NACA 16-015 (naca16015-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: NACA 16-015 (naca16015-il) Reynolds number: 100,000 Max Cl/Cd: 28.07 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca16015-il-100000-n5.txt Download as CSV file: xf-naca16015-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 16-015
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
------ -------- --------- --------- -------- -------- --------
-14.000 -0.6864 0.10070 0.09534 -0.0598 1.0000 0.0301
-13.750 -0.7174 0.09234 0.08692 -0.0634 1.0000 0.0297
-13.500 -0.7487 0.08555 0.08005 -0.0651 1.0000 0.0293
-13.250 -0.7799 0.07992 0.07428 -0.0651 1.0000 0.0290
-13.000 -0.8104 0.07515 0.06936 -0.0635 1.0000 0.0288
-12.750 -0.8396 0.07108 0.06511 -0.0607 1.0000 0.0288
-12.500 -0.8675 0.06755 0.06138 -0.0568 1.0000 0.0288
-12.250 -0.8938 0.06444 0.05807 -0.0521 1.0000 0.0289
-12.000 -0.9190 0.06164 0.05504 -0.0468 1.0000 0.0292
-11.750 -0.9431 0.05912 0.05227 -0.0408 1.0000 0.0295
-11.500 -0.9656 0.05682 0.04970 -0.0343 1.0000 0.0298
-11.250 -0.9869 0.05474 0.04733 -0.0275 1.0000 0.0302
-11.000 -1.0071 0.05289 0.04516 -0.0202 1.0000 0.0305
-10.750 -1.0252 0.05120 0.04315 -0.0129 1.0000 0.0308
-10.500 -1.0298 0.04909 0.04091 -0.0083 1.0000 0.0314
-10.250 -1.0305 0.04744 0.03913 -0.0041 1.0000 0.0321
-10.000 -1.0299 0.04604 0.03755 -0.0001 1.0000 0.0329
-9.750 -1.0280 0.04477 0.03612 0.0039 1.0000 0.0341
-9.500 -1.0242 0.04340 0.03453 0.0077 1.0000 0.0357
-9.250 -1.0172 0.04180 0.03261 0.0111 1.0000 0.0374
-9.000 -1.0063 0.04013 0.03054 0.0140 1.0000 0.0390
-8.750 -0.9900 0.03836 0.02866 0.0155 1.0000 0.0407
-8.500 -0.9749 0.03732 0.02757 0.0171 0.9994 0.0429
-8.250 -0.9512 0.03615 0.02619 0.0172 0.9978 0.0457
-8.000 -0.9233 0.03488 0.02464 0.0167 0.9964 0.0485
-7.750 -0.8957 0.03360 0.02330 0.0160 0.9951 0.0517
-7.500 -0.8703 0.03267 0.02232 0.0157 0.9934 0.0549
-7.250 -0.8452 0.03175 0.02129 0.0157 0.9916 0.0582
-7.000 -0.8210 0.03094 0.02031 0.0159 0.9898 0.0619
-6.750 -0.7992 0.03003 0.01943 0.0163 0.9879 0.0654
-6.500 -0.7763 0.02932 0.01864 0.0167 0.9859 0.0692
-6.250 -0.7548 0.02872 0.01791 0.0174 0.9836 0.0740
-6.000 -0.7388 0.02797 0.01721 0.0191 0.9808 0.0799
-5.750 -0.7194 0.02741 0.01653 0.0203 0.9782 0.0874
-5.500 -0.6991 0.02675 0.01592 0.0212 0.9758 0.0977
-5.250 -0.6783 0.02616 0.01538 0.0221 0.9735 0.1150
-5.000 -0.6635 0.02549 0.01487 0.0241 0.9702 0.1437
-4.750 -0.6470 0.02468 0.01441 0.0257 0.9674 0.2027
-4.500 -0.6324 0.02357 0.01395 0.0275 0.9648 0.3184
-4.250 -0.6222 0.02217 0.01363 0.0305 0.9626 0.5097
-4.000 -0.5179 0.02457 0.01713 0.0184 0.9684 0.7787
-3.750 -0.4911 0.02539 0.01783 0.0194 0.9658 0.8092
-3.500 -0.4598 0.02625 0.01855 0.0194 0.9641 0.8289
-3.250 -0.4169 0.02772 0.01987 0.0176 0.9633 0.8506
-3.000 -0.3604 0.02939 0.02139 0.0131 0.9635 0.8684
-2.750 -0.3270 0.02981 0.02167 0.0118 0.9617 0.8789
-2.500 -0.2938 0.03002 0.02177 0.0103 0.9590 0.8840
-2.250 -0.2734 0.03002 0.02168 0.0112 0.9553 0.8922
-2.000 -0.2347 0.03015 0.02170 0.0084 0.9534 0.8953
-1.750 -0.2011 0.03022 0.02169 0.0065 0.9513 0.9001
-1.500 -0.1741 0.03022 0.02160 0.0059 0.9492 0.9064
