NACA 63012A AIRFOIL (n63012a-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 63012A AIRFOIL (n63012a-il) Reynolds number: 100,000 Max Cl/Cd: 38.28 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-n63012a-il-100000-n5.txt Download as CSV file: xf-n63012a-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 63012A 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.750 -0.7603 0.09822 0.09295 -0.0120 1.0000 0.0279
-12.500 -0.7822 0.08943 0.08408 -0.0179 1.0000 0.0277
-12.250 -0.8050 0.08166 0.07619 -0.0231 1.0000 0.0275
-12.000 -0.8271 0.07502 0.06940 -0.0271 1.0000 0.0274
-11.750 -0.8480 0.06938 0.06356 -0.0297 1.0000 0.0273
-11.500 -0.8675 0.06454 0.05852 -0.0311 1.0000 0.0273
-11.250 -0.8850 0.06039 0.05413 -0.0312 1.0000 0.0273
-11.000 -0.9004 0.05677 0.05025 -0.0300 1.0000 0.0273
-10.750 -0.9134 0.05360 0.04677 -0.0278 1.0000 0.0275
-10.500 -0.9216 0.05059 0.04337 -0.0254 1.0000 0.0279
-10.250 -0.9217 0.04751 0.04004 -0.0237 1.0000 0.0285
-10.000 -0.9145 0.04514 0.03752 -0.0224 1.0000 0.0292
-9.750 -0.9054 0.04296 0.03514 -0.0211 1.0000 0.0300
-9.500 -0.8946 0.04062 0.03253 -0.0197 1.0000 0.0306
-9.250 -0.8814 0.03827 0.02989 -0.0183 1.0000 0.0311
-9.000 -0.8656 0.03609 0.02743 -0.0171 1.0000 0.0318
-8.750 -0.8477 0.03406 0.02515 -0.0160 1.0000 0.0327
-8.500 -0.8281 0.03219 0.02302 -0.0150 1.0000 0.0336
-8.250 -0.8076 0.03054 0.02115 -0.0141 1.0000 0.0349
-8.000 -0.7870 0.02912 0.01954 -0.0131 1.0000 0.0366
-7.750 -0.7681 0.02767 0.01813 -0.0122 1.0000 0.0387
-7.500 -0.7486 0.02648 0.01691 -0.0112 1.0000 0.0407
-7.250 -0.7295 0.02531 0.01564 -0.0099 1.0000 0.0429
-7.000 -0.7112 0.02424 0.01446 -0.0085 1.0000 0.0453
-6.750 -0.6953 0.02313 0.01335 -0.0068 1.0000 0.0484
-6.500 -0.6785 0.02227 0.01249 -0.0052 1.0000 0.0533
-6.250 -0.6625 0.02139 0.01156 -0.0034 1.0000 0.0589
-6.000 -0.6469 0.02055 0.01071 -0.0016 1.0000 0.0666
-5.750 -0.6318 0.01972 0.00993 0.0004 1.0000 0.0782
-5.500 -0.6168 0.01890 0.00920 0.0023 1.0000 0.0967
-5.250 -0.6033 0.01794 0.00850 0.0043 1.0000 0.1319
-5.000 -0.5916 0.01683 0.00781 0.0064 1.0000 0.2034
-4.750 -0.5818 0.01562 0.00728 0.0088 1.0000 0.3197
-4.500 -0.5695 0.01488 0.00710 0.0112 1.0000 0.4328
-4.250 -0.5360 0.01454 0.00704 0.0098 0.9911 0.5208
-4.000 -0.5013 0.01444 0.00702 0.0084 0.9824 0.5747
-3.750 -0.4658 0.01443 0.00704 0.0070 0.9740 0.6165
-3.500 -0.4320 0.01446 0.00709 0.0060 0.9646 0.6494
-3.250 -0.3981 0.01449 0.00706 0.0050 0.9555 0.6755
-3.000 -0.3624 0.01451 0.00702 0.0037 0.9474 0.6947
-2.750 -0.3307 0.01447 0.00693 0.0030 0.9367 0.7098
-2.500 -0.2976 0.01441 0.00678 0.0020 0.9271 0.7225
-2.250 -0.2642 0.01433 0.00661 0.0010 0.9179 0.7344
-2.000 -0.2336 0.01428 0.00652 0.0006 0.9070 0.7441
-1.750 -0.2026 0.01422 0.00640 0.0001 0.8970 0.7544
-1.500 -0.1718 0.01414 0.00626 -0.0004 0.8874 0.7654
-1.250 -0.1431 0.01411 0.00621 -0.0003 0.8763 0.7750
