NASA/LANGLEY MS(1)-0317 AIRFOIL (ms317-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: NASA/LANGLEY MS(1)-0317 AIRFOIL (ms317-il) Reynolds number: 100,000 Max Cl/Cd: 35.55 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ms317-il-100000-n5.txt Download as CSV file: xf-ms317-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.000 -0.7144 0.09347 0.08709 -0.0554 1.0000 0.0443
-14.750 -0.7696 0.08033 0.07361 -0.0638 1.0000 0.0439
-14.500 -0.8047 0.07228 0.06526 -0.0681 1.0000 0.0439
-14.250 -0.8309 0.06621 0.05890 -0.0705 1.0000 0.0442
-14.000 -0.8520 0.06118 0.05357 -0.0718 1.0000 0.0445
-13.750 -0.8694 0.05688 0.04894 -0.0723 1.0000 0.0450
-13.500 -0.8654 0.05476 0.04680 -0.0721 1.0000 0.0455
-13.250 -0.8627 0.05261 0.04459 -0.0718 1.0000 0.0461
-13.000 -0.8610 0.05044 0.04232 -0.0713 1.0000 0.0468
-12.750 -0.8593 0.04829 0.04004 -0.0706 1.0000 0.0475
-12.500 -0.8571 0.04622 0.03781 -0.0696 1.0000 0.0483
-12.250 -0.8553 0.04426 0.03566 -0.0683 1.0000 0.0493
-12.000 -0.8547 0.04239 0.03353 -0.0665 1.0000 0.0505
-11.750 -0.8480 0.04122 0.03241 -0.0648 1.0000 0.0514
-11.500 -0.8455 0.04022 0.03142 -0.0624 1.0000 0.0523
-11.250 -0.8479 0.03934 0.03052 -0.0591 1.0000 0.0533
-11.000 -0.8537 0.03855 0.02967 -0.0550 1.0000 0.0542
-10.750 -0.8578 0.03773 0.02877 -0.0511 1.0000 0.0552
-10.500 -0.8473 0.03656 0.02740 -0.0496 0.9976 0.0567
-10.250 -0.8186 0.03535 0.02625 -0.0515 0.9925 0.0586
-10.000 -0.7911 0.03418 0.02500 -0.0529 0.9861 0.0612
-9.750 -0.7608 0.03296 0.02365 -0.0546 0.9813 0.0642
-9.500 -0.7338 0.03193 0.02265 -0.0558 0.9750 0.0669
-9.250 -0.7043 0.03091 0.02150 -0.0572 0.9699 0.0707
-9.000 -0.6736 0.02989 0.02053 -0.0591 0.9659 0.0745
-8.750 -0.6473 0.02903 0.01957 -0.0598 0.9588 0.0792
-8.500 -0.6181 0.02808 0.01868 -0.0612 0.9538 0.0839
-8.250 -0.5897 0.02725 0.01780 -0.0623 0.9484 0.0901
-8.000 -0.5650 0.02649 0.01706 -0.0627 0.9414 0.0964
-7.750 -0.5359 0.02567 0.01627 -0.0639 0.9365 0.1041
-7.500 -0.5102 0.02500 0.01560 -0.0644 0.9303 0.1128
-7.250 -0.4853 0.02438 0.01498 -0.0646 0.9235 0.1231
-7.000 -0.4570 0.02368 0.01435 -0.0655 0.9187 0.1356
-6.750 -0.4317 0.02308 0.01381 -0.0659 0.9129 0.1503
-6.500 -0.4080 0.02252 0.01334 -0.0659 0.9060 0.1681
-6.250 -0.3810 0.02183 0.01279 -0.0665 0.9011 0.1919
-6.000 -0.3532 0.02114 0.01226 -0.0674 0.8970 0.2236
-5.750 -0.3326 0.02056 0.01189 -0.0670 0.8898 0.2615
