NASA/LANGLEY MS(1)-0313 AIRFOIL (ms313-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: NASA/LANGLEY MS(1)-0313 AIRFOIL (ms313-il) Reynolds number: 500,000 Max Cl/Cd: 69.78 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ms313-il-500000-n5.txt Download as CSV file: xf-ms313-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.000 -0.9201 0.08413 0.08090 -0.0397 1.0000 0.0114
-15.750 -0.9660 0.07029 0.06674 -0.0490 1.0000 0.0113
-15.500 -0.9879 0.06242 0.05867 -0.0542 1.0000 0.0114
-15.250 -1.0014 0.05663 0.05272 -0.0579 1.0000 0.0114
-15.000 -1.0103 0.05199 0.04793 -0.0604 1.0000 0.0115
-14.750 -1.0152 0.04816 0.04398 -0.0623 1.0000 0.0115
-14.500 -1.0180 0.04483 0.04053 -0.0636 1.0000 0.0116
-14.250 -1.0181 0.04197 0.03755 -0.0645 1.0000 0.0117
-14.000 -1.0168 0.03940 0.03486 -0.0651 1.0000 0.0119
-13.750 -1.0139 0.03710 0.03243 -0.0654 1.0000 0.0120
-13.500 -1.0097 0.03499 0.03020 -0.0654 1.0000 0.0121
-13.250 -1.0045 0.03308 0.02816 -0.0652 1.0000 0.0123
-13.000 -0.9984 0.03135 0.02631 -0.0647 1.0000 0.0124
-12.750 -0.9921 0.02980 0.02464 -0.0638 1.0000 0.0126
-12.500 -0.9869 0.02843 0.02317 -0.0624 1.0000 0.0128
-12.250 -0.9780 0.02717 0.02179 -0.0614 1.0000 0.0129
-12.000 -0.9663 0.02604 0.02054 -0.0604 0.9991 0.0132
-11.750 -0.9413 0.02481 0.01917 -0.0617 0.9928 0.0134
-11.500 -0.9157 0.02373 0.01795 -0.0628 0.9861 0.0136
-11.250 -0.8907 0.02253 0.01668 -0.0639 0.9795 0.0139
-11.000 -0.8642 0.02162 0.01571 -0.0650 0.9726 0.0143
-10.750 -0.8376 0.02085 0.01487 -0.0658 0.9657 0.0146
-10.500 -0.8114 0.02013 0.01409 -0.0663 0.9583 0.0150
-10.250 -0.7861 0.01946 0.01333 -0.0666 0.9514 0.0154
-10.000 -0.7613 0.01880 0.01260 -0.0667 0.9439 0.0158
-9.750 -0.7365 0.01820 0.01190 -0.0667 0.9372 0.0163
-9.500 -0.7117 0.01767 0.01127 -0.0666 0.9298 0.0168
-9.000 -0.6618 0.01654 0.01008 -0.0666 0.9171 0.0180
-8.750 -0.6360 0.01609 0.00957 -0.0666 0.9113 0.0187
-8.500 -0.6099 0.01563 0.00905 -0.0667 0.9063 0.0194
-8.250 -0.5833 0.01518 0.00854 -0.0668 0.9008 0.0200
-8.000 -0.5568 0.01470 0.00800 -0.0669 0.8953 0.0208
-7.750 -0.5300 0.01429 0.00756 -0.0670 0.8906 0.0217
-7.500 -0.5023 0.01394 0.00718 -0.0673 0.8858 0.0228
-7.250 -0.4745 0.01361 0.00680 -0.0676 0.8812 0.0240
-7.000 -0.4467 0.01322 0.00638 -0.0679 0.8768 0.0253
-6.750 -0.4187 0.01289 0.00602 -0.0681 0.8729 0.0267
-6.500 -0.3901 0.01258 0.00570 -0.0685 0.8683 0.0283
-6.250 -0.3615 0.01227 0.00536 -0.0689 0.8638 0.0303
-6.000 -0.3328 0.01199 0.00507 -0.0693 0.8599 0.0327
-5.750 -0.3040 0.01175 0.00479 -0.0696 0.8565 0.0352
