NACA 16-018 (naca16018-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 16-018 (naca16018-il) Reynolds number: 200,000 Max Cl/Cd: 29.96 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca16018-il-200000-n5.txt Download as CSV file: xf-naca16018-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 16-018
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-18.500 -0.8658 0.11105 0.10655 -0.0678 1.0000 0.0218
-18.250 -0.9022 0.10147 0.09672 -0.0719 1.0000 0.0218
-18.000 -0.9247 0.09512 0.09021 -0.0739 1.0000 0.0219
-17.750 -0.9426 0.08991 0.08486 -0.0751 1.0000 0.0220
-17.500 -0.9585 0.08535 0.08018 -0.0756 1.0000 0.0222
-17.250 -0.9740 0.08110 0.07579 -0.0756 1.0000 0.0224
-17.000 -0.9883 0.07727 0.07183 -0.0752 1.0000 0.0226
-16.750 -1.0018 0.07375 0.06818 -0.0743 1.0000 0.0229
-16.500 -1.0150 0.07045 0.06473 -0.0730 1.0000 0.0232
-16.250 -1.0273 0.06742 0.06154 -0.0714 1.0000 0.0235
-16.000 -1.0350 0.06429 0.05823 -0.0705 0.9995 0.0240
-15.750 -1.0385 0.06114 0.05485 -0.0702 0.9985 0.0245
-15.500 -1.0405 0.05820 0.05167 -0.0696 0.9973 0.0251
-15.250 -1.0404 0.05552 0.04870 -0.0690 0.9961 0.0258
-15.000 -1.0367 0.05322 0.04622 -0.0684 0.9951 0.0264
-14.750 -1.0290 0.05144 0.04437 -0.0681 0.9941 0.0270
-14.500 -1.0223 0.04981 0.04266 -0.0673 0.9927 0.0277
-14.250 -1.0155 0.04826 0.04100 -0.0662 0.9912 0.0284
-14.000 -1.0075 0.04673 0.03933 -0.0651 0.9897 0.0293
-13.750 -0.9976 0.04524 0.03767 -0.0642 0.9883 0.0302
-13.500 -0.9855 0.04384 0.03605 -0.0635 0.9869 0.0312
-13.250 -0.9715 0.04246 0.03454 -0.0630 0.9858 0.0321
-13.000 -0.9568 0.04126 0.03329 -0.0627 0.9847 0.0331
-12.750 -0.9411 0.04019 0.03215 -0.0624 0.9839 0.0341
-12.500 -0.9312 0.03921 0.03109 -0.0606 0.9814 0.0351
-12.250 -0.9175 0.03825 0.03002 -0.0594 0.9795 0.0363
-12.000 -0.9012 0.03734 0.02896 -0.0586 0.9778 0.0375
-11.750 -0.8834 0.03635 0.02786 -0.0582 0.9763 0.0387
-11.500 -0.8658 0.03536 0.02685 -0.0578 0.9750 0.0399
-11.250 -0.8468 0.03452 0.02596 -0.0576 0.9739 0.0413
-11.000 -0.8270 0.03373 0.02510 -0.0575 0.9730 0.0428
-10.750 -0.8166 0.03307 0.02436 -0.0551 0.9700 0.0442
-10.500 -0.8017 0.03239 0.02357 -0.0537 0.9675 0.0454
-10.250 -0.7854 0.03153 0.02268 -0.0527 0.9655 0.0468
-10.000 -0.7677 0.03073 0.02187 -0.0520 0.9638 0.0486
-9.750 -0.7481 0.03005 0.02114 -0.0516 0.9625 0.0506
-9.500 -0.7275 0.02940 0.02041 -0.0513 0.9614 0.0528
-9.250 -0.7059 0.02878 0.01969 -0.0512 0.9605 0.0548
-9.000 -0.7051 0.02823 0.01915 -0.0466 0.9551 0.0566
-8.750 -0.6890 0.02761 0.01852 -0.0452 0.9526 0.0596
-8.500 -0.6697 0.02707 0.01793 -0.0445 0.9508 0.0635
