NACA M9 AIRFOIL (m9-il) Xfoil prediction polar at RE=100,000 Ncrit=9
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Airfoil: NACA M9 AIRFOIL (m9-il) Reynolds number: 100,000 Max Cl/Cd: 43.54 at α=6.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-m9-il-100000.txt Download as CSV file: xf-m9-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: NACA M9 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.1625 0.10081 0.09724 -0.0175 0.9545 0.0804
-8.750 -0.1643 0.10039 0.09677 -0.0238 0.9238 0.0826
-8.500 -0.1741 0.10051 0.09686 -0.0266 0.8967 0.0830
-8.250 -0.1481 0.09208 0.08836 -0.0227 0.8794 0.0846
-8.000 -0.1381 0.08866 0.08489 -0.0211 0.8607 0.0865
-7.750 -0.1324 0.08607 0.08226 -0.0205 0.8439 0.0886
-7.500 -0.1284 0.08364 0.07980 -0.0205 0.8284 0.0913
-7.250 -0.1280 0.08175 0.07788 -0.0213 0.8141 0.0943
-7.000 -0.1398 0.08187 0.07800 -0.0237 0.8004 0.0961
-6.750 -0.1452 0.08176 0.07783 -0.0298 0.7885 0.0968
-6.500 -0.1243 0.07399 0.07007 -0.0230 0.7765 0.0993
-6.250 -0.1126 0.07093 0.06697 -0.0218 0.7645 0.1028
-6.000 -0.1067 0.06849 0.06445 -0.0224 0.7544 0.1068
-5.750 -0.0999 0.06843 0.06433 -0.0339 0.7420 0.1117
-5.500 -0.0906 0.06309 0.05899 -0.0314 0.7329 0.1131
-5.250 -0.0782 0.05937 0.05524 -0.0283 0.7231 0.1156
-5.000 -0.0639 0.05660 0.05244 -0.0288 0.7129 0.1206
-4.750 -0.0459 0.05388 0.04957 -0.0364 0.7048 0.1286
-4.500 -0.0395 0.06363 0.05899 -0.0404 0.7168 0.1308
-4.250 -0.0213 0.06136 0.05665 -0.0403 0.7066 0.1370
-4.000 0.0053 0.05886 0.05402 -0.0449 0.6964 0.1456
-3.750 0.0260 0.05701 0.05205 -0.0450 0.6880 0.1559
-3.500 0.0468 0.05452 0.04955 -0.0456 0.6779 0.1637
-3.250 0.0723 0.05247 0.04733 -0.0475 0.6708 0.1748
-3.000 0.0988 0.05066 0.04545 -0.0492 0.6613 0.1868
-2.750 0.1236 0.04887 0.04351 -0.0499 0.6546 0.1989
-2.500 0.1540 0.04734 0.04185 -0.0522 0.6459 0.2095
-2.250 0.2065 0.03823 0.03181 -0.0622 0.6405 0.1430
-2.000 0.2298 0.03621 0.02968 -0.0616 0.6346 0.1397
-1.750 0.2603 0.03319 0.02635 -0.0632 0.6266 0.1388
-1.500 0.2913 0.02849 0.02096 -0.0645 0.6216 0.1388
-1.250 0.3201 0.02587 0.01782 -0.0649 0.6159 0.1467
-1.000 0.3479 0.02527 0.01709 -0.0648 0.6088 0.1547
-0.750 0.3743 0.02555 0.01734 -0.0637 0.6035 0.1632
-0.500 0.4020 0.02550 0.01722 -0.0636 0.5960 0.1735
-0.250 0.4288 0.02591 0.01759 -0.0627 0.5893 0.1851
0.000 0.4557 0.02621 0.01779 -0.0618 0.5832 0.1972
0.250 0.4821 0.02663 0.01822 -0.0611 0.5745 0.2108
0.500 0.5088 0.02647 0.01785 -0.0598 0.5688 0.2271
