NACA 66(3)-218 (naca663218-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: NACA 66(3)-218 (naca663218-il) Reynolds number: 50,000 Max Cl/Cd: 16.94 at α=9° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca663218-il-50000-n5.txt Download as CSV file: xf-naca663218-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 66(3)-218
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.250 -0.4891 0.11726 0.10983 -0.0719 1.0000 0.0605
-14.000 -0.5085 0.11190 0.10453 -0.0730 1.0000 0.0601
-13.750 -0.5332 0.10678 0.09945 -0.0735 1.0000 0.0595
-13.500 -0.5666 0.10132 0.09400 -0.0740 1.0000 0.0590
-13.250 -0.6028 0.09641 0.08909 -0.0737 1.0000 0.0584
-13.000 -0.6413 0.09190 0.08453 -0.0726 1.0000 0.0580
-12.750 -0.6707 0.08651 0.07898 -0.0737 0.9967 0.0575
-12.500 -0.6949 0.08112 0.07334 -0.0753 0.9911 0.0572
-12.250 -0.7157 0.07657 0.06853 -0.0758 0.9860 0.0570
-12.000 -0.7334 0.07271 0.06438 -0.0754 0.9807 0.0569
-11.750 -0.7465 0.06930 0.06067 -0.0746 0.9755 0.0569
-11.500 -0.7566 0.06633 0.05740 -0.0732 0.9703 0.0570
-11.250 -0.7637 0.06367 0.05442 -0.0714 0.9650 0.0572
-11.000 -0.7643 0.06105 0.05146 -0.0702 0.9608 0.0575
-10.750 -0.7694 0.05915 0.04926 -0.0671 0.9552 0.0579
-10.500 -0.7682 0.05714 0.04690 -0.0649 0.9510 0.0590
-10.250 -0.7596 0.05506 0.04440 -0.0636 0.9480 0.0602
-10.000 -0.7625 0.05376 0.04276 -0.0596 0.9430 0.0611
-9.750 -0.7357 0.05175 0.04069 -0.0604 0.9408 0.0628
-9.500 -0.7010 0.04981 0.03857 -0.0623 0.9390 0.0649
-9.250 -0.6542 0.04794 0.03645 -0.0653 0.9381 0.0675
-9.000 -0.6056 0.04655 0.03480 -0.0682 0.9372 0.0720
-8.750 -0.5544 0.04564 0.03391 -0.0712 0.9366 0.0770
-8.500 -0.5087 0.04510 0.03315 -0.0730 0.9355 0.0826
-8.250 -0.4791 0.04433 0.03245 -0.0737 0.9339 0.0893
-8.000 -0.4710 0.04396 0.03198 -0.0708 0.9300 0.0946
-7.750 -0.4633 0.04333 0.03141 -0.0683 0.9267 0.1007
-7.500 -0.4530 0.04270 0.03072 -0.0663 0.9238 0.1098
-7.250 -0.4449 0.04182 0.02995 -0.0643 0.9213 0.1230
-7.000 -0.4380 0.04066 0.02907 -0.0624 0.9189 0.1471
-6.750 -0.4487 0.03989 0.02856 -0.0572 0.9146 0.1746
-6.500 -0.4634 0.03882 0.02796 -0.0515 0.9104 0.2279
-6.250 -0.4784 0.03766 0.02743 -0.0458 0.9070 0.3131
-6.000 -0.4023 0.04249 0.03357 -0.0449 0.9074 0.5815
-5.750 -0.4137 0.04262 0.03361 -0.0391 0.9044 0.6224
-5.500 -0.4123 0.04423 0.03511 -0.0334 0.9020 0.6680
-5.250 -0.4097 0.04641 0.03721 -0.0266 0.8987 0.7017
-5.000 -0.3572 0.04879 0.03927 -0.0278 0.8975 0.7266
-4.750 -0.3470 0.04915 0.03947 -0.0249 0.8948 0.7408
-4.500 -0.3412 0.04939 0.03957 -0.0214 0.8925 0.7552
-4.250 -0.2996 0.04983 0.03975 -0.0237 0.8914 0.7641
-4.000 -0.2831 0.04991 0.03967 -0.0223 0.8892 0.7756
-3.750 -0.2588 0.05001 0.03959 -0.0222 0.8873 0.7861
-3.500 -0.2290 0.05004 0.03943 -0.0232 0.8857 0.7944
-3.250 -0.2276 0.05009 0.03939 -0.0193 0.8831 0.8046
-3.000 -0.2136 0.05008 0.03927 -0.0176 0.8804 0.8118
-2.750 -0.2010 0.05004 0.03914 -0.0158 0.8774 0.8197
-2.500 -0.1904 0.04996 0.03896 -0.0136 0.8747 0.8275
-2.250 -0.1628 0.04993 0.03880 -0.0145 0.8724 0.8330
-2.000 -0.1598 0.04985 0.03864 -0.0111 0.8696 0.8419
-1.750 -0.1215 0.04984 0.03850 -0.0140 0.8679 0.8455
-1.500 -0.1172 0.04981 0.03843 -0.0107 0.8639 0.8514