-8.250 -0.6503 0.02646 0.01731 -0.0438 0.9493 0.0683
-8.000 -0.6289 0.02591 0.01675 -0.0435 0.9481 0.0749
-7.750 -0.6066 0.02532 0.01617 -0.0434 0.9471 0.0836
-7.250 -0.5920 0.02458 0.01546 -0.0363 0.9382 0.1027
-7.000 -0.5738 0.02405 0.01500 -0.0353 0.9363 0.1202
-6.750 -0.5543 0.02346 0.01452 -0.0345 0.9347 0.1440
-6.500 -0.5339 0.02283 0.01402 -0.0339 0.9334 0.1747
-6.250 -0.5373 0.02254 0.01382 -0.0280 0.9273 0.1975
-6.000 -0.5295 0.02197 0.01343 -0.0247 0.9238 0.2358
-5.750 -0.5196 0.02121 0.01292 -0.0219 0.9213 0.2909
-5.500 -0.5124 0.02025 0.01231 -0.0185 0.9191 0.3621
-5.250 -0.5289 0.01980 0.01209 -0.0097 0.9123 0.4111
-5.000 -0.5386 0.01899 0.01165 -0.0022 0.9075 0.4839
-4.750 -0.5406 0.01805 0.01130 0.0039 0.9047 0.5930
-4.500 -0.4619 0.01914 0.01306 -0.0060 0.9066 0.7263
-4.250 -0.4323 0.01937 0.01325 -0.0063 0.9053 0.7504
-4.000 -0.4030 0.01954 0.01337 -0.0067 0.9042 0.7659
-3.750 -0.3666 0.01994 0.01371 -0.0084 0.9035 0.7783
-3.500 -0.3619 0.02052 0.01429 -0.0033 0.8966 0.7888
-3.250 -0.3354 0.02122 0.01496 -0.0025 0.8941 0.8031
-3.000 -0.3055 0.02200 0.01570 -0.0024 0.8924 0.8155
-2.500 -0.2481 0.02235 0.01594 -0.0030 0.8895 0.8285
-2.250 -0.2073 0.02260 0.01613 -0.0059 0.8889 0.8297
-1.750 -0.1958 0.02278 0.01627 0.0028 0.8780 0.8432
-1.500 -0.1575 0.02297 0.01642 0.0003 0.8768 0.8441
-1.250 -0.1201 0.02310 0.01652 -0.0021 0.8758 0.8453
-0.750 -0.1058 0.02301 0.01640 0.0059 0.8660 0.8579
-0.500 -0.0719 0.02316 0.01653 0.0042 0.8639 0.8589
-0.250 -0.0361 0.02323 0.01659 0.0021 0.8623 0.8599
0.000 0.0000 0.02324 0.01661 0.0000 0.8610 0.8610
0.250 0.0361 0.02323 0.01659 -0.0022 0.8599 0.8623
0.500 0.0719 0.02316 0.01653 -0.0042 0.8589 0.8639
0.750 0.1057 0.02301 0.01640 -0.0059 0.8579 0.8660
1.250 0.1201 0.02310 0.01652 0.0021 0.8453 0.8758
1.500 0.1575 0.02296 0.01641 -0.0003 0.8441 0.8768
1.750 0.1957 0.02278 0.01627 -0.0028 0.8432 0.8780
2.250 0.2074 0.02259 0.01612 0.0059 0.8297 0.8889
2.500 0.2481 0.02234 0.01593 0.0029 0.8286 0.8895
3.000 0.3056 0.02199 0.01570 0.0024 0.8155 0.8924
3.250 0.3354 0.02121 0.01495 0.0025 0.8031 0.8942
3.500 0.3619 0.02051 0.01428 0.0033 0.7889 0.8967
3.750 0.3668 0.01993 0.01370 0.0084 0.7783 0.9035
4.000 0.4032 0.01953 0.01336 0.0066 0.7659 0.9042
4.250 0.4327 0.01935 0.01323 0.0062 0.7504 0.9053
4.500 0.4621 0.01913 0.01304 0.0059 0.7262 0.9066
4.750 0.5407 0.01805 0.01129 -0.0039 0.5920 0.9047
5.000 0.5387 0.01899 0.01164 0.0022 0.4838 0.9075
5.250 0.5289 0.01979 0.01208 0.0097 0.4111 0.9123
5.500 0.5126 0.02025 0.01230 0.0185 0.3619 0.9191
5.750 0.5198 0.02120 0.01291 0.0218 0.2910 0.9213
