NASA/LANGLEY MS(1)-0313 AIRFOIL (ms313-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: NASA/LANGLEY MS(1)-0313 AIRFOIL (ms313-il) Reynolds number: 200,000 Max Cl/Cd: 50.52 at α=2.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ms313-il-200000-n5.txt Download as CSV file: xf-ms313-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.750 -0.6087 0.09535 0.09140 -0.0372 1.0000 0.0200
-12.500 -0.7152 0.06510 0.06075 -0.0588 1.0000 0.0192
-12.250 -0.7479 0.05714 0.05252 -0.0638 1.0000 0.0192
-12.000 -0.7733 0.05136 0.04646 -0.0661 1.0000 0.0192
-11.750 -0.7934 0.04693 0.04177 -0.0665 1.0000 0.0193
-11.500 -0.8110 0.04356 0.03814 -0.0652 1.0000 0.0194
-11.250 -0.8247 0.04070 0.03501 -0.0630 1.0000 0.0197
-11.000 -0.8346 0.03816 0.03213 -0.0600 1.0000 0.0200
-10.750 -0.8417 0.03610 0.02975 -0.0565 1.0000 0.0204
-10.500 -0.8222 0.03465 0.02824 -0.0572 0.9965 0.0208
-10.250 -0.7962 0.03325 0.02673 -0.0589 0.9924 0.0214
-10.000 -0.7707 0.03162 0.02491 -0.0603 0.9877 0.0220
-9.750 -0.7434 0.02978 0.02282 -0.0619 0.9841 0.0227
-9.500 -0.7163 0.02801 0.02078 -0.0631 0.9800 0.0235
-9.250 -0.6892 0.02643 0.01892 -0.0640 0.9754 0.0243
-9.000 -0.6603 0.02514 0.01754 -0.0653 0.9719 0.0250
-8.750 -0.6307 0.02427 0.01664 -0.0666 0.9682 0.0260
-8.500 -0.6030 0.02343 0.01570 -0.0673 0.9629 0.0273
-8.250 -0.5733 0.02246 0.01458 -0.0682 0.9587 0.0286
-8.000 -0.5432 0.02143 0.01348 -0.0693 0.9555 0.0297
-7.750 -0.5169 0.02068 0.01272 -0.0697 0.9499 0.0308
-7.500 -0.4887 0.01998 0.01199 -0.0703 0.9452 0.0324
-7.250 -0.4590 0.01933 0.01122 -0.0710 0.9415 0.0345
-7.000 -0.4317 0.01861 0.01052 -0.0716 0.9368 0.0364
-6.750 -0.4048 0.01803 0.00992 -0.0718 0.9312 0.0385
-6.500 -0.3763 0.01748 0.00929 -0.0723 0.9269 0.0410
-6.250 -0.3474 0.01687 0.00870 -0.0730 0.9235 0.0442
-6.000 -0.3207 0.01645 0.00824 -0.0731 0.9181 0.0480
-5.750 -0.2930 0.01593 0.00773 -0.0736 0.9133 0.0522
-5.500 -0.2641 0.01553 0.00728 -0.0740 0.9093 0.0581
-5.250 -0.2355 0.01507 0.00686 -0.0745 0.9055 0.0661
-5.000 -0.2076 0.01467 0.00650 -0.0749 0.9006 0.0773
-4.750 -0.1789 0.01426 0.00614 -0.0755 0.8964 0.0947
-4.500 -0.1498 0.01375 0.00579 -0.0762 0.8927 0.1278
-4.250 -0.1205 0.01310 0.00544 -0.0771 0.8893 0.1951
-4.000 -0.0911 0.01233 0.00512 -0.0784 0.8847 0.3014
-3.750 -0.0608 0.01142 0.00491 -0.0799 0.8809 0.4576
-3.500 -0.0322 0.01118 0.00503 -0.0800 0.8772 0.5569
-3.250 -0.0036 0.01119 0.00514 -0.0799 0.8741 0.6026
-3.000 0.0250 0.01129 0.00525 -0.0799 0.8698 0.6307
-2.750 0.0535 0.01141 0.00537 -0.0798 0.8655 0.6538
-2.500 0.0817 0.01157 0.00553 -0.0795 0.8615 0.6773
-2.250 0.1103 0.01171 0.00563 -0.0793 0.8582 0.6930
-2.000 0.1381 0.01181 0.00573 -0.0790 0.8545 0.7002
-1.750 0.1670 0.01191 0.00580 -0.0792 0.8498 0.7105
-1.500 0.1943 0.01203 0.00593 -0.0787 0.8456 0.7188
-1.250 0.2246 0.01205 0.00588 -0.0792 0.8421 0.7262
-1.000 0.2528 0.01208 0.00592 -0.0791 0.8381 0.7295
-0.750 0.2810 0.01212 0.00595 -0.0791 0.8322 0.7333
-0.500 0.3098 0.01202 0.00580 -0.0789 0.8243 0.7377
-0.250 0.3378 0.01185 0.00553 -0.0785 0.8083 0.7423
0.000 0.3642 0.01170 0.00531 -0.0776 0.7902 0.7453
0.250 0.3914 0.01164 0.00522 -0.0771 0.7752 0.7486
0.500 0.4196 0.01161 0.00518 -0.0770 0.7621 0.7523
0.750 0.4485 0.01159 0.00513 -0.0771 0.7487 0.7564
1.000 0.4774 0.01157 0.00507 -0.0772 0.7339 0.7603
1.250 0.5047 0.01156 0.00505 -0.0768 0.7166 0.7631
1.500 0.5321 0.01157 0.00502 -0.0765 0.6949 0.7664
1.750 0.5596 0.01161 0.00499 -0.0762 0.6657 0.7702
2.000 0.5868 0.01172 0.00492 -0.0759 0.6192 0.7742
