NACA 63(3)-018 (naca633018-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 63(3)-018 (naca633018-il) Reynolds number: 100,000 Max Cl/Cd: 40.72 at α=8.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca633018-il-100000.txt Download as CSV file: xf-naca633018-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 63(3)-018
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.000 -0.6636 0.17610 0.17090 0.0163 1.0000 0.1678
-15.750 -0.9043 0.10105 0.09567 -0.0239 1.0000 0.0958
-15.500 -0.9445 0.09156 0.08601 -0.0285 1.0000 0.0951
-15.250 -0.9834 0.08350 0.07774 -0.0320 1.0000 0.0946
-15.000 -1.0178 0.07683 0.07083 -0.0343 1.0000 0.0943
-14.750 -1.0481 0.07126 0.06502 -0.0356 1.0000 0.0943
-14.500 -1.0740 0.06659 0.06008 -0.0360 1.0000 0.0945
-14.250 -1.0969 0.06260 0.05581 -0.0357 1.0000 0.0949
-14.000 -1.1165 0.05922 0.05215 -0.0348 1.0000 0.0954
-13.750 -1.1331 0.05639 0.04902 -0.0332 1.0000 0.0959
-13.500 -1.1148 0.05286 0.04545 -0.0336 1.0000 0.0983
-13.250 -1.1034 0.05073 0.04327 -0.0332 1.0000 0.1007
-13.000 -1.0954 0.04863 0.04103 -0.0325 1.0000 0.1030
-12.750 -1.0891 0.04645 0.03865 -0.0315 1.0000 0.1049
-12.500 -1.0830 0.04442 0.03635 -0.0303 1.0000 0.1069
-12.250 -1.0795 0.04265 0.03431 -0.0288 1.0000 0.1088
-12.000 -1.0411 0.04037 0.03209 -0.0302 1.0000 0.1130
-11.750 -1.0151 0.03885 0.03055 -0.0304 1.0000 0.1167
-11.500 -0.9945 0.03735 0.02890 -0.0301 1.0000 0.1206
-11.250 -0.9675 0.03583 0.02730 -0.0302 1.0000 0.1254
-11.000 -0.9384 0.03466 0.02627 -0.0304 1.0000 0.1317
-10.750 -0.9199 0.03341 0.02487 -0.0299 1.0000 0.1377
-10.500 -0.8889 0.03232 0.02406 -0.0300 1.0000 0.1466
-10.250 -0.8693 0.03113 0.02297 -0.0294 1.0000 0.1571
-10.000 -0.8552 0.02982 0.02183 -0.0286 1.0000 0.1708
-9.750 -0.8464 0.02833 0.02060 -0.0274 1.0000 0.1881
-9.500 -0.8453 0.02663 0.01915 -0.0258 1.0000 0.2123
-9.250 -0.8535 0.02491 0.01782 -0.0232 1.0000 0.2410
-9.000 -0.8771 0.02410 0.01723 -0.0173 1.0000 0.2606
-8.750 -0.9132 0.02406 0.01726 -0.0085 1.0000 0.2647
-8.500 -0.9299 0.02315 0.01666 -0.0036 0.9956 0.2997
-8.250 -0.9051 0.02224 0.01620 -0.0054 0.9824 0.3818
-8.000 -0.8704 0.02236 0.01632 -0.0076 0.9717 0.4299
-7.750 -0.8293 0.02285 0.01674 -0.0102 0.9634 0.4616
-7.500 -0.7832 0.02359 0.01741 -0.0132 0.9560 0.4856
-7.250 -0.7376 0.02459 0.01835 -0.0155 0.9486 0.5043
-7.000 -0.6896 0.02581 0.01953 -0.0177 0.9415 0.5210
-6.750 -0.6368 0.02766 0.02135 -0.0196 0.9354 0.5365