-5.500 -0.3074 0.01979 0.01142 -0.0675 0.8845 0.3171
-5.250 -0.2806 0.01897 0.01109 -0.0682 0.8804 0.3993
-5.000 -0.2575 0.01889 0.01149 -0.0669 0.8750 0.4846
-4.750 -0.2340 0.01928 0.01206 -0.0652 0.8689 0.5380
-4.500 -0.2056 0.01957 0.01235 -0.0648 0.8644 0.5734
-4.250 -0.1754 0.01986 0.01257 -0.0647 0.8607 0.5981
-4.000 -0.1480 0.02014 0.01277 -0.0644 0.8554 0.6181
-3.750 -0.1222 0.02051 0.01308 -0.0637 0.8495 0.6342
-3.500 -0.0940 0.02085 0.01335 -0.0633 0.8451 0.6493
-3.250 -0.0637 0.02107 0.01347 -0.0634 0.8415 0.6641
-3.000 -0.0398 0.02160 0.01398 -0.0616 0.8366 0.6720
-2.750 -0.0139 0.02178 0.01409 -0.0615 0.8306 0.6837
-2.500 0.0101 0.02224 0.01454 -0.0597 0.8262 0.6905
-2.250 0.0401 0.02233 0.01455 -0.0601 0.8226 0.7027
-2.000 0.0642 0.02275 0.01497 -0.0581 0.8188 0.7089
-1.750 0.0868 0.02299 0.01519 -0.0574 0.8119 0.7183
-1.500 0.1134 0.02305 0.01521 -0.0571 0.8071 0.7241
-1.250 0.1412 0.02306 0.01519 -0.0567 0.8032 0.7277
-1.000 0.1708 0.02299 0.01507 -0.0569 0.7998 0.7320
-0.750 0.1949 0.02308 0.01515 -0.0571 0.7927 0.7376
-0.500 0.2247 0.02298 0.01502 -0.0579 0.7877 0.7422
-0.250 0.2527 0.02294 0.01497 -0.0576 0.7838 0.7449
0.000 0.2807 0.02290 0.01491 -0.0575 0.7792 0.7481
0.250 0.3040 0.02298 0.01502 -0.0570 0.7708 0.7519
0.500 0.3358 0.02278 0.01478 -0.0578 0.7651 0.7561
0.750 0.3689 0.02251 0.01447 -0.0591 0.7576 0.7607
1.000 0.3948 0.02222 0.01418 -0.0581 0.7460 0.7628
1.250 0.4203 0.02190 0.01385 -0.0569 0.7324 0.7655
1.500 0.4502 0.02146 0.01335 -0.0565 0.7203 0.7686
1.750 0.4769 0.02125 0.01316 -0.0562 0.7071 0.7720
2.000 0.5051 0.02109 0.01299 -0.0564 0.6945 0.7755
2.250 0.5379 0.02080 0.01267 -0.0573 0.6822 0.7795
2.500 0.5623 0.02066 0.01255 -0.0564 0.6676 0.7819
2.750 0.5865 0.02056 0.01249 -0.0555 0.6512 0.7844
3.000 0.6118 0.02044 0.01238 -0.0548 0.6329 0.7873
3.250 0.6380 0.02032 0.01224 -0.0543 0.6118 0.7907
3.500 0.6645 0.02026 0.01214 -0.0541 0.5851 0.7942
3.750 0.6922 0.02022 0.01200 -0.0542 0.5489 0.7975
4.000 0.7156 0.02028 0.01183 -0.0531 0.4985 0.7999
4.250 0.7333 0.02063 0.01181 -0.0511 0.4362 0.8024
4.500 0.7479 0.02127 0.01209 -0.0490 0.3786 0.8055
4.750 0.7629 0.02200 0.01251 -0.0472 0.3319 0.8089
5.000 0.7801 0.02272 0.01299 -0.0460 0.2948 0.8122
5.250 0.7995 0.02340 0.01349 -0.0453 0.2655 0.8154
5.500 0.8167 0.02405 0.01401 -0.0441 0.2437 0.8181
5.750 0.8327 0.02463 0.01451 -0.0424 0.2267 0.8209
