NASA/LANGLEY MS(1)-0313 AIRFOIL (ms313-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: NASA/LANGLEY MS(1)-0313 AIRFOIL (ms313-il) Reynolds number: 1,000,000 Max Cl/Cd: 85.33 at α=8.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ms313-il-1000000.txt Download as CSV file: xf-ms313-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.250 -0.9908 0.07431 0.07164 -0.0457 1.0000 0.0116
-16.000 -1.0236 0.06412 0.06122 -0.0526 1.0000 0.0116
-15.750 -1.0427 0.05737 0.05428 -0.0568 1.0000 0.0116
-15.500 -1.0554 0.05213 0.04890 -0.0597 1.0000 0.0116
-15.250 -1.0635 0.04786 0.04450 -0.0618 1.0000 0.0116
-15.000 -1.0687 0.04423 0.04075 -0.0633 1.0000 0.0117
-14.750 -1.0703 0.04117 0.03757 -0.0643 1.0000 0.0118
-14.500 -1.0702 0.03846 0.03475 -0.0649 1.0000 0.0119
-14.250 -1.0677 0.03609 0.03228 -0.0653 1.0000 0.0120
-14.000 -1.0638 0.03395 0.03003 -0.0654 1.0000 0.0121
-13.750 -1.0584 0.03203 0.02801 -0.0653 1.0000 0.0122
-13.500 -1.0520 0.03028 0.02615 -0.0650 1.0000 0.0123
-13.250 -1.0449 0.02871 0.02447 -0.0644 1.0000 0.0125
-13.000 -1.0386 0.02730 0.02297 -0.0633 1.0000 0.0126
-12.750 -1.0300 0.02603 0.02160 -0.0624 1.0000 0.0128
-12.500 -1.0175 0.02491 0.02039 -0.0616 1.0000 0.0130
-12.250 -1.0072 0.02401 0.01941 -0.0598 1.0000 0.0131
-12.000 -0.9872 0.02310 0.01841 -0.0598 0.9983 0.0133
-11.750 -0.9569 0.02231 0.01752 -0.0615 0.9957 0.0136
-11.500 -0.9310 0.02059 0.01566 -0.0631 0.9928 0.0140
-11.250 -0.9040 0.01946 0.01447 -0.0644 0.9878 0.0144
-11.000 -0.8737 0.01870 0.01367 -0.0659 0.9838 0.0147
-10.750 -0.8456 0.01805 0.01297 -0.0667 0.9772 0.0150
-10.500 -0.8177 0.01742 0.01229 -0.0674 0.9706 0.0154
-10.250 -0.7929 0.01686 0.01166 -0.0674 0.9620 0.0158
-10.000 -0.7682 0.01633 0.01106 -0.0673 0.9544 0.0162
-9.750 -0.7434 0.01586 0.01052 -0.0671 0.9465 0.0166
-9.500 -0.7190 0.01534 0.00991 -0.0668 0.9395 0.0169
-9.250 -0.6951 0.01445 0.00898 -0.0668 0.9324 0.0176
-9.000 -0.6693 0.01405 0.00853 -0.0667 0.9259 0.0182
-8.750 -0.6426 0.01368 0.00813 -0.0668 0.9202 0.0188
-8.500 -0.6154 0.01332 0.00773 -0.0669 0.9144 0.0195
-8.250 -0.5883 0.01299 0.00734 -0.0670 0.9091 0.0201
-8.000 -0.5610 0.01250 0.00679 -0.0673 0.9041 0.0209
-7.750 -0.5332 0.01209 0.00638 -0.0676 0.8989 0.0220
-7.500 -0.5052 0.01182 0.00608 -0.0678 0.8939 0.0230
-7.250 -0.4769 0.01156 0.00578 -0.0681 0.8892 0.0240
-7.000 -0.4481 0.01119 0.00536 -0.0685 0.8849 0.0250
-6.750 -0.4194 0.01082 0.00500 -0.0689 0.8804 0.0266
-6.500 -0.3905 0.01061 0.00476 -0.0693 0.8761 0.0282
-6.250 -0.3614 0.01034 0.00445 -0.0697 0.8719 0.0301
-6.000 -0.3319 0.01005 0.00418 -0.0702 0.8677 0.0326
