NACA 0015 (naca0015-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: NACA 0015 (naca0015-il) Reynolds number: 100,000 Max Cl/Cd: 37.8 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca0015-il-100000-n5.txt Download as CSV file: xf-naca0015-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 0015
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
------ -------- --------- --------- -------- -------- --------
-16.250 -0.9329 0.10524 0.09877 -0.0212 1.0000 0.0569
-16.000 -0.9892 0.09122 0.08440 -0.0301 1.0000 0.0569
-15.750 -1.0223 0.08241 0.07530 -0.0351 1.0000 0.0570
-15.500 -1.0467 0.07555 0.06816 -0.0386 1.0000 0.0573
-15.250 -1.0656 0.06986 0.06218 -0.0411 1.0000 0.0577
-15.000 -1.0637 0.06704 0.05934 -0.0416 1.0000 0.0584
-14.750 -1.0633 0.06414 0.05638 -0.0422 1.0000 0.0591
-14.500 -1.0648 0.06110 0.05325 -0.0428 1.0000 0.0600
-14.250 -1.0671 0.05805 0.05007 -0.0433 1.0000 0.0609
-14.000 -1.0692 0.05509 0.04696 -0.0435 1.0000 0.0619
-13.750 -1.0705 0.05230 0.04399 -0.0435 1.0000 0.0630
-13.500 -1.0704 0.04968 0.04117 -0.0432 1.0000 0.0641
-13.250 -1.0690 0.04726 0.03850 -0.0427 1.0000 0.0653
-13.000 -1.0614 0.04543 0.03664 -0.0419 1.0000 0.0664
-12.750 -1.0540 0.04372 0.03491 -0.0411 1.0000 0.0676
-12.500 -1.0473 0.04203 0.03316 -0.0402 1.0000 0.0691
-12.250 -1.0403 0.04040 0.03143 -0.0391 1.0000 0.0709
-12.000 -1.0326 0.03883 0.02969 -0.0379 1.0000 0.0730
-11.750 -1.0240 0.03735 0.02812 -0.0365 1.0000 0.0749
-11.500 -1.0157 0.03603 0.02680 -0.0350 1.0000 0.0769
-11.250 -1.0067 0.03479 0.02551 -0.0334 1.0000 0.0792
-11.000 -0.9969 0.03359 0.02421 -0.0316 1.0000 0.0819
-10.750 -0.9872 0.03244 0.02299 -0.0297 1.0000 0.0847
-10.500 -0.9795 0.03139 0.02195 -0.0274 1.0000 0.0875
-10.250 -0.9702 0.03044 0.02095 -0.0251 1.0000 0.0912
-10.000 -0.9593 0.02951 0.01995 -0.0230 1.0000 0.0954
-9.750 -0.9493 0.02858 0.01905 -0.0207 1.0000 0.0994
-9.500 -0.9364 0.02776 0.01815 -0.0187 1.0000 0.1047
-9.250 -0.9249 0.02691 0.01733 -0.0165 1.0000 0.1098
-9.000 -0.9118 0.02616 0.01655 -0.0144 1.0000 0.1162
-8.750 -0.8991 0.02541 0.01582 -0.0122 1.0000 0.1228
-8.500 -0.8854 0.02475 0.01513 -0.0100 1.0000 0.1308
-8.250 -0.8725 0.02407 0.01449 -0.0078 1.0000 0.1388
-8.000 -0.8580 0.02347 0.01388 -0.0057 1.0000 0.1484
-7.750 -0.8440 0.02287 0.01332 -0.0035 1.0000 0.1587
-7.500 -0.8298 0.02229 0.01280 -0.0014 1.0000 0.1697
-7.250 -0.8149 0.02176 0.01229 0.0007 1.0000 0.1820
