NACA M9 AIRFOIL (m9-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA M9 AIRFOIL (m9-il) Reynolds number: 200,000 Max Cl/Cd: 63.84 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-m9-il-200000-n5.txt Download as CSV file: xf-m9-il-200000-n5.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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.2204 0.09182 0.08769 -0.0113 0.6872 0.0213
-7.750 -0.2161 0.08866 0.08454 -0.0126 0.6800 0.0215
-7.500 -0.2122 0.08561 0.08149 -0.0138 0.6725 0.0215
-7.250 -0.2093 0.08282 0.07869 -0.0148 0.6650 0.0213
-7.000 -0.2044 0.07929 0.07516 -0.0172 0.6573 0.0215
-6.750 -0.1959 0.07587 0.07170 -0.0197 0.6503 0.0215
-6.500 -0.1877 0.07100 0.06682 -0.0241 0.6430 0.0221
-6.250 -0.1746 0.06690 0.06267 -0.0280 0.6356 0.0230
-6.000 -0.1559 0.06513 0.06087 -0.0295 0.6263 0.0238
-5.750 -0.1378 0.06168 0.05735 -0.0329 0.6181 0.0249
-5.500 -0.1180 0.05638 0.05196 -0.0382 0.6100 0.0257
-5.250 -0.0884 0.02527 0.01935 -0.0666 0.6128 0.0324
-5.000 -0.0614 0.02282 0.01654 -0.0676 0.6029 0.0342
-4.750 -0.0340 0.02199 0.01554 -0.0677 0.5923 0.0363
-4.500 -0.0069 0.01995 0.01288 -0.0681 0.5829 0.0395
-4.250 0.0200 0.01930 0.01212 -0.0679 0.5725 0.0414
-4.000 0.0473 0.01891 0.01158 -0.0676 0.5635 0.0439
-3.750 0.0749 0.01808 0.01042 -0.0673 0.5543 0.0469
-3.500 0.1020 0.01744 0.00957 -0.0670 0.5461 0.0494
-3.250 0.1295 0.01714 0.00919 -0.0667 0.5373 0.0520
-3.000 0.1570 0.01669 0.00854 -0.0663 0.5296 0.0547
-2.750 0.1849 0.01626 0.00787 -0.0659 0.5215 0.0575
-2.250 0.2399 0.01558 0.00704 -0.0652 0.5080 0.0629
-2.000 0.2677 0.01536 0.00669 -0.0648 0.5018 0.0667
-1.750 0.2954 0.01514 0.00634 -0.0644 0.4965 0.0702
-1.500 0.3232 0.01497 0.00618 -0.0641 0.4904 0.0739
-1.250 0.3509 0.01486 0.00597 -0.0637 0.4840 0.0785
-1.000 0.3786 0.01477 0.00581 -0.0633 0.4775 0.0838
-0.750 0.4064 0.01469 0.00570 -0.0630 0.4699 0.0899
-0.500 0.4340 0.01466 0.00554 -0.0626 0.4638 0.0961
-0.250 0.4618 0.01457 0.00548 -0.0623 0.4580 0.1042
0.000 0.4896 0.01453 0.00537 -0.0620 0.4526 0.1120
0.250 0.5172 0.01449 0.00531 -0.0616 0.4478 0.1223
0.500 0.5449 0.01446 0.00530 -0.0613 0.4425 0.1348
0.750 0.5725 0.01470 0.00569 -0.0609 0.4362 0.1544
1.000 0.5990 0.01554 0.00670 -0.0603 0.4307 0.1806
1.250 0.6277 0.01555 0.00645 -0.0601 0.4254 0.2207
1.500 0.6552 0.01585 0.00669 -0.0597 0.4199 0.2313
1.750 0.6825 0.01608 0.00680 -0.0593 0.4147 0.2391
2.000 0.7095 0.01624 0.00694 -0.0589 0.4097 0.2450
2.250 0.7368 0.01633 0.00701 -0.0586 0.4041 0.2503
2.500 0.7638 0.01639 0.00705 -0.0583 0.3986 0.2538
2.750 0.7908 0.01650 0.00709 -0.0580 0.3934 0.2580
3.000 0.8180 0.01653 0.00714 -0.0577 0.3874 0.2616
3.250 0.8447 0.01657 0.00719 -0.0574 0.3818 0.2650