0.750 0.5351 0.02654 0.01788 -0.0596 0.5591 0.2483
1.000 0.5612 0.02599 0.01714 -0.0585 0.5532 0.2740
1.250 0.5863 0.02567 0.01681 -0.0582 0.5448 0.3053
1.500 0.6124 0.02515 0.01610 -0.0574 0.5386 0.3401
1.750 0.6380 0.02474 0.01564 -0.0569 0.5324 0.3635
2.000 0.6643 0.02465 0.01552 -0.0567 0.5247 0.3804
2.250 0.6918 0.02430 0.01500 -0.0560 0.5193 0.3949
2.500 0.7177 0.02451 0.01526 -0.0559 0.5106 0.4051
2.750 0.7451 0.02432 0.01494 -0.0553 0.5041 0.4161
3.000 0.7726 0.02437 0.01505 -0.0553 0.4960 0.4264
3.250 0.8021 0.02430 0.01490 -0.0553 0.4884 0.4363
3.500 0.8307 0.02438 0.01497 -0.0553 0.4805 0.4418
3.750 0.8587 0.02441 0.01494 -0.0549 0.4718 0.4422
4.000 0.8857 0.02457 0.01508 -0.0546 0.4628 0.4412
4.250 0.9133 0.02452 0.01494 -0.0540 0.4539 0.4404
4.500 0.9388 0.02476 0.01523 -0.0535 0.4434 0.4399
4.750 0.9667 0.02462 0.01494 -0.0528 0.4354 0.4401
5.000 0.9908 0.02494 0.01535 -0.0523 0.4232 0.4404
5.250 1.0162 0.02510 0.01547 -0.0516 0.4129 0.4404
5.500 1.0425 0.02510 0.01538 -0.0508 0.4029 0.4399
5.750 1.0657 0.02548 0.01583 -0.0502 0.3905 0.4396
6.000 1.0906 0.02573 0.01601 -0.0495 0.3804 0.4394
6.250 1.1157 0.02592 0.01615 -0.0488 0.3708 0.4395
6.500 1.1382 0.02654 0.01687 -0.0482 0.3608 0.4398
6.750 1.1643 0.02674 0.01696 -0.0476 0.3538 0.4404
7.000 1.1854 0.02760 0.01798 -0.0470 0.3452 0.4411
7.250 1.2105 0.02797 0.01831 -0.0464 0.3390 0.4424
7.500 1.2329 0.02878 0.01920 -0.0458 0.3328 0.4439
7.750 1.2543 0.02956 0.02012 -0.0452 0.3263 0.4459
8.000 1.2809 0.02988 0.02034 -0.0448 0.3218 0.4498
8.250 1.2992 0.03106 0.02179 -0.0441 0.3162 0.4549
8.500 1.3189 0.03206 0.02298 -0.0435 0.3113 0.4641
8.750 1.3403 0.03238 0.02364 -0.0426 0.3078 0.6467
9.000 1.3831 0.03328 0.02497 -0.0462 0.3035 1.0000
9.250 1.3945 0.03510 0.02710 -0.0452 0.2990 1.0000
9.500 1.4122 0.03624 0.02835 -0.0443 0.2950 1.0000
9.750 1.4378 0.03663 0.02867 -0.0438 0.2915 1.0000
10.000 1.4547 0.03793 0.03009 -0.0429 0.2878 1.0000
10.250 1.4577 0.04017 0.03265 -0.0414 0.2834 1.0000
10.500 1.4719 0.04140 0.03399 -0.0404 0.2795 1.0000
10.750 1.4992 0.04163 0.03417 -0.0399 0.2762 1.0000
11.000 1.5143 0.04309 0.03573 -0.0390 0.2731 1.0000
11.250 1.4899 0.04732 0.04036 -0.0365 0.2702 1.0000
12.250 1.5024 0.05523 0.04868 -0.0311 0.2586 1.0000
13.000 0.9175 0.16256 0.15561 -0.0807 0.2930 0.4625
13.250 0.9737 0.16677 0.16068 -0.0809 0.2895 1.0000
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Polar data table (+)
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