6.000 0.5297 0.02196 0.01342 0.0246 0.2357 0.9239
6.250 0.5373 0.02252 0.01380 0.0280 0.1975 0.9274
6.500 0.5342 0.02282 0.01401 0.0339 0.1746 0.9334
6.750 0.5546 0.02345 0.01451 0.0344 0.1439 0.9347
7.000 0.5742 0.02404 0.01498 0.0352 0.1201 0.9363
7.250 0.5923 0.02456 0.01544 0.0363 0.1027 0.9382
7.750 0.6072 0.02530 0.01616 0.0433 0.0835 0.9471
8.000 0.6295 0.02589 0.01673 0.0434 0.0749 0.9482
8.250 0.6508 0.02645 0.01730 0.0437 0.0683 0.9494
8.500 0.6703 0.02705 0.01791 0.0444 0.0635 0.9509
8.750 0.6895 0.02759 0.01850 0.0451 0.0596 0.9527
9.000 0.7055 0.02820 0.01912 0.0465 0.0566 0.9552
9.250 0.7067 0.02876 0.01967 0.0511 0.0548 0.9605
9.500 0.7284 0.02938 0.02038 0.0512 0.0528 0.9614
9.750 0.7490 0.03003 0.02111 0.0515 0.0506 0.9626
10.000 0.7686 0.03071 0.02184 0.0519 0.0486 0.9639
10.250 0.7862 0.03151 0.02265 0.0525 0.0468 0.9656
10.500 0.8024 0.03236 0.02354 0.0535 0.0454 0.9676
10.750 0.8170 0.03303 0.02432 0.0551 0.0442 0.9703
11.000 0.8282 0.03370 0.02507 0.0573 0.0428 0.9731
11.250 0.8481 0.03449 0.02593 0.0574 0.0413 0.9740
11.500 0.8671 0.03533 0.02682 0.0576 0.0399 0.9751
11.750 0.8847 0.03633 0.02784 0.0580 0.0387 0.9764
12.000 0.9025 0.03731 0.02893 0.0584 0.0375 0.9779
12.250 0.9187 0.03822 0.02998 0.0592 0.0363 0.9797
12.500 0.9322 0.03917 0.03105 0.0604 0.0351 0.9817
12.750 0.9428 0.04016 0.03211 0.0621 0.0341 0.9839
13.000 0.9584 0.04122 0.03325 0.0624 0.0330 0.9849
13.250 0.9731 0.04243 0.03450 0.0627 0.0321 0.9859
13.500 0.9872 0.04380 0.03601 0.0632 0.0311 0.9871
13.750 0.9993 0.04521 0.03763 0.0639 0.0302 0.9885
14.000 1.0092 0.04669 0.03929 0.0649 0.0292 0.9899
14.250 1.0172 0.04822 0.04096 0.0659 0.0284 0.9914
14.500 1.0241 0.04977 0.04262 0.0670 0.0276 0.9929
14.750 1.0312 0.05139 0.04431 0.0677 0.0270 0.9942
15.000 1.0390 0.05318 0.04617 0.0680 0.0264 0.9952
15.250 1.0426 0.05549 0.04867 0.0686 0.0258 0.9963
15.500 1.0426 0.05818 0.05165 0.0692 0.0251 0.9975
15.750 1.0407 0.06110 0.05482 0.0698 0.0245 0.9987
16.000 1.0374 0.06426 0.05820 0.0701 0.0239 0.9997
16.250 1.0284 0.06725 0.06137 0.0714 0.0235 1.0000
16.500 1.0162 0.07027 0.06455 0.0730 0.0232 1.0000
16.750 1.0035 0.07349 0.06790 0.0743 0.0229 1.0000
17.000 0.9902 0.07697 0.07152 0.0752 0.0226 1.0000
17.250 0.9761 0.08077 0.07545 0.0757 0.0224 1.0000
17.500 0.9612 0.08491 0.07971 0.0757 0.0222 1.0000
17.750 0.9456 0.08942 0.08435 0.0752 0.0220 1.0000
18.000 0.9285 0.09446 0.08951 0.0742 0.0218 1.0000
18.250 0.9056 0.10087 0.09609 0.0722 0.0217 1.0000
18.500 0.8781 0.10860 0.10400 0.0691 0.0217 1.0000
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