6.000 0.8498 0.02521 0.01503 -0.0410 0.2130 0.8242
6.250 0.8672 0.02582 0.01559 -0.0398 0.2024 0.8277
6.500 0.8853 0.02645 0.01617 -0.0388 0.1932 0.8312
6.750 0.9054 0.02710 0.01679 -0.0383 0.1854 0.8345
7.000 0.9213 0.02769 0.01738 -0.0367 0.1786 0.8373
7.250 0.9376 0.02841 0.01805 -0.0354 0.1730 0.8407
7.500 0.9578 0.02903 0.01873 -0.0347 0.1672 0.8444
7.750 0.9779 0.02976 0.01945 -0.0341 0.1623 0.8482
8.000 0.9986 0.03062 0.02022 -0.0339 0.1584 0.8517
8.250 1.0185 0.03125 0.02094 -0.0330 0.1547 0.8546
8.500 1.0382 0.03194 0.02168 -0.0323 0.1511 0.8580
8.750 1.0580 0.03269 0.02246 -0.0316 0.1477 0.8620
9.000 1.0787 0.03353 0.02325 -0.0313 0.1448 0.8663
9.250 1.0997 0.03433 0.02409 -0.0308 0.1420 0.8703
9.500 1.1191 0.03507 0.02496 -0.0300 0.1393 0.8743
9.750 1.1397 0.03589 0.02585 -0.0295 0.1368 0.8785
10.000 1.1610 0.03676 0.02676 -0.0293 0.1344 0.8829
10.250 1.1806 0.03761 0.02764 -0.0287 0.1323 0.8871
10.500 1.2013 0.03848 0.02847 -0.0281 0.1303 0.8917
10.750 1.2198 0.03947 0.02961 -0.0275 0.1283 0.8973
11.000 1.2366 0.04048 0.03078 -0.0266 0.1263 0.9031
11.250 1.2528 0.04149 0.03195 -0.0257 0.1244 0.9097
11.500 1.2691 0.04255 0.03312 -0.0249 0.1226 0.9166
11.750 1.2838 0.04355 0.03420 -0.0238 0.1208 0.9243
12.000 1.3000 0.04454 0.03524 -0.0230 0.1192 0.9330
12.500 1.3278 0.04686 0.03775 -0.0210 0.1162 0.9647
12.750 1.3360 0.04853 0.03968 -0.0203 0.1146 1.0000
13.000 1.3460 0.05043 0.04180 -0.0200 0.1128 1.0000
13.250 1.3554 0.05233 0.04386 -0.0197 0.1111 1.0000
13.500 1.3655 0.05417 0.04582 -0.0195 0.1095 1.0000
13.750 1.3772 0.05590 0.04761 -0.0194 0.1081 1.0000
14.000 1.3927 0.05740 0.04911 -0.0195 0.1066 1.0000
14.250 1.4023 0.05943 0.05121 -0.0193 0.1052 1.0000
14.500 1.3925 0.06279 0.05492 -0.0186 0.1040 1.0000
14.750 1.3819 0.06642 0.05884 -0.0182 0.1027 1.0000
15.000 1.3708 0.07024 0.06292 -0.0181 0.1014 1.0000
15.250 1.3596 0.07420 0.06711 -0.0183 0.1001 1.0000
15.500 1.3494 0.07820 0.07130 -0.0189 0.0989 1.0000
15.750 1.3413 0.08208 0.07532 -0.0196 0.0978 1.0000
16.000 1.3378 0.08555 0.07889 -0.0205 0.0967 1.0000
16.250 1.3462 0.08767 0.08102 -0.0209 0.0956 1.0000
16.500 1.3266 0.09352 0.08706 -0.0229 0.0947 1.0000
16.750 1.2404 0.11040 0.10452 -0.0317 0.0942 1.0000
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Polar data table (+)
Polar graphs
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