3.500 0.8715 0.01664 0.00723 -0.0571 0.3766 0.2667
3.750 0.8986 0.01669 0.00730 -0.0569 0.3703 0.2682
4.000 0.9251 0.01683 0.00740 -0.0566 0.3640 0.2713
4.250 0.9516 0.01684 0.00746 -0.0563 0.3573 0.2747
4.500 0.9779 0.01691 0.00755 -0.0560 0.3491 0.2774
4.750 1.0041 0.01700 0.00766 -0.0557 0.3408 0.2783
5.000 1.0300 0.01711 0.00777 -0.0554 0.3311 0.2785
5.250 1.0559 0.01724 0.00791 -0.0550 0.3210 0.2784
5.500 1.0812 0.01741 0.00807 -0.0546 0.3104 0.2782
5.750 1.1063 0.01761 0.00825 -0.0543 0.2983 0.2780
6.000 1.1310 0.01784 0.00848 -0.0538 0.2856 0.2779
6.250 1.1550 0.01812 0.00875 -0.0534 0.2733 0.2778
6.500 1.1785 0.01846 0.00905 -0.0529 0.2623 0.2778
6.750 1.2016 0.01884 0.00940 -0.0523 0.2527 0.2778
7.000 1.2243 0.01923 0.00979 -0.0517 0.2447 0.2778
7.250 1.2461 0.01969 0.01024 -0.0511 0.2373 0.2778
7.500 1.2678 0.02014 0.01069 -0.0504 0.2310 0.2779
7.750 1.2893 0.02060 0.01117 -0.0497 0.2255 0.2779
8.000 1.3093 0.02115 0.01172 -0.0489 0.2207 0.2780
8.250 1.3302 0.02161 0.01224 -0.0482 0.2172 0.2782
8.500 1.3511 0.02205 0.01277 -0.0474 0.2140 0.2784
8.750 1.3712 0.02255 0.01333 -0.0466 0.2109 0.2786
9.000 1.3901 0.02311 0.01395 -0.0457 0.2078 0.2789
9.250 1.4076 0.02375 0.01461 -0.0447 0.2051 0.2794
9.500 1.4245 0.02440 0.01530 -0.0435 0.2026 0.2801
9.750 1.4426 0.02492 0.01594 -0.0425 0.2005 0.2807
10.000 1.4592 0.02549 0.01664 -0.0414 0.1981 0.2813
10.250 1.4722 0.02611 0.01736 -0.0398 0.1955 0.2816
10.500 1.4834 0.02686 0.01818 -0.0381 0.1932 0.2819
10.750 1.4943 0.02773 0.01911 -0.0366 0.1912 0.2821
11.000 1.5052 0.02868 0.02012 -0.0353 0.1894 0.2824
11.250 1.5153 0.02975 0.02123 -0.0341 0.1872 0.2827
11.500 1.5262 0.03077 0.02239 -0.0332 0.1848 0.2829
11.750 1.5353 0.03197 0.02374 -0.0324 0.1810 0.2833
12.000 1.5421 0.03340 0.02526 -0.0318 0.1767 0.2836
12.250 1.5467 0.03510 0.02699 -0.0311 0.1729 0.2840
12.500 1.5530 0.03674 0.02874 -0.0307 0.1692 0.2841
12.750 1.5605 0.03835 0.03051 -0.0303 0.1655 0.2846
13.000 1.5649 0.04028 0.03254 -0.0301 0.1615 0.2849
13.250 1.5672 0.04245 0.03477 -0.0299 0.1582 0.2851
13.500 1.5704 0.04462 0.03706 -0.0298 0.1546 0.2855
13.750 1.5736 0.04688 0.03947 -0.0298 0.1498 0.2859
14.000 1.5725 0.04967 0.04234 -0.0301 0.1450 0.2864
14.250 1.5714 0.05252 0.04528 -0.0304 0.1407 0.2870
14.500 1.5696 0.05557 0.04845 -0.0309 0.1336 0.2873
14.750 1.5638 0.05919 0.05215 -0.0317 0.1274 0.2877
15.250 1.5454 0.06785 0.06092 -0.0340 0.1060 0.2885
15.500 1.5272 0.07367 0.06671 -0.0359 0.0928 0.2886
15.750 1.5016 0.08078 0.07379 -0.0385 0.0808 0.2884
16.000 1.4799 0.08755 0.08059 -0.0409 0.0736 0.2885
16.250 1.4635 0.09370 0.08682 -0.0432 0.0701 0.2888
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