-5.750 -0.3024 0.00987 0.00398 -0.0706 0.8636 0.0346
-5.500 -0.2729 0.00958 0.00369 -0.0712 0.8598 0.0387
-5.250 -0.2433 0.00939 0.00348 -0.0716 0.8560 0.0428
-5.000 -0.2133 0.00917 0.00330 -0.0722 0.8523 0.0483
-4.750 -0.1832 0.00892 0.00310 -0.0728 0.8483 0.0570
-4.500 -0.1531 0.00869 0.00291 -0.0734 0.8447 0.0710
-4.250 -0.1229 0.00844 0.00274 -0.0741 0.8411 0.0946
-4.000 -0.0922 0.00809 0.00257 -0.0750 0.8376 0.1369
-3.750 -0.0607 0.00759 0.00237 -0.0762 0.8340 0.2121
-3.500 -0.0287 0.00703 0.00217 -0.0777 0.8305 0.3118
-3.250 0.0044 0.00633 0.00196 -0.0795 0.8272 0.4518
-3.000 0.0362 0.00601 0.00189 -0.0806 0.8236 0.5389
-2.750 0.0672 0.00587 0.00188 -0.0813 0.8203 0.5813
-2.500 0.0978 0.00582 0.00188 -0.0818 0.8166 0.6058
-2.250 0.1279 0.00580 0.00186 -0.0822 0.8115 0.6251
-2.000 0.1575 0.00579 0.00184 -0.0824 0.8023 0.6397
-1.750 0.1868 0.00579 0.00179 -0.0825 0.7890 0.6508
-1.500 0.2164 0.00579 0.00177 -0.0827 0.7773 0.6636
-1.250 0.2463 0.00585 0.00180 -0.0830 0.7695 0.6757
-1.000 0.2760 0.00585 0.00181 -0.0832 0.7617 0.6819
-0.750 0.3058 0.00588 0.00181 -0.0835 0.7533 0.6873
-0.500 0.3356 0.00593 0.00181 -0.0838 0.7440 0.6932
-0.250 0.3651 0.00595 0.00186 -0.0841 0.7359 0.7000
0.000 0.3948 0.00601 0.00188 -0.0843 0.7266 0.7057
0.250 0.4247 0.00606 0.00189 -0.0847 0.7149 0.7091
0.500 0.4539 0.00608 0.00189 -0.0849 0.6994 0.7125
0.750 0.4831 0.00615 0.00191 -0.0851 0.6808 0.7156
1.000 0.5120 0.00627 0.00194 -0.0852 0.6556 0.7187
1.250 0.5400 0.00650 0.00199 -0.0853 0.6103 0.7218
1.500 0.5658 0.00704 0.00215 -0.0850 0.5226 0.7248
1.750 0.5908 0.00768 0.00238 -0.0847 0.4304 0.7278
2.000 0.6163 0.00823 0.00261 -0.0845 0.3551 0.7307
2.250 0.6425 0.00869 0.00282 -0.0844 0.2977 0.7336
2.750 0.6961 0.00944 0.00320 -0.0843 0.2201 0.7397
3.000 0.7235 0.00973 0.00337 -0.0844 0.1952 0.7423
3.250 0.7507 0.00999 0.00354 -0.0843 0.1753 0.7455
3.500 0.7779 0.01024 0.00372 -0.0843 0.1593 0.7485
3.750 0.8053 0.01048 0.00390 -0.0843 0.1465 0.7514
4.000 0.8327 0.01071 0.00409 -0.0843 0.1364 0.7545
4.250 0.8599 0.01097 0.00429 -0.0843 0.1274 0.7575
4.500 0.8875 0.01117 0.00447 -0.0843 0.1219 0.7604
4.750 0.9141 0.01143 0.00470 -0.0842 0.1149 0.7636
5.000 0.9415 0.01160 0.00491 -0.0841 0.1119 0.7666
5.250 0.9686 0.01182 0.00512 -0.0840 0.1084 0.7699
5.500 0.9952 0.01208 0.00535 -0.0839 0.1046 0.7731
5.750 1.0213 0.01242 0.00567 -0.0837 0.1005 0.7760
6.000 1.0483 0.01257 0.00587 -0.0836 0.0990 0.7795
6.250 1.0749 0.01277 0.00611 -0.0834 0.0971 0.7828
6.500 1.1011 0.01302 0.00637 -0.0832 0.0950 0.7861
6.750 1.1269 0.01330 0.00665 -0.0830 0.0928 0.7895