-6.500 -0.5912 0.02921 0.02285 -0.0206 0.9273 0.5497
-6.250 -0.5659 0.02949 0.02300 -0.0203 0.9173 0.5629
-6.000 -0.4985 0.03187 0.02536 -0.0226 0.9122 0.5664
-5.750 -0.4616 0.03277 0.02617 -0.0227 0.9039 0.5749
-5.500 -0.4282 0.03345 0.02677 -0.0223 0.8949 0.5822
-5.250 -0.4171 0.03315 0.02639 -0.0204 0.8841 0.5934
-5.000 -0.3765 0.03406 0.02722 -0.0203 0.8771 0.5981
-4.750 -0.3810 0.03297 0.02604 -0.0175 0.8654 0.6110
-4.500 -0.3378 0.03388 0.02689 -0.0176 0.8598 0.6139
-4.250 -0.2999 0.03467 0.02764 -0.0177 0.8512 0.6176
-4.000 -0.3054 0.03330 0.02616 -0.0147 0.8427 0.6296
-3.750 -0.2693 0.03394 0.02679 -0.0149 0.8343 0.6330
-3.500 -0.2745 0.03256 0.02529 -0.0120 0.8270 0.6452
-3.250 -0.2398 0.03316 0.02589 -0.0122 0.8185 0.6482
-3.000 -0.2121 0.03324 0.02591 -0.0115 0.8123 0.6534
-2.750 -0.2106 0.03236 0.02499 -0.0096 0.8034 0.6632
-2.500 -0.1792 0.03261 0.02520 -0.0093 0.7975 0.6672
-2.250 -0.1809 0.03159 0.02411 -0.0072 0.7895 0.6782
-2.000 -0.1499 0.03189 0.02441 -0.0069 0.7827 0.6814
-1.750 -0.1239 0.03180 0.02426 -0.0061 0.7781 0.6867
-1.500 -0.1203 0.03129 0.02373 -0.0048 0.7689 0.6958
-1.250 -0.0908 0.03139 0.02382 -0.0043 0.7637 0.6997
-1.000 -0.0779 0.03113 0.02352 -0.0032 0.7568 0.7077
-0.750 -0.0602 0.03103 0.02341 -0.0024 0.7497 0.7135
-0.500 -0.0318 0.03099 0.02336 -0.0018 0.7456 0.7181
-0.250 -0.0279 0.03077 0.02312 -0.0005 0.7368 0.7279
0.000 0.0000 0.03092 0.02329 0.0000 0.7314 0.7314
0.250 0.0279 0.03077 0.02312 0.0005 0.7279 0.7368
0.500 0.0317 0.03099 0.02336 0.0018 0.7181 0.7456
0.750 0.0602 0.03103 0.02341 0.0024 0.7135 0.7497
1.000 0.0779 0.03113 0.02352 0.0032 0.7077 0.7568
1.250 0.0907 0.03139 0.02382 0.0043 0.6997 0.7637
1.500 0.1203 0.03129 0.02373 0.0048 0.6958 0.7689
1.750 0.1240 0.03179 0.02425 0.0061 0.6867 0.7781
2.000 0.1498 0.03191 0.02442 0.0069 0.6814 0.7827
2.250 0.1810 0.03159 0.02410 0.0072 0.6782 0.7895
2.500 0.1792 0.03261 0.02520 0.0093 0.6672 0.7975
2.750 0.2106 0.03236 0.02498 0.0096 0.6632 0.8034
3.000 0.2121 0.03324 0.02591 0.0115 0.6534 0.8123
3.250 0.2399 0.03316 0.02588 0.0122 0.6482 0.8185
3.500 0.2743 0.03258 0.02530 0.0120 0.6452 0.8270
3.750 0.2692 0.03395 0.02679 0.0149 0.6330 0.8343
4.000 0.3054 0.03330 0.02617 0.0147 0.6296 0.8426
4.250 0.2999 0.03466 0.02764 0.0177 0.6176 0.8512
4.500 0.3376 0.03389 0.02690 0.0176 0.6139 0.8598
4.750 0.3812 0.03295 0.02602 0.0175 0.6110 0.8654