2.250 0.6103 0.01208 0.00489 -0.0749 0.5412 0.7775
2.500 0.6300 0.01279 0.00510 -0.0733 0.4506 0.7807
2.750 0.6507 0.01351 0.00544 -0.0722 0.3745 0.7842
3.000 0.6732 0.01415 0.00577 -0.0716 0.3151 0.7881
3.250 0.6973 0.01472 0.00608 -0.0713 0.2692 0.7923
3.500 0.7206 0.01518 0.00639 -0.0706 0.2370 0.7953
3.750 0.7446 0.01559 0.00670 -0.0701 0.2129 0.7987
4.000 0.7692 0.01600 0.00702 -0.0697 0.1940 0.8024
4.250 0.7943 0.01640 0.00734 -0.0694 0.1786 0.8066
4.500 0.8189 0.01678 0.00768 -0.0690 0.1663 0.8103
4.750 0.8424 0.01717 0.00803 -0.0684 0.1565 0.8136
5.000 0.8668 0.01752 0.00839 -0.0679 0.1485 0.8174
5.250 0.8908 0.01796 0.00879 -0.0675 0.1421 0.8218
5.500 0.9154 0.01831 0.00919 -0.0671 0.1366 0.8260
5.750 0.9382 0.01872 0.00960 -0.0663 0.1317 0.8296
6.000 0.9607 0.01920 0.01007 -0.0656 0.1274 0.8336
6.250 0.9849 0.01958 0.01051 -0.0651 0.1234 0.8383
6.500 1.0079 0.02000 0.01097 -0.0644 0.1197 0.8427
6.750 1.0293 0.02048 0.01147 -0.0635 0.1166 0.8471
7.000 1.0504 0.02107 0.01205 -0.0626 0.1139 0.8519
7.250 1.0737 0.02153 0.01259 -0.0620 0.1117 0.8569
7.500 1.0948 0.02198 0.01314 -0.0609 0.1093 0.8616
7.750 1.1162 0.02247 0.01370 -0.0600 0.1069 0.8673
8.000 1.1373 0.02299 0.01427 -0.0592 0.1045 0.8732
8.250 1.1563 0.02357 0.01487 -0.0579 0.1023 0.8790
8.500 1.1759 0.02431 0.01562 -0.0568 0.1004 0.8855
8.750 1.1958 0.02482 0.01626 -0.0557 0.0990 0.8923
9.000 1.2153 0.02537 0.01693 -0.0545 0.0971 0.9008
9.250 1.2328 0.02589 0.01756 -0.0529 0.0952 0.9107
9.500 1.2482 0.02640 0.01817 -0.0510 0.0933 0.9236
9.750 1.2621 0.02688 0.01874 -0.0489 0.0915 0.9450
10.000 1.2774 0.02751 0.01940 -0.0473 0.0896 1.0000
10.250 1.2971 0.02843 0.02034 -0.0467 0.0876 1.0000
10.500 1.3167 0.02916 0.02123 -0.0460 0.0857 1.0000
10.750 1.3352 0.02996 0.02214 -0.0452 0.0837 1.0000
11.000 1.3525 0.03078 0.02306 -0.0443 0.0818 1.0000
11.250 1.3686 0.03162 0.02397 -0.0433 0.0800 1.0000
11.500 1.3836 0.03255 0.02496 -0.0422 0.0783 1.0000
11.750 1.3980 0.03371 0.02610 -0.0412 0.0765 1.0000
12.000 1.4124 0.03469 0.02729 -0.0401 0.0749 1.0000
12.250 1.4259 0.03576 0.02852 -0.0389 0.0730 1.0000
12.500 1.4382 0.03688 0.02977 -0.0378 0.0711 1.0000
12.750 1.4495 0.03803 0.03103 -0.0367 0.0693 1.0000
13.000 1.4595 0.03928 0.03235 -0.0355 0.0678 1.0000
13.250 1.4678 0.04076 0.03384 -0.0344 0.0662 1.0000
13.500 1.4770 0.04226 0.03557 -0.0333 0.0646 1.0000
13.750 1.4851 0.04386 0.03736 -0.0323 0.0627 1.0000
14.000 1.4920 0.04553 0.03917 -0.0314 0.0609 1.0000
14.250 1.4978 0.04730 0.04105 -0.0306 0.0593 1.0000
14.500 1.5020 0.04925 0.04309 -0.0298 0.0579 1.0000
14.750 1.5044 0.05150 0.04543 -0.0291 0.0566 1.0000
15.000 1.5065 0.05394 0.04811 -0.0286 0.0549 1.0000
15.250 1.5072 0.05656 0.05090 -0.0282 0.0533 1.0000
15.500 1.5068 0.05935 0.05384 -0.0281 0.0518 1.0000
15.750 1.5051 0.06237 0.05698 -0.0282 0.0505 1.0000
16.000 1.5013 0.06577 0.06047 -0.0287 0.0494 1.0000
16.250 1.4952 0.06971 0.06455 -0.0294 0.0484 1.0000
16.500 1.4870 0.07421 0.06928 -0.0305 0.0472 1.0000
16.750 1.4768 0.07921 0.07450 -0.0321 0.0461 1.0000
17.000 1.4643 0.08482 0.08030 -0.0344 0.0451 1.0000
17.250 1.4496 0.09111 0.08677 -0.0374 0.0442 1.0000
17.500 1.4319 0.09822 0.09404 -0.0410 0.0435 1.0000
17.750 1.4107 0.10622 0.10220 -0.0454 0.0430 1.0000
18.000 1.3856 0.11527 0.11142 -0.0506 0.0425 1.0000
18.250 1.3564 0.12543 0.12173 -0.0567 0.0421 1.0000
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Polar data table (+)
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