NACA 2-H-15 AIRFOIL (n2h15-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 2-H-15 AIRFOIL (n2h15-il) Reynolds number: 500,000 Max Cl/Cd: 110.53 at α=6.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-n2h15-il-500000.txt Download as CSV file: xf-n2h15-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 2-H-15 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.0988 0.08916 0.08568 -0.0885 0.7093 0.0290
-10.000 -0.0977 0.08661 0.08315 -0.0890 0.7083 0.0292
-9.750 -0.0975 0.08405 0.08059 -0.0895 0.7074 0.0298
-9.500 -0.0989 0.08139 0.07795 -0.0901 0.7066 0.0303
-9.250 -0.1020 0.07863 0.07521 -0.0907 0.7057 0.0308
-9.000 -0.1137 0.07520 0.07180 -0.0921 0.7048 0.0317
-8.750 -0.1363 0.07115 0.06778 -0.0947 0.7038 0.0321
-8.500 -0.1589 0.06784 0.06444 -0.0944 0.7028 0.0322
-8.250 -0.1872 0.06496 0.06148 -0.0910 0.7015 0.0324
-8.000 -0.2106 0.06275 0.05924 -0.0860 0.6998 0.0325
-7.750 -0.2267 0.06108 0.05753 -0.0811 0.6979 0.0325
-7.500 -0.2469 0.05769 0.05406 -0.0764 0.6963 0.0326
-7.250 -0.2471 0.05519 0.05157 -0.0741 0.6949 0.0329
-7.000 -0.2450 0.05348 0.04985 -0.0716 0.6937 0.0331
-6.750 -0.2428 0.05178 0.04811 -0.0689 0.6925 0.0333
-6.500 -0.2407 0.04996 0.04621 -0.0660 0.6914 0.0334
-6.250 -0.2360 0.04836 0.04455 -0.0633 0.6905 0.0338
-6.000 -0.2306 0.04675 0.04286 -0.0605 0.6896 0.0342
-5.750 -0.2250 0.04503 0.04103 -0.0575 0.6887 0.0348
-5.500 -0.2192 0.04317 0.03904 -0.0543 0.6879 0.0353
-5.250 -0.2130 0.04128 0.03698 -0.0508 0.6870 0.0365
-5.000 -0.2128 0.04047 0.03561 -0.0438 0.6857 0.0386
-4.750 -0.2175 0.03682 0.03183 -0.0391 0.6832 0.0392
-4.500 -0.2040 0.03525 0.03028 -0.0374 0.6810 0.0396
-4.250 -0.1905 0.03409 0.02908 -0.0354 0.6794 0.0400
-4.000 -0.1757 0.03305 0.02799 -0.0334 0.6780 0.0406
-3.750 -0.1610 0.03198 0.02684 -0.0311 0.6768 0.0415
-3.500 -0.1453 0.03092 0.02564 -0.0288 0.6758 0.0430
-3.250 -0.1296 0.03191 0.02619 -0.0246 0.6748 0.0459
-3.000 -0.1198 0.02804 0.02217 -0.0217 0.6740 0.0473
-2.750 -0.0989 0.02687 0.02096 -0.0206 0.6733 0.0481
-2.500 -0.0778 0.02599 0.02001 -0.0194 0.6726 0.0497
-2.250 -0.0564 0.02529 0.01917 -0.0179 0.6720 0.0520
-2.000 -0.0395 0.02441 0.01796 -0.0152 0.6712 0.0566
-1.750 -0.0231 0.02441 0.01812 -0.0146 0.6659 0.0579
-1.500 -0.0005 0.02391 0.01759 -0.0139 0.6637 0.0600
-1.250 0.0198 0.02417 0.01774 -0.0121 0.6623 0.0645
-1.000 0.0769 0.02094 0.01396 -0.0167 0.6620 0.0468
-0.750 0.1580 0.01852 0.01145 -0.0281 0.6620 0.0405
-0.500 0.2146 0.01753 0.01046 -0.0345 0.6615 0.0406
-0.250 0.2549 0.01696 0.00989 -0.0374 0.6607 0.0405
0.000 0.2896 0.01655 0.00949 -0.0390 0.6600 0.0413
0.250 0.3208 0.01623 0.00919 -0.0398 0.6593 0.0423
0.500 0.3509 0.01594 0.00890 -0.0404 0.6587 0.0433
0.750 0.3804 0.01568 0.00863 -0.0408 0.6580 0.0448
1.000 0.4099 0.01543 0.00838 -0.0411 0.6574 0.0458
1.250 0.4403 0.01516 0.00810 -0.0417 0.6568 0.0474
1.500 0.4697 0.01503 0.00798 -0.0422 0.6562 0.0506
1.750 0.4840 0.01654 0.00964 -0.0416 0.6494 0.0531
2.000 0.5121 0.01655 0.00970 -0.0419 0.6479 0.0640
2.250 0.7737 0.01471 0.01025 -0.0908 0.6558 0.9937
2.500 0.8272 0.01493 0.01057 -0.0973 0.6524 0.9995
2.750 0.8482 0.01527 0.01096 -0.0970 0.6496 1.0000
3.000 0.8693 0.01540 0.01110 -0.0962 0.6478 1.0000
3.250 0.8926 0.01546 0.01116 -0.0956 0.6465 1.0000
3.500 0.9172 0.01544 0.01114 -0.0952 0.6454 1.0000