-1.000 -0.1138 0.01407 0.00614 -0.0004 0.8660 0.7850
-0.750 -0.0846 0.01402 0.00604 -0.0005 0.8567 0.7959
-0.500 -0.0565 0.01401 0.00604 -0.0003 0.8455 0.8052
-0.250 -0.0283 0.01400 0.00602 -0.0001 0.8354 0.8152
0.000 0.0000 0.01398 0.00596 0.0000 0.8261 0.8261
0.250 0.0283 0.01400 0.00602 0.0001 0.8152 0.8354
0.500 0.0565 0.01402 0.00604 0.0003 0.8052 0.8455
0.750 0.0846 0.01402 0.00604 0.0005 0.7959 0.8567
1.000 0.1139 0.01407 0.00614 0.0004 0.7850 0.8660
1.250 0.1431 0.01411 0.00621 0.0003 0.7750 0.8763
1.500 0.1718 0.01414 0.00626 0.0004 0.7654 0.8874
1.750 0.2026 0.01422 0.00640 -0.0001 0.7544 0.8970
2.000 0.2336 0.01428 0.00652 -0.0006 0.7441 0.9070
2.250 0.2642 0.01433 0.00661 -0.0010 0.7344 0.9179
2.500 0.2976 0.01441 0.00678 -0.0021 0.7225 0.9271
2.750 0.3307 0.01447 0.00693 -0.0030 0.7098 0.9367
3.000 0.3625 0.01451 0.00702 -0.0037 0.6947 0.9474
3.250 0.3981 0.01449 0.00706 -0.0050 0.6755 0.9554
3.500 0.4320 0.01447 0.00709 -0.0060 0.6494 0.9646
3.750 0.4658 0.01443 0.00704 -0.0070 0.6165 0.9740
4.000 0.5013 0.01444 0.00702 -0.0084 0.5747 0.9824
4.250 0.5361 0.01454 0.00704 -0.0098 0.5208 0.9911
4.500 0.5696 0.01488 0.00710 -0.0112 0.4327 1.0000
4.750 0.5819 0.01562 0.00728 -0.0088 0.3196 1.0000
5.000 0.5917 0.01683 0.00782 -0.0065 0.2033 1.0000
5.250 0.6034 0.01794 0.00850 -0.0043 0.1317 1.0000
5.500 0.6168 0.01890 0.00920 -0.0023 0.0967 1.0000
5.750 0.6319 0.01972 0.00993 -0.0004 0.0781 1.0000
6.000 0.6470 0.02055 0.01071 0.0015 0.0666 1.0000
6.250 0.6625 0.02139 0.01157 0.0034 0.0589 1.0000
6.500 0.6786 0.02227 0.01249 0.0052 0.0533 1.0000
6.750 0.6953 0.02313 0.01335 0.0068 0.0484 1.0000
7.000 0.7112 0.02424 0.01446 0.0085 0.0453 1.0000
7.250 0.7295 0.02531 0.01564 0.0099 0.0429 1.0000
7.500 0.7486 0.02648 0.01691 0.0112 0.0407 1.0000
7.750 0.7681 0.02767 0.01813 0.0122 0.0387 1.0000
8.000 0.7870 0.02912 0.01954 0.0131 0.0366 1.0000
8.250 0.8076 0.03054 0.02115 0.0141 0.0349 1.0000
8.500 0.8282 0.03219 0.02302 0.0150 0.0336 1.0000
8.750 0.8477 0.03406 0.02515 0.0160 0.0327 1.0000
9.000 0.8656 0.03609 0.02743 0.0171 0.0318 1.0000
9.250 0.8814 0.03827 0.02989 0.0183 0.0311 1.0000
9.500 0.8946 0.04062 0.03253 0.0196 0.0306 1.0000
9.750 0.9055 0.04296 0.03514 0.0211 0.0300 1.0000
10.000 0.9147 0.04513 0.03751 0.0224 0.0292 1.0000
10.250 0.9219 0.04751 0.04004 0.0237 0.0284 1.0000
10.500 0.9217 0.05060 0.04338 0.0254 0.0279 1.0000
10.750 0.9136 0.05361 0.04679 0.0278 0.0275 1.0000
11.000 0.9006 0.05679 0.05027 0.0300 0.0273 1.0000
11.250 0.8853 0.06042 0.05416 0.0311 0.0273 1.0000
11.500 0.8678 0.06458 0.05856 0.0310 0.0273 1.0000
11.750 0.8484 0.06942 0.06362 0.0296 0.0273 1.0000
12.000 0.8275 0.07509 0.06947 0.0269 0.0274 1.0000
12.250 0.8054 0.08174 0.07628 0.0229 0.0275 1.0000
12.500 0.7827 0.08953 0.08419 0.0176 0.0277 1.0000
12.750 0.7607 0.09840 0.09313 0.0117 0.0279 1.0000
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