-5.500 -0.2746 0.01147 0.00453 -0.0702 0.8525 0.0384
-5.250 -0.2453 0.01123 0.00428 -0.0706 0.8484 0.0424
-5.000 -0.2160 0.01099 0.00406 -0.0711 0.8444 0.0479
-4.750 -0.1866 0.01076 0.00383 -0.0715 0.8410 0.0551
-4.500 -0.1568 0.01053 0.00364 -0.0721 0.8377 0.0650
-4.250 -0.1269 0.01029 0.00346 -0.0727 0.8338 0.0799
-4.000 -0.0969 0.01000 0.00327 -0.0734 0.8299 0.1039
-3.750 -0.0667 0.00966 0.00307 -0.0742 0.8264 0.1429
-3.250 -0.0047 0.00874 0.00269 -0.0765 0.8199 0.2865
-3.000 0.0273 0.00816 0.00248 -0.0780 0.8162 0.3887
-2.750 0.0597 0.00762 0.00237 -0.0795 0.8127 0.5085
-2.500 0.0905 0.00744 0.00237 -0.0802 0.8095 0.5673
-2.250 0.1207 0.00740 0.00239 -0.0806 0.8063 0.5994
-2.000 0.1510 0.00739 0.00243 -0.0810 0.8024 0.6266
-1.750 0.1809 0.00740 0.00251 -0.0813 0.7984 0.6500
-1.500 0.2105 0.00743 0.00248 -0.0816 0.7922 0.6604
-1.250 0.2393 0.00743 0.00244 -0.0815 0.7772 0.6679
-1.000 0.2679 0.00746 0.00237 -0.0814 0.7559 0.6775
-0.750 0.2966 0.00750 0.00238 -0.0814 0.7391 0.6859
-0.500 0.3262 0.00756 0.00235 -0.0817 0.7261 0.6917
-0.250 0.3554 0.00758 0.00235 -0.0819 0.7120 0.6949
0.000 0.3844 0.00763 0.00235 -0.0820 0.6946 0.6982
0.250 0.4133 0.00771 0.00235 -0.0821 0.6725 0.7016
0.500 0.4418 0.00784 0.00236 -0.0822 0.6425 0.7051
0.750 0.4694 0.00808 0.00238 -0.0821 0.5960 0.7086
1.000 0.4944 0.00857 0.00252 -0.0817 0.5163 0.7114
1.250 0.5188 0.00919 0.00276 -0.0812 0.4318 0.7142
1.500 0.5440 0.00974 0.00300 -0.0810 0.3627 0.7174
1.750 0.5702 0.01018 0.00319 -0.0809 0.3124 0.7208
2.000 0.5969 0.01056 0.00338 -0.0808 0.2715 0.7240
2.250 0.6237 0.01091 0.00356 -0.0808 0.2385 0.7269
2.500 0.6504 0.01120 0.00375 -0.0807 0.2130 0.7298
2.750 0.6772 0.01150 0.00395 -0.0806 0.1913 0.7327
3.250 0.7313 0.01205 0.00433 -0.0806 0.1596 0.7392
3.500 0.7587 0.01229 0.00452 -0.0806 0.1492 0.7424
3.750 0.7855 0.01253 0.00473 -0.0805 0.1403 0.7451
4.000 0.8124 0.01276 0.00495 -0.0804 0.1327 0.7480
4.250 0.8391 0.01301 0.00518 -0.0802 0.1264 0.7512
4.500 0.8660 0.01324 0.00541 -0.0802 0.1208 0.7546
4.750 0.8924 0.01353 0.00565 -0.0800 0.1151 0.7578
5.000 0.9190 0.01377 0.00590 -0.0799 0.1112 0.7608
5.250 0.9452 0.01401 0.00616 -0.0797 0.1077 0.7638
5.500 0.9711 0.01429 0.00644 -0.0794 0.1042 0.7670
5.750 0.9965 0.01461 0.00676 -0.0791 0.1008 0.7703
6.000 1.0227 0.01487 0.00705 -0.0789 0.0990 0.7738
6.250 1.0484 0.01514 0.00735 -0.0786 0.0970 0.7771
6.500 1.0735 0.01542 0.00768 -0.0782 0.0948 0.7802
6.750 1.0983 0.01574 0.00801 -0.0778 0.0925 0.7835
7.000 1.1226 0.01610 0.00837 -0.0773 0.0901 0.7870
7.250 1.1463 0.01651 0.00880 -0.0768 0.0880 0.7909
