NASA/LANGLEY MS(1)-0317 AIRFOIL (ms317-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: NASA/LANGLEY MS(1)-0317 AIRFOIL (ms317-il) Reynolds number: 200,000 Max Cl/Cd: 47.7 at α=3° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ms317-il-200000-n5.txt Download as CSV file: xf-ms317-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-17.500 -0.8667 0.10357 0.09843 -0.0443 1.0000 0.0279
-17.250 -0.8970 0.09361 0.08822 -0.0504 1.0000 0.0280
-17.000 -0.9154 0.08637 0.08079 -0.0547 1.0000 0.0281
-16.750 -0.9287 0.08034 0.07460 -0.0581 1.0000 0.0283
-16.500 -0.9389 0.07508 0.06918 -0.0609 1.0000 0.0285
-16.250 -0.9470 0.07038 0.06433 -0.0633 1.0000 0.0288
-16.000 -0.9534 0.06615 0.05996 -0.0652 1.0000 0.0291
-15.750 -0.9583 0.06230 0.05595 -0.0667 1.0000 0.0294
-15.500 -0.9619 0.05879 0.05227 -0.0678 1.0000 0.0298
-15.250 -0.9644 0.05558 0.04889 -0.0686 1.0000 0.0303
-15.000 -0.9657 0.05263 0.04574 -0.0692 1.0000 0.0307
-14.750 -0.9639 0.05012 0.04309 -0.0694 1.0000 0.0311
-14.500 -0.9580 0.04812 0.04108 -0.0694 1.0000 0.0315
-14.250 -0.9520 0.04619 0.03910 -0.0694 1.0000 0.0319
-14.000 -0.9455 0.04434 0.03720 -0.0693 1.0000 0.0324
-13.750 -0.9382 0.04257 0.03536 -0.0690 1.0000 0.0329
-13.500 -0.9304 0.04088 0.03358 -0.0687 1.0000 0.0334
-13.250 -0.9216 0.03929 0.03189 -0.0682 1.0000 0.0340
-13.000 -0.9122 0.03779 0.03028 -0.0676 1.0000 0.0347
-12.750 -0.9023 0.03639 0.02879 -0.0669 1.0000 0.0354
-12.500 -0.8927 0.03510 0.02751 -0.0662 1.0000 0.0360
-12.250 -0.8826 0.03392 0.02631 -0.0654 1.0000 0.0368
-12.000 -0.8728 0.03282 0.02517 -0.0643 1.0000 0.0376
-11.750 -0.8639 0.03180 0.02411 -0.0629 1.0000 0.0385
-11.500 -0.8575 0.03089 0.02315 -0.0609 1.0000 0.0394
-11.250 -0.8538 0.03007 0.02230 -0.0584 0.9988 0.0401
-11.000 -0.8290 0.02888 0.02111 -0.0601 0.9912 0.0412
-10.750 -0.8039 0.02782 0.02001 -0.0615 0.9824 0.0426
-10.500 -0.7789 0.02683 0.01895 -0.0627 0.9732 0.0443
-10.250 -0.7539 0.02582 0.01791 -0.0639 0.9646 0.0460
-10.000 -0.7308 0.02494 0.01700 -0.0646 0.9547 0.0478
-9.750 -0.7074 0.02412 0.01612 -0.0651 0.9458 0.0500
-9.500 -0.6839 0.02327 0.01525 -0.0657 0.9371 0.0520
-9.250 -0.6610 0.02255 0.01449 -0.0659 0.9282 0.0546
-9.000 -0.6379 0.02185 0.01374 -0.0661 0.9198 0.0576
-8.750 -0.6152 0.02120 0.01308 -0.0661 0.9119 0.0609
-8.500 -0.5926 0.02061 0.01245 -0.0660 0.9038 0.0646
-8.250 -0.5689 0.02004 0.01185 -0.0660 0.8973 0.0690
-8.000 -0.5462 0.01952 0.01133 -0.0658 0.8892 0.0738
-7.750 -0.5218 0.01905 0.01081 -0.0657 0.8827 0.0795
-7.500 -0.4976 0.01853 0.01030 -0.0657 0.8769 0.0855
-7.250 -0.4731 0.01808 0.00985 -0.0657 0.8699 0.0923
