NACA 63(2)-215 MOD B (n63215b-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 63(2)-215 MOD B (n63215b-il) Reynolds number: 100,000 Max Cl/Cd: 35.32 at α=8° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-n63215b-il-100000-n5.txt Download as CSV file: xf-n63215b-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 63(2)-215 MOD B
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
------ -------- --------- --------- -------- -------- --------
-14.500 -0.6191 0.11806 0.11231 -0.0174 1.0000 0.0355
-14.250 -0.6960 0.09493 0.08896 -0.0321 1.0000 0.0347
-14.000 -0.7402 0.08320 0.07698 -0.0401 1.0000 0.0343
-13.750 -0.7730 0.07494 0.06847 -0.0454 1.0000 0.0341
-13.500 -0.7984 0.06851 0.06180 -0.0488 1.0000 0.0341
-13.250 -0.8180 0.06332 0.05637 -0.0511 1.0000 0.0342
-13.000 -0.8337 0.05889 0.05169 -0.0524 1.0000 0.0345
-12.750 -0.8457 0.05507 0.04763 -0.0531 1.0000 0.0348
-12.500 -0.8558 0.05161 0.04387 -0.0532 1.0000 0.0353
-12.250 -0.8621 0.04861 0.04059 -0.0528 1.0000 0.0357
-12.000 -0.8621 0.04608 0.03785 -0.0521 1.0000 0.0363
-11.750 -0.8529 0.04428 0.03605 -0.0515 1.0000 0.0370
-11.500 -0.8450 0.04264 0.03435 -0.0507 1.0000 0.0378
-11.250 -0.8380 0.04110 0.03275 -0.0497 1.0000 0.0389
-11.000 -0.8308 0.03952 0.03103 -0.0485 1.0000 0.0402
-10.750 -0.8222 0.03794 0.02926 -0.0471 1.0000 0.0415
-10.500 -0.8128 0.03647 0.02760 -0.0456 1.0000 0.0429
-10.250 -0.7988 0.03525 0.02647 -0.0445 1.0000 0.0444
-10.000 -0.7862 0.03417 0.02538 -0.0431 1.0000 0.0459
-9.750 -0.7718 0.03304 0.02418 -0.0418 1.0000 0.0476
-9.500 -0.7564 0.03192 0.02296 -0.0405 1.0000 0.0492
-9.250 -0.7420 0.03086 0.02184 -0.0389 1.0000 0.0510
-9.000 -0.7308 0.02994 0.02102 -0.0370 1.0000 0.0526
-8.750 -0.7235 0.02920 0.02031 -0.0344 1.0000 0.0543
-8.500 -0.7206 0.02857 0.01968 -0.0310 1.0000 0.0556
-8.250 -0.6925 0.02754 0.01858 -0.0320 0.9895 0.0582
-8.000 -0.6604 0.02639 0.01743 -0.0339 0.9802 0.0615
-7.750 -0.6295 0.02539 0.01645 -0.0356 0.9699 0.0655
-7.500 -0.5988 0.02449 0.01546 -0.0370 0.9603 0.0698
-7.250 -0.5688 0.02344 0.01448 -0.0385 0.9519 0.0752
-7.000 -0.5424 0.02263 0.01364 -0.0391 0.9411 0.0829
-6.750 -0.5163 0.02180 0.01283 -0.0397 0.9316 0.0944
-6.500 -0.4907 0.02089 0.01203 -0.0401 0.9228 0.1118
-6.250 -0.4695 0.02006 0.01134 -0.0398 0.9123 0.1395
-6.000 -0.4481 0.01910 0.01063 -0.0395 0.9037 0.1863
-5.750 -0.4308 0.01810 0.01004 -0.0387 0.8939 0.2569
-5.500 -0.4121 0.01731 0.00973 -0.0377 0.8855 0.3449
-5.250 -0.3891 0.01700 0.00966 -0.0369 0.8775 0.4119
-5.000 -0.3640 0.01691 0.00966 -0.0362 0.8704 0.4604
-4.750 -0.3392 0.01694 0.00973 -0.0353 0.8626 0.4962
-4.500 -0.3120 0.01701 0.00976 -0.0348 0.8572 0.5254
-4.250 -0.2871 0.01715 0.00990 -0.0339 0.8496 0.5456
-4.000 -0.2601 0.01723 0.00994 -0.0333 0.8436 0.5626
-3.750 -0.2336 0.01735 0.01002 -0.0326 0.8375 0.5790
-3.500 -0.2079 0.01752 0.01017 -0.0317 0.8307 0.5950
-3.250 -0.1806 0.01758 0.01015 -0.0312 0.8257 0.6085
-3.000 -0.1541 0.01766 0.01023 -0.0306 0.8194 0.6159
-2.750 -0.1276 0.01760 0.01007 -0.0301 0.8115 0.6256
-2.500 -0.1015 0.01759 0.01003 -0.0291 0.8022 0.6328
-2.250 -0.0747 0.01742 0.00974 -0.0285 0.7925 0.6415
-2.000 -0.0493 0.01737 0.00967 -0.0275 0.7811 0.6471
-1.750 -0.0226 0.01723 0.00945 -0.0269 0.7713 0.6548
-1.500 0.0038 0.01713 0.00931 -0.0261 0.7612 0.6612
-1.250 0.0301 0.01708 0.00924 -0.0254 0.7517 0.6680