7.500 1.1708 0.01681 0.00917 -0.0763 0.0869 0.7944
7.750 1.1947 0.01713 0.00956 -0.0757 0.0857 0.7979
8.000 1.2183 0.01747 0.00996 -0.0751 0.0843 0.8017
8.250 1.2417 0.01783 0.01036 -0.0745 0.0826 0.8057
8.500 1.2646 0.01820 0.01075 -0.0738 0.0805 0.8096
8.750 1.2862 0.01863 0.01120 -0.0729 0.0783 0.8136
9.000 1.3066 0.01914 0.01175 -0.0719 0.0764 0.8182
9.250 1.3289 0.01949 0.01218 -0.0711 0.0754 0.8228
9.500 1.3502 0.01988 0.01264 -0.0702 0.0741 0.8270
9.750 1.3706 0.02027 0.01312 -0.0691 0.0726 0.8316
10.000 1.3901 0.02069 0.01360 -0.0679 0.0710 0.8368
10.250 1.4068 0.02114 0.01409 -0.0662 0.0695 0.8424
10.500 1.4231 0.02165 0.01466 -0.0645 0.0679 0.8485
10.750 1.4385 0.02232 0.01537 -0.0628 0.0661 0.8551
11.000 1.4568 0.02278 0.01595 -0.0615 0.0651 0.8615
11.250 1.4744 0.02330 0.01656 -0.0602 0.0637 0.8690
11.500 1.4914 0.02384 0.01720 -0.0588 0.0620 0.8770
11.750 1.5076 0.02444 0.01787 -0.0574 0.0603 0.8872
12.000 1.5222 0.02508 0.01859 -0.0558 0.0587 0.9002
12.250 1.5339 0.02582 0.01940 -0.0538 0.0569 0.9203
12.500 1.5444 0.02634 0.02007 -0.0514 0.0557 1.0000
12.750 1.5607 0.02712 0.02092 -0.0504 0.0538 1.0000
13.000 1.5759 0.02797 0.02182 -0.0493 0.0518 1.0000
13.250 1.5899 0.02893 0.02280 -0.0481 0.0499 1.0000
13.500 1.6033 0.02994 0.02389 -0.0470 0.0480 1.0000
13.750 1.6166 0.03097 0.02498 -0.0459 0.0458 1.0000
14.000 1.6285 0.03212 0.02617 -0.0447 0.0432 1.0000
14.250 1.6389 0.03341 0.02751 -0.0436 0.0410 1.0000
14.500 1.6491 0.03475 0.02891 -0.0424 0.0386 1.0000
14.750 1.6568 0.03630 0.03050 -0.0412 0.0361 1.0000
15.000 1.6640 0.03794 0.03221 -0.0401 0.0342 1.0000
15.250 1.6701 0.03971 0.03406 -0.0389 0.0325 1.0000
15.500 1.6742 0.04170 0.03612 -0.0379 0.0310 1.0000
15.750 1.6769 0.04387 0.03836 -0.0369 0.0298 1.0000
16.000 1.6801 0.04603 0.04064 -0.0360 0.0288 1.0000
16.250 1.6813 0.04847 0.04317 -0.0353 0.0278 1.0000
16.500 1.6802 0.05123 0.04603 -0.0347 0.0267 1.0000
16.750 1.6771 0.05434 0.04924 -0.0344 0.0259 1.0000
17.000 1.6724 0.05779 0.05281 -0.0343 0.0252 1.0000
17.250 1.6693 0.06120 0.05636 -0.0345 0.0245 1.0000
17.500 1.6635 0.06509 0.06038 -0.0351 0.0238 1.0000
17.750 1.6550 0.06953 0.06496 -0.0360 0.0233 1.0000
18.000 1.6435 0.07465 0.07022 -0.0375 0.0227 1.0000
18.250 1.6284 0.08057 0.07629 -0.0396 0.0223 1.0000
18.500 1.6089 0.08746 0.08335 -0.0424 0.0220 1.0000
18.750 1.5848 0.09544 0.09151 -0.0461 0.0218 1.0000
19.000 1.5556 0.10463 0.10089 -0.0506 0.0216 1.0000
19.250 1.5210 0.11499 0.11146 -0.0560 0.0217 1.0000
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