NACA 63(2)-215 MOD B (n63215b-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 63(2)-215 MOD B (n63215b-il) Reynolds number: 50,000 Max Cl/Cd: 25.87 at α=3.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-n63215b-il-50000.txt Download as CSV file: xf-n63215b-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 63(2)-215 MOD B
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 -0.5775 0.09084 0.08363 -0.0357 1.0000 0.1539
-10.750 -0.5782 0.08517 0.07795 -0.0374 1.0000 0.1523
-10.500 -0.6956 0.07177 0.06435 -0.0461 1.0000 0.1376
-10.250 -0.7125 0.06752 0.06003 -0.0455 1.0000 0.1368
-10.000 -0.7297 0.06341 0.05578 -0.0446 1.0000 0.1361
-9.750 -0.7456 0.05960 0.05176 -0.0431 1.0000 0.1358
-9.500 -0.7559 0.05611 0.04801 -0.0414 1.0000 0.1359
-9.250 -0.7631 0.05293 0.04452 -0.0391 1.0000 0.1366
-9.000 -0.7670 0.05007 0.04133 -0.0366 1.0000 0.1373
-8.750 -0.7686 0.04749 0.03840 -0.0338 1.0000 0.1380
-8.500 -0.7619 0.04471 0.03550 -0.0315 1.0000 0.1395
-8.250 -0.7496 0.04261 0.03347 -0.0296 1.0000 0.1434
-8.000 -0.7425 0.04083 0.03155 -0.0270 1.0000 0.1475
-7.750 -0.7365 0.03904 0.02943 -0.0242 1.0000 0.1513
-7.500 -0.7263 0.03716 0.02730 -0.0218 1.0000 0.1548
-7.250 -0.7099 0.03550 0.02575 -0.0200 1.0000 0.1610
-7.000 -0.6977 0.03414 0.02414 -0.0178 1.0000 0.1687
-6.750 -0.6799 0.03267 0.02290 -0.0160 1.0000 0.1786
-6.500 -0.6629 0.03131 0.02162 -0.0140 1.0000 0.1906
-6.250 -0.6485 0.03007 0.02054 -0.0118 1.0000 0.2080
-6.000 -0.6367 0.02873 0.01940 -0.0094 1.0000 0.2343
-5.750 -0.6298 0.02704 0.01829 -0.0066 1.0000 0.2793
-5.500 -0.6306 0.02537 0.01799 -0.0021 1.0000 0.3952
-5.250 -0.6267 0.02681 0.02001 0.0048 1.0000 0.5143
-5.000 -0.6167 0.02876 0.02199 0.0109 1.0000 0.5645
-4.750 -0.6055 0.03082 0.02404 0.0174 1.0000 0.5998
-4.500 -0.5942 0.03261 0.02580 0.0235 1.0000 0.6297
-4.250 -0.5841 0.03398 0.02710 0.0293 1.0000 0.6587
-4.000 -0.5689 0.03575 0.02882 0.0355 1.0000 0.6829
-3.750 -0.5593 0.03627 0.02925 0.0401 1.0000 0.7082
-3.500 -0.5406 0.03729 0.03017 0.0446 1.0000 0.7301
-3.250 -0.5270 0.03753 0.03030 0.0482 1.0000 0.7527
-3.000 -0.5147 0.03753 0.03021 0.0515 1.0000 0.7748
-2.750 -0.4869 0.03799 0.03054 0.0532 1.0000 0.7961
-2.500 -0.4662 0.03783 0.03027 0.0545 1.0000 0.8150
-2.250 -0.4478 0.03741 0.02974 0.0554 1.0000 0.8311
-2.000 -0.4306 0.03689 0.02913 0.0561 1.0000 0.8457
-1.750 -0.4133 0.03638 0.02852 0.0566 1.0000 0.8600
-1.500 -0.3950 0.03592 0.02797 0.0568 1.0000 0.8743
-1.250 -0.3790 0.03542 0.02739 0.0571 1.0000 0.8881
-1.000 -0.3416 0.03535 0.02722 0.0540 1.0000 0.9000
-0.750 -0.3084 0.03522 0.02701 0.0512 1.0000 0.9116
-0.500 -0.2757 0.03514 0.02686 0.0482 1.0000 0.9236
-0.250 -0.1556 0.03675 0.02832 0.0296 0.9739 0.9325
0.000 -0.0441 0.03758 0.02905 0.0132 0.9462 0.9405
0.250 0.0535 0.03793 0.02936 -0.0001 0.9204 0.9496
0.500 0.1556 0.03763 0.02908 -0.0135 0.8931 0.9574
0.750 0.2497 0.03690 0.02841 -0.0247 0.8648 0.9659
1.000 0.3941 0.03445 0.02607 -0.0420 0.8306 0.9734
1.250 0.4799 0.03189 0.02360 -0.0486 0.7957 0.9819
1.500 0.5352 0.02952 0.02126 -0.0500 0.7569 0.9904
1.750 0.5755 0.02734 0.01904 -0.0490 0.7093 0.9991
2.000 0.5889 0.02617 0.01774 -0.0445 0.6597 1.0000
2.250 0.5993 0.02547 0.01683 -0.0402 0.6054 1.0000
2.500 0.6119 0.02506 0.01610 -0.0368 0.5577 1.0000
2.750 0.6249 0.02502 0.01574 -0.0341 0.5173 1.0000
3.000 0.6387 0.02519 0.01563 -0.0319 0.4855 1.0000
3.250 0.6535 0.02549 0.01567 -0.0301 0.4604 1.0000
3.500 0.6679 0.02592 0.01593 -0.0283 0.4382 1.0000
3.750 0.6830 0.02640 0.01621 -0.0267 0.4195 1.0000
4.000 0.6980 0.02701 0.01669 -0.0251 0.4036 1.0000
4.250 0.7126 0.02777 0.01737 -0.0236 0.3900 1.0000
4.500 0.7268 0.02859 0.01813 -0.0220 0.3777 1.0000
4.750 0.7421 0.02945 0.01882 -0.0204 0.3662 1.0000
5.000 0.7531 0.03039 0.01978 -0.0184 0.3551 1.0000
5.250 0.7620 0.03149 0.02093 -0.0162 0.3459 1.0000
5.500 0.7754 0.03255 0.02190 -0.0144 0.3368 1.0000
5.750 0.7769 0.03376 0.02332 -0.0113 0.3291 1.0000
6.000 0.7892 0.03491 0.02437 -0.0093 0.3210 1.0000
6.250 0.7938 0.03646 0.02612 -0.0068 0.3146 1.0000
6.500 0.8069 0.03812 0.02789 -0.0056 0.3078 1.0000
6.750 0.8271 0.03997 0.02972 -0.0052 0.3016 1.0000
7.000 0.8313 0.04234 0.03245 -0.0038 0.2955 1.0000
7.250 0.8544 0.04402 0.03406 -0.0037 0.2881 1.0000
7.500 0.8582 0.04681 0.03712 -0.0025 0.2826 1.0000
7.750 0.8550 0.05009 0.04071 -0.0012 0.2783 1.0000
8.000 0.8536 0.05357 0.04440 -0.0004 0.2751 1.0000
8.250 0.8905 0.05529 0.04594 -0.0010 0.2699 1.0000
8.500 0.8622 0.06051 0.05152 0.0005 0.2691 1.0000
8.750 0.8255 0.06673 0.05795 0.0013 0.2694 1.0000
9.000 0.4563 0.11429 0.10565 -0.0329 0.4569 1.0000
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Polar data table (+)
Polar graphs
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