2588 0.7850
3.500 0.7584 0.01188 0.00486 -0.0791 0.2208 0.7886
3.750 0.7846 0.01229 0.00511 -0.0790 0.1939 0.7922
4.000 0.8099 0.01264 0.00537 -0.0787 0.1744 0.7951
4.250 0.8355 0.01297 0.00564 -0.0784 0.1604 0.7981
4.500 0.8614 0.01327 0.00591 -0.0781 0.1499 0.8017
4.750 0.8872 0.01363 0.00622 -0.0779 0.1411 0.8054
5.000 0.9138 0.01392 0.00649 -0.0778 0.1346 0.8090
5.250 0.9376 0.01434 0.00688 -0.0772 0.1281 0.8120
5.500 0.9636 0.01457 0.00715 -0.0769 0.1248 0.8155
5.750 0.9891 0.01486 0.00747 -0.0765 0.1210 0.8194
6.000 1.0139 0.01526 0.00784 -0.0762 0.1173 0.8233
6.250 1.0369 0.01577 0.00836 -0.0755 0.1136 0.8268
6.500 1.0619 0.01602 0.00868 -0.0750 0.1116 0.8304
6.750 1.0866 0.01632 0.00902 -0.0745 0.1091 0.8346
7.000 1.1112 0.01667 0.00940 -0.0741 0.1068 0.8389
7.250 1.1344 0.01709 0.00984 -0.0735 0.1045 0.8427
7.500 1.1552 0.01769 0.01045 -0.0724 0.1020 0.8467
7.750 1.1766 0.01829 0.01110 -0.0714 0.1001 0.8515
8.000 1.2010 0.01861 0.01148 -0.0710 0.0987 0.8565
8.250 1.2235 0.01891 0.01187 -0.0702 0.0969 0.8609
8.500 1.2461 0.01926 0.01227 -0.0694 0.0948 0.8659
8.750 1.2685 0.01964 0.01269 -0.0687 0.0928 0.8714
9.000 1.2882 0.02014 0.01322 -0.0675 0.0909 0.8768
9.250 1.3053 0.02108 0.01418 -0.0660 0.0883 0.8831
9.500 1.3260 0.02148 0.01467 -0.0650 0.0873 0.8896
9.750 1.3455 0.02181 0.01511 -0.0637 0.0860 0.8968
10.000 1.3634 0.02217 0.01557 -0.0621 0.0844 0.9050
10.250 1.3790 0.02255 0.01604 -0.0602 0.0828 0.9152
10.500 1.3940 0.02294 0.01651 -0.0582 0.0813 0.9291
10.750 1.4043 0.02328 0.01693 -0.0553 0.0798 0.9666
11.000 1.4207 0.02415 0.01780 -0.0541 0.0777 1.0000
11.250 1.4388 0.02506 0.01877 -0.0532 0.0760 1.0000
11.500 1.4580 0.02554 0.01936 -0.0525 0.0747 1.0000
11.750 1.4763 0.02612 0.02001 -0.0516 0.0729 1.0000
12.000 1.4936 0.02675 0.02070 -0.0507 0.0711 1.0000
12.250 1.5100 0.02743 0.02142 -0.0497 0.0694 1.0000
12.500 1.5232 0.02842 0.02241 -0.0484 0.0674 1.0000
12.750 1.5362 0.02950 0.02356 -0.0471 0.0655 1.0000
13.000 1.5526 0.03019 0.02437 -0.0462 0.0639 1.0000
13.250 1.5680 0.03098 0.02524 -0.0453 0.0620 1.0000
13.500 1.5827 0.03183 0.02613 -0.0444 0.0600 1.0000
13.750 1.5927 0.03309 0.02739 -0.0431 0.0579 1.0000
14.000 1.6043 0.03429 0.02868 -0.0420 0.0559 1.0000
14.250 1.6190 0.03521 0.02971 -0.0413 0.0537 1.0000
14.500 1.6318 0.03629 0.03083 -0.0405 0.0515 1.0000
14.750 1.6377 0.03802 0.03255 -0.0394 0.0492 1.0000
15.000 1.6489 0.03933 0.03399 -0.0386 0.0473 1.0000
15.250 1.6587 0.04079 0.03553 -0.0378 0.0452 1.0000
15.500 1.6647 0.04261 0.03740 -0.0369 0.0435 1.0000
16.000 1.6695 0.04712 0.04208 -0.0352 0.0404 1.0000
16.250 1.6731 0.04935 0.04443 -0.0346 0.0390 1.0000
16.500 1.6735 0.05199 0.04714 -0.0341 0.0376 1.0000
16.750 1.6693 0.05527 0.05049 -0.0339 0.0364 1.0000
17.000 1.6612 0.05918 0.05449 -0.0340 0.0354 1.0000
17.250 1.6594 0.06250 0.05798 -0.0342 0.0345 1.0000
17.500 1.6547 0.06631 0.06192 -0.0348 0.0335 1.0000
17.750 1.6465 0.07078 0.06652 -0.0358 0.0327 1.0000
18.000 1.6350 0.07594 0.07181 -0.0374 0.0320 1.0000
18.250 1.6195 0.08195 0.07794 -0.0396 0.0314 1.0000
18.500 1.5994 0.08892 0.08504 -0.0425 0.0309 1.0000
18.750 1.5758 0.09671 0.09298 -0.0460 0.0305 1.0000
19.000 1.5498 0.10512 0.10152 -0.0500 0.0301 1.0000
19.250 1.5276 0.11304 0.10962 -0.0540 0.0298 1.0000
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Polar data table (+)
Polar graphs
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