5.000 0.3764 0.03407 0.02723 0.0203 0.5981 0.8771
5.250 0.4173 0.03314 0.02637 0.0203 0.5934 0.8840
5.500 0.4282 0.03345 0.02677 0.0222 0.5822 0.8949
5.750 0.4905 0.03132 0.02469 0.0207 0.5796 0.9005
6.000 0.4982 0.03189 0.02538 0.0226 0.5664 0.9123
6.250 0.5657 0.02949 0.02301 0.0203 0.5629 0.9173
6.500 0.5911 0.02922 0.02287 0.0206 0.5498 0.9274
6.750 0.6367 0.02766 0.02135 0.0196 0.5365 0.9355
7.000 0.6895 0.02583 0.01955 0.0177 0.5211 0.9416
7.250 0.7376 0.02458 0.01834 0.0155 0.5043 0.9487
7.500 0.7834 0.02357 0.01738 0.0132 0.4855 0.9560
7.750 0.8292 0.02285 0.01673 0.0102 0.4615 0.9634
8.000 0.8706 0.02235 0.01631 0.0076 0.4300 0.9718
8.250 0.9052 0.02223 0.01619 0.0054 0.3818 0.9824
8.500 0.9301 0.02314 0.01665 0.0036 0.2999 0.9956
8.750 0.9131 0.02405 0.01725 0.0085 0.2647 1.0000
9.000 0.8774 0.02410 0.01723 0.0173 0.2607 1.0000
9.250 0.8537 0.02491 0.01781 0.0231 0.2409 1.0000
9.500 0.8457 0.02662 0.01914 0.0257 0.2124 1.0000
9.750 0.8470 0.02831 0.02058 0.0273 0.1882 1.0000
10.000 0.8556 0.02981 0.02182 0.0285 0.1707 1.0000
10.250 0.8699 0.03111 0.02296 0.0293 0.1571 1.0000
10.500 0.8893 0.03231 0.02405 0.0299 0.1466 1.0000
10.750 0.9205 0.03340 0.02487 0.0298 0.1377 1.0000
11.000 0.9387 0.03465 0.02627 0.0304 0.1316 1.0000
11.250 0.9682 0.03582 0.02729 0.0301 0.1254 1.0000
11.500 0.9949 0.03734 0.02890 0.0300 0.1205 1.0000
11.750 1.0156 0.03885 0.03055 0.0303 0.1167 1.0000
12.000 1.0417 0.04037 0.03209 0.0301 0.1129 1.0000
12.250 1.0791 0.04262 0.03428 0.0288 0.1088 1.0000
12.500 1.0833 0.04440 0.03635 0.0303 0.1069 1.0000
12.750 1.0894 0.04646 0.03865 0.0314 0.1048 1.0000
13.000 1.0960 0.04862 0.04101 0.0324 0.1029 1.0000
13.250 1.1041 0.05075 0.04328 0.0331 0.1007 1.0000
13.500 1.1155 0.05287 0.04546 0.0335 0.0983 1.0000
13.750 1.1338 0.05638 0.04902 0.0331 0.0959 1.0000
14.000 1.1170 0.05924 0.05217 0.0347 0.0953 1.0000
14.250 1.0969 0.06261 0.05583 0.0356 0.0948 1.0000
14.500 1.0745 0.06659 0.06008 0.0359 0.0945 1.0000
14.750 1.0482 0.07128 0.06504 0.0355 0.0942 1.0000
15.000 1.0183 0.07685 0.07086 0.0342 0.0943 1.0000
15.250 0.9833 0.08356 0.07780 0.0319 0.0945 1.0000
15.500 0.9448 0.09160 0.08605 0.0284 0.0951 1.0000
15.750 0.9055 0.10103 0.09565 0.0238 0.0958 1.0000
16.000 0.6649 0.17621 0.17100 -0.0164 0.1677 1.0000
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Polar data table (+)
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