-7.000 -0.4476 0.01766 0.00941 -0.0657 0.8641 0.1002
-6.750 -0.4218 0.01721 0.00897 -0.0659 0.8595 0.1094
-6.500 -0.3958 0.01678 0.00859 -0.0661 0.8538 0.1203
-6.250 -0.3693 0.01636 0.00821 -0.0664 0.8484 0.1338
-6.000 -0.3424 0.01594 0.00784 -0.0668 0.8436 0.1514
-5.750 -0.3151 0.01546 0.00745 -0.0673 0.8394 0.1749
-5.500 -0.2876 0.01499 0.00712 -0.0679 0.8337 0.2050
-5.250 -0.2595 0.01444 0.00677 -0.0687 0.8286 0.2437
-5.000 -0.2306 0.01387 0.00639 -0.0697 0.8243 0.2932
-4.750 -0.2008 0.01319 0.00600 -0.0710 0.8206 0.3605
-4.500 -0.1708 0.01255 0.00583 -0.0722 0.8157 0.4533
-4.250 -0.1418 0.01237 0.00596 -0.0725 0.8108 0.5229
-4.000 -0.1127 0.01242 0.00612 -0.0725 0.8065 0.5625
-3.750 -0.0829 0.01250 0.00618 -0.0727 0.8027 0.5879
-3.500 -0.0527 0.01259 0.00623 -0.0730 0.7987 0.6063
-3.250 -0.0232 0.01272 0.00636 -0.0731 0.7938 0.6202
-3.000 0.0063 0.01286 0.00649 -0.0733 0.7895 0.6332
-2.750 0.0367 0.01300 0.00656 -0.0736 0.7857 0.6465
-2.500 0.0656 0.01319 0.00672 -0.0734 0.7823 0.6556
-2.250 0.0965 0.01327 0.00674 -0.0741 0.7783 0.6644
-2.000 0.1239 0.01348 0.00699 -0.0736 0.7734 0.6708
-1.750 0.1549 0.01363 0.00708 -0.0742 0.7689 0.6823
-1.500 0.1808 0.01389 0.00739 -0.0731 0.7649 0.6882
-1.250 0.2100 0.01401 0.00745 -0.0731 0.7615 0.6934
-1.000 0.2407 0.01401 0.00745 -0.0738 0.7567 0.6976
-0.750 0.2728 0.01397 0.00736 -0.0750 0.7518 0.7018
-0.500 0.3012 0.01400 0.00739 -0.0749 0.7470 0.7039
-0.250 0.3302 0.01400 0.00734 -0.0748 0.7413 0.7062
0.000 0.3579 0.01391 0.00725 -0.0746 0.7276 0.7087
0.250 0.3862 0.01380 0.00708 -0.0743 0.7112 0.7115
0.500 0.4154 0.01373 0.00694 -0.0744 0.6970 0.7147
0.750 0.4458 0.01367 0.00682 -0.0750 0.6864 0.7178
1.000 0.4769 0.01362 0.00673 -0.0758 0.6743 0.7212
1.250 0.5048 0.01362 0.00671 -0.0755 0.6622 0.7231
1.500 0.5325 0.01363 0.00670 -0.0753 0.6481 0.7251
1.750 0.5605 0.01365 0.00671 -0.0752 0.6316 0.7271
2.000 0.5884 0.01369 0.00670 -0.0752 0.6126 0.7294
2.250 0.6162 0.01376 0.00670 -0.0751 0.5900 0.7320
2.500 0.6437 0.01387 0.00670 -0.0750 0.5599 0.7349
2.750 0.6700 0.01409 0.00671 -0.0748 0.5172 0.7378
3.000 0.6936 0.01454 0.00679 -0.0742 0.4530 0.7408
3.250 0.7120 0.01521 0.00711 -0.0727 0.3895 0.7428
3.500 0.7311 0.01587 0.00750 -0.0713 0.3364 0.7447
3.750 0.7513 0.01648 0.00789 -0.0703 0.2945 0.7467
4.000 0.7727 0.01702 0.00826 -0.0694 0.2619 0.7488
4.250 0.7950 0.01751 0.00862 -0.0687 0.2370 0.7512
4.500 0.8177 0.01798 0.00898 -0.0681 0.2169 0.7540
4.750 0.8407 0.01844 0.00934 -0.0676 0.2007 0.7569
5.000 0.8640 0.01890 0.00971 -0.0673 0.1872 0.7596
5.250 0.8860 0.01933 0.01010 -0.0665 0.1760 0.7616