-7.000 -0.7996 0.02126 0.01182 0.0027 1.0000 0.1954
-6.750 -0.7840 0.02079 0.01138 0.0047 1.0000 0.2099
-6.500 -0.7683 0.02034 0.01097 0.0067 1.0000 0.2251
-6.250 -0.7524 0.01991 0.01060 0.0086 1.0000 0.2409
-6.000 -0.7361 0.01951 0.01027 0.0105 1.0000 0.2575
-5.750 -0.7193 0.01914 0.00996 0.0123 1.0000 0.2746
-5.500 -0.7021 0.01881 0.00968 0.0140 1.0000 0.2923
-5.250 -0.6846 0.01850 0.00943 0.0157 1.0000 0.3103
-5.000 -0.6668 0.01822 0.00923 0.0172 1.0000 0.3287
-4.750 -0.6297 0.01791 0.00901 0.0150 0.9938 0.3531
-4.500 -0.5934 0.01764 0.00879 0.0129 0.9868 0.3780
-4.250 -0.5558 0.01738 0.00862 0.0107 0.9802 0.4030
-4.000 -0.5205 0.01713 0.00846 0.0090 0.9721 0.4279
-3.750 -0.4845 0.01690 0.00830 0.0072 0.9643 0.4530
-3.500 -0.4477 0.01667 0.00817 0.0054 0.9564 0.4777
-3.250 -0.4130 0.01646 0.00803 0.0040 0.9475 0.5019
-3.000 -0.3749 0.01624 0.00789 0.0020 0.9399 0.5261
-2.750 -0.3429 0.01604 0.00778 0.0014 0.9292 0.5486
-2.500 -0.3054 0.01583 0.00764 -0.0003 0.9214 0.5725
-2.250 -0.2758 0.01565 0.00753 -0.0004 0.9086 0.5947
-2.000 -0.2438 0.01548 0.00743 -0.0008 0.8972 0.6166
-1.750 -0.2093 0.01529 0.00733 -0.0016 0.8868 0.6386
-1.500 -0.1802 0.01516 0.00726 -0.0014 0.8725 0.6598
-1.250 -0.1501 0.01503 0.00719 -0.0013 0.8585 0.6811
-1.000 -0.1195 0.01491 0.00712 -0.0012 0.8443 0.7021
-0.750 -0.0890 0.01480 0.00704 -0.0011 0.8297 0.7226
-0.500 -0.0585 0.01473 0.00699 -0.0008 0.8143 0.7421
-0.250 -0.0293 0.01469 0.00697 -0.0004 0.7970 0.7610
0.000 0.0000 0.01468 0.00697 0.0000 0.7793 0.7793
0.250 0.0293 0.01469 0.00697 0.0004 0.7610 0.7970
0.500 0.0585 0.01473 0.00699 0.0008 0.7421 0.8143
0.750 0.0889 0.01480 0.00704 0.0011 0.7226 0.8297
1.000 0.1195 0.01491 0.00712 0.0012 0.7021 0.8443
1.250 0.1501 0.01503 0.00719 0.0013 0.6811 0.8585
1.500 0.1802 0.01515 0.00726 0.0014 0.6598 0.8725
1.750 0.2093 0.01529 0.00733 0.0016 0.6386 0.8868
2.000 0.2438 0.01548 0.00743 0.0008 0.6166 0.8972
2.250 0.2757 0.01565 0.00753 0.0004 0.5947 0.9087
2.500 0.3054 0.01583 0.00764 0.0003 0.5725 0.9214
2.750 0.3429 0.01604 0.00778 -0.0014 0.5487 0.9292
3.000 0.3749 0.01624 0.00789 -0.0020 0.5261 0.9399
3.250 0.4130 0.01646 0.00803 -0.0040 0.5019 0.9475
3.500 0.4477 0.01667 0.00817 -0.0054 0.4777 0.9565
3.750 0.4844 0.01690 0.00830 -0.0072 0.4530 0.9644
4.000 0.5205 0.01713 0.00845 -0.0090 0.4280 0.9721
4.250 0.5558 0.01738 0.00862 -0.0107 0.4030 0.9803
4.500 0.5934 0.01764 0.00879 -0.0129 0.3780 0.9868
4.750 0.6298 0.01791 0.00900 -0.0150 0.3531 0.9939