3.750 0.9431 0.01528 0.01097 -0.0949 0.6445 1.0000
4.000 0.9706 0.01488 0.01054 -0.0947 0.6435 1.0000
4.250 1.0006 0.01405 0.00966 -0.0945 0.6422 1.0000
4.500 1.0289 0.01366 0.00922 -0.0943 0.6409 1.0000
4.750 1.0514 0.01401 0.00970 -0.0940 0.6359 1.0000
5.000 1.0790 0.01366 0.00936 -0.0939 0.6325 1.0000
5.250 1.1111 0.01255 0.00818 -0.0939 0.6285 1.0000
5.500 1.1391 0.01207 0.00770 -0.0938 0.6222 1.0000
5.750 1.1671 0.01167 0.00732 -0.0938 0.6149 1.0000
6.000 1.1943 0.01144 0.00710 -0.0937 0.6083 1.0000
6.250 1.2206 0.01136 0.00708 -0.0936 0.5989 1.0000
6.500 1.2466 0.01134 0.00709 -0.0935 0.5844 1.0000
6.750 1.2711 0.01150 0.00722 -0.0933 0.5561 1.0000
7.000 1.2800 0.01360 0.00883 -0.0924 0.4621 1.0000
7.250 1.2522 0.01796 0.01285 -0.0879 0.3960 1.0000
7.500 1.2178 0.02022 0.01503 -0.0790 0.3764 1.0000
7.750 1.1815 0.02330 0.01790 -0.0713 0.3357 1.0000
8.000 1.1509 0.02650 0.02081 -0.0649 0.2861 1.0000
8.250 1.1242 0.02983 0.02379 -0.0595 0.2239 1.0000
8.500 1.1019 0.03313 0.02666 -0.0550 0.1525 1.0000
8.750 1.0915 0.03576 0.02895 -0.0518 0.0994 1.0000
9.000 1.0876 0.03800 0.03093 -0.0493 0.0621 1.0000
9.250 1.0941 0.03954 0.03242 -0.0477 0.0519 1.0000
9.500 1.1038 0.04085 0.03372 -0.0464 0.0473 1.0000
9.750 1.1115 0.04234 0.03520 -0.0449 0.0437 1.0000
10.000 1.1225 0.04361 0.03650 -0.0438 0.0413 1.0000
10.250 1.1326 0.04494 0.03787 -0.0427 0.0394 1.0000
10.500 1.1374 0.04675 0.03967 -0.0411 0.0368 1.0000
10.750 1.1488 0.04801 0.04098 -0.0402 0.0357 1.0000
11.000 1.1592 0.04939 0.04240 -0.0392 0.0345 1.0000
11.250 1.1691 0.05081 0.04384 -0.0381 0.0329 1.0000
11.500 1.1773 0.05238 0.04542 -0.0370 0.0318 1.0000
11.750 1.1794 0.05448 0.04755 -0.0355 0.0305 1.0000
12.000 1.1910 0.05581 0.04893 -0.0347 0.0299 1.0000
12.250 1.2016 0.05720 0.05038 -0.0338 0.0289 1.0000
12.500 1.2131 0.05851 0.05172 -0.0330 0.0279 1.0000
12.750 1.2226 0.05999 0.05323 -0.0321 0.0270 1.0000
13.000 1.2324 0.06147 0.05474 -0.0313 0.0266 1.0000
13.250 1.2387 0.06309 0.05634 -0.0299 0.0255 1.0000
13.500 1.2494 0.06438 0.05769 -0.0289 0.0250 1.0000
13.750 1.2609 0.06576 0.05914 -0.0282 0.0243 1.0000
14.000 1.2720 0.06714 0.06059 -0.0276 0.0236 1.0000
14.250 1.2830 0.06848 0.06197 -0.0268 0.0230 1.0000
14.500 1.2938 0.06986 0.06339 -0.0261 0.0224 1.0000
14.750 1.3038 0.07135 0.06489 -0.0254 0.0218 1.0000
15.000 1.3158 0.07231 0.06583 -0.0243 0.0211 1.0000
15.250 1.3289 0.07322 0.06680 -0.0232 0.0207 1.0000
15.500 1.3378 0.07493 0.06863 -0.0226 0.0203 1.0000
15.750 1.3481 0.07637 0.07017 -0.0218 0.0199 1.0000
16.000 1.3593 0.07767 0.07156 -0.0210 0.0197 1.0000
16.250 1.3671 0.07950 0.07349 -0.0204 0.0192 1.0000
16.500 1.3747 0.08137 0.07544 -0.0199 0.0187 1.0000
16.750 1.3814 0.08335 0.07750 -0.0194 0.0183 1.0000
17.000 1.3889 0.08517 0.07941 -0.0188 0.0181 1.0000
17.250 1.3949 0.08724 0.08155 -0.0184 0.0179 1.0000
17.500 1.4013 0.08917 0.08347 -0.0181 0.0174 1.0000
17.750 1.4120 0.09041 0.08481 -0.0167 0.0170 1.0000
18.000 1.4088 0.09386 0.08846 -0.0165 0.0169 1.0000
18.250 1.4052 0.09741 0.09219 -0.0166 0.0167 1.0000
18.500 1.4012 0.10108 0.09604 -0.0167 0.0164 1.0000
18.750 1.3965 0.10484 0.10000 -0.0168 0.0163 1.0000
19.000 1.3878 0.10934 0.10471 -0.0173 0.0160 1.0000
19.250 1.3791 0.11392 0.10948 -0.0178 0.0160 1.0000
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