5.500 0.9073 0.01975 0.01050 -0.0656 0.1672 0.7634
5.750 0.9275 0.02022 0.01095 -0.0645 0.1597 0.7654
6.000 0.9486 0.02064 0.01139 -0.0636 0.1538 0.7678
6.250 0.9688 0.02111 0.01185 -0.0626 0.1483 0.7705
6.500 0.9873 0.02167 0.01238 -0.0613 0.1438 0.7734
6.750 1.0071 0.02210 0.01285 -0.0603 0.1400 0.7763
7.000 1.0251 0.02259 0.01335 -0.0590 0.1362 0.7791
7.250 1.0414 0.02315 0.01391 -0.0574 0.1328 0.7812
7.500 1.0571 0.02384 0.01459 -0.0558 0.1298 0.7835
7.750 1.0761 0.02438 0.01521 -0.0548 0.1272 0.7862
8.000 1.0947 0.02499 0.01587 -0.0537 0.1246 0.7892
8.250 1.1130 0.02565 0.01658 -0.0528 0.1223 0.7921
8.500 1.1309 0.02638 0.01731 -0.0518 0.1202 0.7950
8.750 1.1481 0.02721 0.01812 -0.0509 0.1183 0.7980
9.000 1.1648 0.02799 0.01894 -0.0498 0.1166 0.8003
9.250 1.1826 0.02869 0.01973 -0.0488 0.1149 0.8029
9.500 1.1999 0.02943 0.02055 -0.0478 0.1130 0.8060
9.750 1.2171 0.03022 0.02140 -0.0469 0.1113 0.8094
10.000 1.2343 0.03105 0.02228 -0.0461 0.1098 0.8130
10.250 1.2513 0.03195 0.02320 -0.0453 0.1084 0.8163
10.500 1.2666 0.03287 0.02415 -0.0443 0.1070 0.8190
10.750 1.2818 0.03387 0.02515 -0.0432 0.1057 0.8220
11.000 1.2984 0.03474 0.02614 -0.0423 0.1044 0.8253
11.250 1.3148 0.03566 0.02717 -0.0415 0.1031 0.8290
11.500 1.3310 0.03664 0.02824 -0.0408 0.1017 0.8328
11.750 1.3460 0.03764 0.02933 -0.0399 0.1004 0.8364
12.000 1.3598 0.03868 0.03044 -0.0389 0.0991 0.8402
12.250 1.3733 0.03977 0.03160 -0.0381 0.0978 0.8447
12.500 1.3868 0.04093 0.03281 -0.0373 0.0966 0.8494
12.750 1.4004 0.04211 0.03399 -0.0364 0.0954 0.8536
13.000 1.4123 0.04333 0.03534 -0.0354 0.0942 0.8579
13.250 1.4233 0.04466 0.03682 -0.0346 0.0929 0.8628
13.500 1.4344 0.04606 0.03835 -0.0338 0.0916 0.8681
13.750 1.4436 0.04745 0.03987 -0.0329 0.0903 0.8730
14.000 1.4528 0.04891 0.04143 -0.0320 0.0890 0.8788
14.500 1.4692 0.05198 0.04465 -0.0304 0.0869 0.8917
14.750 1.4776 0.05355 0.04625 -0.0296 0.0859 0.8998
15.000 1.4833 0.05526 0.04809 -0.0286 0.0849 0.9093
15.250 1.4860 0.05724 0.05029 -0.0277 0.0838 0.9219
15.500 1.4871 0.05918 0.05241 -0.0265 0.0828 0.9450
15.750 1.4884 0.06130 0.05469 -0.0259 0.0817 1.0000
16.000 1.4931 0.06373 0.05724 -0.0261 0.0806 1.0000
16.250 1.4975 0.06621 0.05981 -0.0264 0.0796 1.0000
16.500 1.5015 0.06875 0.06243 -0.0267 0.0786 1.0000
16.750 1.5053 0.07136 0.06509 -0.0271 0.0777 1.0000
17.000 1.5104 0.07377 0.06751 -0.0274 0.0768 1.0000
17.250 1.5065 0.07750 0.07145 -0.0282 0.0758 1.0000
17.500 1.5009 0.08157 0.07574 -0.0293 0.0748 1.0000
17.750 1.4951 0.08577 0.08013 -0.0305 0.0737 1.0000
18.000 1.4893 0.09007 0.08459 -0.0320 0.0727 1.0000
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