5.000 0.6667 0.01822 0.00922 -0.0172 0.3288 1.0000
5.250 0.6845 0.01850 0.00943 -0.0156 0.3103 1.0000
5.500 0.7020 0.01881 0.00967 -0.0140 0.2923 1.0000
5.750 0.7192 0.01914 0.00996 -0.0123 0.2746 1.0000
6.000 0.7359 0.01950 0.01026 -0.0105 0.2575 1.0000
6.250 0.7523 0.01990 0.01060 -0.0086 0.2409 1.0000
6.500 0.7682 0.02033 0.01097 -0.0067 0.2252 1.0000
6.750 0.7839 0.02078 0.01138 -0.0047 0.2099 1.0000
7.000 0.7995 0.02126 0.01181 -0.0027 0.1954 1.0000
7.250 0.8148 0.02176 0.01228 -0.0007 0.1820 1.0000
7.500 0.8297 0.02229 0.01279 0.0014 0.1697 1.0000
7.750 0.8440 0.02287 0.01332 0.0035 0.1587 1.0000
8.000 0.8580 0.02347 0.01388 0.0057 0.1484 1.0000
8.250 0.8725 0.02407 0.01449 0.0078 0.1388 1.0000
8.500 0.8854 0.02475 0.01513 0.0100 0.1308 1.0000
8.750 0.8992 0.02541 0.01582 0.0121 0.1228 1.0000
9.000 0.9119 0.02616 0.01655 0.0143 0.1162 1.0000
9.250 0.9250 0.02690 0.01732 0.0164 0.1098 1.0000
9.500 0.9366 0.02776 0.01815 0.0187 0.1046 1.0000
9.750 0.9495 0.02858 0.01905 0.0207 0.0994 1.0000
10.000 0.9596 0.02951 0.01994 0.0229 0.0953 1.0000
10.250 0.9706 0.03044 0.02095 0.0251 0.0912 1.0000
10.500 0.9799 0.03139 0.02195 0.0274 0.0875 1.0000
10.750 0.9877 0.03244 0.02298 0.0296 0.0847 1.0000
11.000 0.9975 0.03359 0.02421 0.0315 0.0819 1.0000
11.250 1.0074 0.03479 0.02551 0.0333 0.0792 1.0000
11.500 1.0163 0.03603 0.02680 0.0349 0.0768 1.0000
11.750 1.0247 0.03735 0.02811 0.0364 0.0749 1.0000
12.000 1.0334 0.03882 0.02969 0.0377 0.0729 1.0000
12.250 1.0411 0.04040 0.03142 0.0390 0.0709 1.0000
12.500 1.0482 0.04203 0.03315 0.0401 0.0691 1.0000
12.750 1.0550 0.04371 0.03490 0.0410 0.0676 1.0000
13.000 1.0625 0.04541 0.03663 0.0418 0.0664 1.0000
13.250 1.0700 0.04726 0.03850 0.0425 0.0653 1.0000
13.500 1.0716 0.04968 0.04116 0.0431 0.0641 1.0000
13.750 1.0717 0.05229 0.04398 0.0433 0.0629 1.0000
14.000 1.0706 0.05508 0.04695 0.0434 0.0618 1.0000
14.250 1.0686 0.05803 0.05005 0.0431 0.0608 1.0000
14.500 1.0665 0.06106 0.05321 0.0426 0.0599 1.0000
14.750 1.0652 0.06408 0.05632 0.0420 0.0591 1.0000
15.000 1.0658 0.06697 0.05926 0.0414 0.0583 1.0000
15.250 1.0669 0.06989 0.06222 0.0408 0.0577 1.0000
15.500 1.0480 0.07560 0.06821 0.0383 0.0573 1.0000
15.750 1.0235 0.08248 0.07538 0.0348 0.0570 1.0000
16.000 0.9901 0.09137 0.08456 0.0297 0.0568 1.0000
16.250 0.9327 0.10566 0.09919 0.0207 0.0569 1.0000
|
Polar data table (+)
Polar graphs
<< Back to NACA 0015 (naca0015-il)