7.000 1.1520 0.01366 0.00700 -0.0826 0.0902 0.7928
7.250 1.1759 0.01406 0.00745 -0.0820 0.0879 0.7965
7.500 1.2020 0.01425 0.00769 -0.0818 0.0871 0.8001
7.750 1.2279 0.01446 0.00792 -0.0816 0.0856 0.8038
8.000 1.2534 0.01471 0.00820 -0.0813 0.0839 0.8074
8.250 1.2782 0.01498 0.00849 -0.0808 0.0822 0.8112
8.500 1.3022 0.01530 0.00883 -0.0803 0.0805 0.8153
8.750 1.3248 0.01574 0.00930 -0.0795 0.0783 0.8195
9.000 1.3464 0.01625 0.00985 -0.0786 0.0764 0.8237
9.250 1.3708 0.01647 0.01012 -0.0782 0.0757 0.8279
9.500 1.3948 0.01671 0.01042 -0.0776 0.0746 0.8324
9.750 1.4182 0.01700 0.01075 -0.0770 0.0733 0.8373
10.000 1.4411 0.01729 0.01108 -0.0763 0.0719 0.8423
10.250 1.4630 0.01762 0.01144 -0.0755 0.0703 0.8475
10.500 1.4833 0.01805 0.01190 -0.0744 0.0685 0.8532
10.750 1.4989 0.01874 0.01264 -0.0725 0.0662 0.8590
11.000 1.5205 0.01896 0.01293 -0.0716 0.0655 0.8654
11.500 1.5578 0.01955 0.01366 -0.0688 0.0630 0.8813
11.750 1.5761 0.01993 0.01410 -0.0674 0.0614 0.8909
12.250 1.6057 0.02103 0.01530 -0.0637 0.0569 0.9218
12.500 1.6189 0.02122 0.01563 -0.0613 0.0558 1.0000
12.750 1.6379 0.02172 0.01616 -0.0604 0.0538 1.0000
13.000 1.6551 0.02235 0.01678 -0.0592 0.0512 1.0000
13.250 1.6702 0.02312 0.01756 -0.0579 0.0485 1.0000
13.500 1.6869 0.02377 0.01826 -0.0568 0.0462 1.0000
13.750 1.7009 0.02464 0.01911 -0.0554 0.0433 1.0000
14.000 1.7140 0.02558 0.02008 -0.0540 0.0409 1.0000
14.250 1.7268 0.02655 0.02109 -0.0526 0.0387 1.0000
14.500 1.7369 0.02774 0.02229 -0.0510 0.0363 1.0000
14.750 1.7479 0.02889 0.02349 -0.0496 0.0346 1.0000
15.000 1.7577 0.03013 0.02478 -0.0482 0.0330 1.0000
15.250 1.7651 0.03159 0.02628 -0.0466 0.0314 1.0000
15.500 1.7715 0.03318 0.02792 -0.0451 0.0299 1.0000
15.750 1.7802 0.03458 0.02940 -0.0439 0.0290 1.0000
16.000 1.7864 0.03622 0.03111 -0.0426 0.0279 1.0000
16.250 1.7903 0.03811 0.03307 -0.0413 0.0269 1.0000
16.500 1.7913 0.04033 0.03535 -0.0399 0.0258 1.0000
16.750 1.7940 0.04242 0.03753 -0.0388 0.0250 1.0000
17.000 1.7980 0.04443 0.03963 -0.0380 0.0243 1.0000
17.250 1.7995 0.04677 0.04206 -0.0372 0.0236 1.0000
17.500 1.7985 0.04946 0.04483 -0.0365 0.0228 1.0000
17.750 1.7944 0.05259 0.04804 -0.0360 0.0221 1.0000
18.000 1.7869 0.05629 0.05185 -0.0358 0.0213 1.0000
18.250 1.7825 0.05978 0.05545 -0.0359 0.0209 1.0000
18.500 1.7792 0.06325 0.05903 -0.0362 0.0204 1.0000
18.750 1.7720 0.06736 0.06327 -0.0369 0.0199 1.0000
19.000 1.7615 0.07214 0.06816 -0.0381 0.0195 1.0000
19.250 1.7470 0.07770 0.07386 -0.0398 0.0191 1.0000
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Polar data table (+)
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