-1.250 -0.1451 0.03026 0.02160 0.0050 0.9453 0.9095
-0.750 -0.0960 0.03024 0.02149 0.0049 0.9382 0.9202
-0.500 -0.0571 0.03025 0.02148 0.0018 0.9364 0.9222
-0.250 -0.0212 0.03027 0.02148 -0.0006 0.9342 0.9246
0.000 0.0000 0.03028 0.02150 0.0000 0.9288 0.9288
0.250 0.0211 0.03027 0.02148 0.0007 0.9246 0.9342
0.500 0.0571 0.03025 0.02148 -0.0018 0.9222 0.9364
0.750 0.0960 0.03023 0.02149 -0.0049 0.9202 0.9383
1.250 0.1451 0.03025 0.02159 -0.0050 0.9095 0.9453
1.500 0.1742 0.03021 0.02160 -0.0059 0.9064 0.9492
1.750 0.2012 0.03021 0.02168 -0.0065 0.9001 0.9513
2.000 0.2347 0.03014 0.02169 -0.0084 0.8954 0.9534
2.250 0.2734 0.03001 0.02167 -0.0112 0.8922 0.9554
2.500 0.2938 0.03001 0.02176 -0.0103 0.8840 0.9590
2.750 0.3268 0.02981 0.02166 -0.0118 0.8789 0.9617
3.000 0.3605 0.02938 0.02137 -0.0131 0.8685 0.9635
3.250 0.4171 0.02771 0.01985 -0.0176 0.8506 0.9633
3.500 0.4601 0.02623 0.01853 -0.0194 0.8289 0.9641
3.750 0.4912 0.02538 0.01782 -0.0195 0.8093 0.9659
4.000 0.5182 0.02455 0.01711 -0.0185 0.7786 0.9684
4.250 0.6223 0.02217 0.01362 -0.0305 0.5081 0.9627
4.500 0.6326 0.02356 0.01394 -0.0275 0.3184 0.9648
4.750 0.6472 0.02467 0.01440 -0.0257 0.2025 0.9674
5.000 0.6636 0.02548 0.01486 -0.0241 0.1438 0.9703
5.250 0.6783 0.02615 0.01537 -0.0221 0.1150 0.9736
5.500 0.6993 0.02674 0.01591 -0.0213 0.0977 0.9759
5.750 0.7196 0.02740 0.01652 -0.0204 0.0874 0.9783
6.000 0.7390 0.02796 0.01720 -0.0192 0.0799 0.9809
6.250 0.7550 0.02871 0.01790 -0.0175 0.0740 0.9837
6.500 0.7766 0.02930 0.01863 -0.0167 0.0691 0.9859
6.750 0.7995 0.03002 0.01941 -0.0164 0.0654 0.9879
7.000 0.8213 0.03093 0.02030 -0.0160 0.0618 0.9899
7.250 0.8455 0.03175 0.02128 -0.0158 0.0582 0.9917
7.500 0.8707 0.03266 0.02231 -0.0158 0.0549 0.9935
7.750 0.8961 0.03359 0.02329 -0.0161 0.0517 0.9951
8.000 0.9236 0.03487 0.02463 -0.0168 0.0485 0.9965
8.250 0.9516 0.03614 0.02618 -0.0173 0.0457 0.9979
8.500 0.9753 0.03732 0.02757 -0.0172 0.0428 0.9995
8.750 0.9900 0.03834 0.02864 -0.0155 0.0407 1.0000
9.000 1.0063 0.04012 0.03053 -0.0140 0.0390 1.0000
9.250 1.0173 0.04179 0.03259 -0.0111 0.0374 1.0000
9.500 1.0242 0.04340 0.03453 -0.0077 0.0357 1.0000
9.750 1.0282 0.04477 0.03612 -0.0040 0.0341 1.0000
10.000 1.0300 0.04603 0.03754 0.0000 0.0329 1.0000
10.250 1.0307 0.04743 0.03912 0.0041 0.0321 1.0000
10.500 1.0300 0.04908 0.04090 0.0083 0.0314 1.0000
10.750 1.0252 0.05118 0.04314 0.0130 0.0308 1.0000
11.000 1.0072 0.05288 0.04516 0.0202 0.0305 1.0000
11.250 0.9870 0.05473 0.04732 0.0275 0.0301 1.0000
11.500 0.9659 0.05680 0.04968 0.0343 0.0298 1.0000
11.750 0.9432 0.05910 0.05225 0.0408 0.0294 1.0000
12.000 0.9195 0.06162 0.05501 0.0467 0.0292 1.0000
12.250 0.8943 0.06441 0.05803 0.0521 0.0289 1.0000
12.500 0.8677 0.06753 0.06137 0.0568 0.0288 1.0000
12.750 0.8399 0.07106 0.06509 0.0607 0.0287 1.0000
13.000 0.8108 0.07512 0.06932 0.0635 0.0288 1.0000
13.250 0.7803 0.07988 0.07424 0.0651 0.0290 1.0000
13.500 0.7488 0.08556 0.08006 0.0651 0.0292 1.0000
13.750 0.7178 0.09232 0.08689 0.0634 0.0297 1.0000
14.000 0.6865 0.10078 0.09542 0.0597 0.0301 1.0000
|
Polar data table (+)
Polar graphs
<< Back to NACA 16-015 (naca16015-il)