-1.000 0.0575 0.01697 0.00905 -0.0250 0.7435 0.6754
-0.750 0.0834 0.01694 0.00903 -0.0243 0.7332 0.6810
-0.500 0.1109 0.01681 0.00884 -0.0239 0.7239 0.6884
-0.250 0.1369 0.01674 0.00877 -0.0231 0.7122 0.6944
0.000 0.1630 0.01666 0.00868 -0.0224 0.6994 0.7011
0.250 0.1897 0.01654 0.00852 -0.0218 0.6854 0.7084
0.500 0.2151 0.01645 0.00843 -0.0208 0.6685 0.7144
0.750 0.2414 0.01634 0.00827 -0.0202 0.6497 0.7229
1.000 0.2666 0.01627 0.00819 -0.0191 0.6303 0.7290
1.250 0.2922 0.01621 0.00809 -0.0183 0.6070 0.7366
1.500 0.3172 0.01617 0.00798 -0.0174 0.5768 0.7434
1.750 0.3413 0.01618 0.00789 -0.0162 0.5348 0.7504
2.000 0.3641 0.01633 0.00771 -0.0150 0.4615 0.7582
2.250 0.3822 0.01683 0.00772 -0.0131 0.3828 0.7648
2.500 0.4030 0.01737 0.00791 -0.0121 0.3497 0.7733
2.750 0.4241 0.01776 0.00821 -0.0108 0.3285 0.7799
3.000 0.4475 0.01812 0.00847 -0.0101 0.3110 0.7889
3.250 0.4694 0.01845 0.00875 -0.0090 0.2962 0.7963
3.500 0.4928 0.01878 0.00900 -0.0083 0.2830 0.8059
3.750 0.5145 0.01909 0.00927 -0.0071 0.2714 0.8135
4.000 0.5385 0.01939 0.00954 -0.0065 0.2609 0.8231
4.250 0.5599 0.01972 0.00981 -0.0053 0.2522 0.8315
4.500 0.5831 0.02000 0.01010 -0.0045 0.2424 0.8412
4.750 0.6047 0.02032 0.01038 -0.0034 0.2339 0.8508
5.000 0.6266 0.02061 0.01068 -0.0024 0.2252 0.8608
5.250 0.6484 0.02096 0.01098 -0.0014 0.2181 0.8722
5.500 0.6696 0.02124 0.01131 -0.0002 0.2110 0.8838
5.750 0.6905 0.02161 0.01162 0.0009 0.2055 0.8964
6.000 0.7131 0.02194 0.01202 0.0018 0.1998 0.9103
6.250 0.7369 0.02230 0.01242 0.0024 0.1941 0.9259
6.500 0.7639 0.02277 0.01284 0.0022 0.1892 0.9438
7.000 0.8278 0.02374 0.01392 -0.0006 0.1771 1.0000
7.250 0.8517 0.02434 0.01440 -0.0007 0.1728 1.0000
7.500 0.8765 0.02492 0.01508 -0.0008 0.1677 1.0000
7.750 0.9008 0.02554 0.01571 -0.0009 0.1634 1.0000
8.000 0.9243 0.02617 0.01631 -0.0008 0.1597 1.0000
8.250 0.9477 0.02690 0.01702 -0.0007 0.1560 1.0000
8.500 0.9702 0.02762 0.01785 -0.0005 0.1517 1.0000
8.750 0.9918 0.02831 0.01857 -0.0001 0.1477 1.0000
9.000 1.0128 0.02900 0.01923 0.0003 0.1443 1.0000
9.250 1.0341 0.02984 0.02005 0.0006 0.1413 1.0000
9.500 1.0535 0.03071 0.02110 0.0012 0.1377 1.0000
9.750 1.0722 0.03156 0.02204 0.0019 0.1343 1.0000
10.000 1.0901 0.03235 0.02285 0.0026 0.1314 1.0000
10.250 1.1077 0.03316 0.02363 0.0033 0.1289 1.0000
10.500 1.1250 0.03420 0.02470 0.0041 0.1267 1.0000
10.750 1.1381 0.03538 0.02611 0.0053 0.1243 1.0000
11.000 1.1506 0.03660 0.02748 0.0064 0.1219 1.0000
11.250 1.1625 0.03780 0.02879 0.0075 0.1197 1.0000
11.500 1.1743 0.03898 0.03005 0.0085 0.1177 1.0000
11.750 1.1864 0.04010 0.03120 0.0094 0.1159 1.0000
12.000 1.1999 0.04122 0.03232 0.0101 0.1142 1.0000
12.250 1.2078 0.04283 0.03404 0.0110 0.1125 1.0000
12.500 1.2067 0.04493 0.03641 0.0122 0.1107 1.0000
12.750 1.2051 0.04718 0.03890 0.0131 0.1089 1.0000
13.000 1.2031 0.04956 0.04147 0.0138 0.1072 1.0000
13.250 1.2008 0.05209 0.04416 0.0141 0.1057 1.0000
13.500 1.1979 0.05479 0.04701 0.0143 0.1045 1.0000
13.750 1.1950 0.05758 0.04993 0.0141 0.1033 1.0000
14.000 1.1935 0.06036 0.05282 0.0138 0.1022 1.0000
14.250 1.1941 0.06305 0.05559 0.0133 0.1012 1.0000
14.500 1.1979 0.06559 0.05816 0.0129 0.1002 1.0000
14.750 1.1756 0.07121 0.06399 0.0109 0.0994 1.0000
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Polar data table (+)
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