-1.250 -0.1259 0.04970 0.03827 -0.0052 0.8596 0.8592
-1.000 -0.0969 0.04969 0.03819 -0.0065 0.8568 0.8626
-0.750 -0.0718 0.04968 0.03812 -0.0070 0.8539 0.8666
-0.500 -0.0510 0.04971 0.03807 -0.0068 0.8512 0.8714
-0.250 -0.0601 0.04960 0.03794 -0.0012 0.8461 0.8770
0.000 -0.0402 0.04961 0.03792 -0.0009 0.8419 0.8802
0.250 -0.0199 0.04962 0.03790 -0.0007 0.8381 0.8835
0.500 0.0011 0.04967 0.03792 -0.0004 0.8348 0.8873
0.750 -0.0092 0.04954 0.03777 0.0054 0.8289 0.8925
1.000 0.0110 0.04959 0.03782 0.0056 0.8240 0.8950
1.250 0.0361 0.04967 0.03790 0.0050 0.8197 0.8975
1.500 0.0646 0.04981 0.03803 0.0039 0.8163 0.9000
1.750 0.0565 0.04971 0.03794 0.0092 0.8086 0.9043
2.000 0.0591 0.04960 0.03783 0.0129 0.8029 0.9082
2.250 0.0922 0.04977 0.03803 0.0110 0.7991 0.9096
2.500 0.0985 0.04984 0.03813 0.0135 0.7912 0.9124
2.750 0.1210 0.04996 0.03829 0.0134 0.7857 0.9148
3.000 0.1511 0.05012 0.03848 0.0122 0.7816 0.9168
3.500 0.1567 0.04998 0.03841 0.0192 0.7664 0.9237
3.750 0.1733 0.05020 0.03870 0.0198 0.7583 0.9260
4.000 0.1994 0.05038 0.03897 0.0191 0.7516 0.9283
4.250 0.2206 0.05052 0.03919 0.0193 0.7448 0.9308
4.500 0.2312 0.05056 0.03930 0.0213 0.7359 0.9339
4.750 0.2481 0.05051 0.03933 0.0226 0.7292 0.9371
5.000 0.2664 0.05069 0.03962 0.0230 0.7193 0.9394
5.250 0.2944 0.05085 0.03990 0.0220 0.7116 0.9416
5.500 0.3173 0.05097 0.04016 0.0219 0.7021 0.9445
5.750 0.3326 0.05108 0.04039 0.0231 0.6919 0.9483
6.000 0.3619 0.05096 0.04042 0.0224 0.6842 0.9511
6.250 0.3815 0.05117 0.04080 0.0225 0.6718 0.9537
6.500 0.4077 0.05116 0.04096 0.0220 0.6616 0.9562
6.750 0.4385 0.05084 0.04084 0.0213 0.6518 0.9589
7.000 0.4533 0.05082 0.04097 0.0225 0.6381 0.9628
7.250 0.4789 0.05076 0.04115 0.0220 0.6243 0.9655
7.500 0.5044 0.05060 0.04121 0.0216 0.6101 0.9687
7.750 0.5286 0.05029 0.04112 0.0217 0.5954 0.9728
8.000 0.5602 0.04950 0.04061 0.0213 0.5788 0.9759
8.250 0.5938 0.04749 0.03886 0.0219 0.5525 0.9795
8.500 0.6262 0.04434 0.03586 0.0241 0.5087 0.9838
8.750 0.6591 0.04223 0.03372 0.0254 0.4417 0.9874
9.000 0.6906 0.04077 0.03158 0.0270 0.3263 0.9910
9.250 0.6918 0.04237 0.03249 0.0291 0.2340 0.9969
9.500 0.6824 0.04408 0.03373 0.0324 0.1801 1.0000
9.750 0.6692 0.04522 0.03461 0.0369 0.1507 1.0000
10.000 0.6579 0.04632 0.03547 0.0410 0.1317 1.0000
10.250 0.6504 0.04733 0.03634 0.0447 0.1179 1.0000
10.500 0.6484 0.04843 0.03734 0.0475 0.1062 1.0000
10.750 0.6520 0.04962 0.03848 0.0494 0.0975 1.0000
11.000 0.6583 0.05095 0.03971 0.0508 0.0904 1.0000
11.250 0.6717 0.05204 0.04090 0.0518 0.0832 1.0000
11.500 0.6868 0.05318 0.04194 0.0525 0.0782 1.0000
11.750 0.7098 0.05403 0.04296 0.0529 0.0729 1.0000
12.000 0.7341 0.05493 0.04385 0.0530 0.0683 1.0000
12.250 0.7708 0.05569 0.04476 0.0528 0.0646 1.0000
12.500 0.7989 0.05700 0.04625 0.0526 0.0612 1.0000
12.750 0.8241 0.05848 0.04775 0.0522 0.0585 1.0000
13.000 0.8470 0.06053 0.05001 0.0521 0.0565 1.0000
13.250 0.8621 0.06306 0.05288 0.0523 0.0553 1.0000
13.500 0.8706 0.06586 0.05598 0.0526 0.0545 1.0000
13.750 0.8721 0.06892 0.05933 0.0532 0.0535 1.0000
14.000 0.8701 0.07216 0.06283 0.0536 0.0529 1.0000
14.250 0.8640 0.07572 0.06664 0.0539 0.0523 1.0000
14.500 0.8565 0.07932 0.07044 0.0539 0.0515 1.0000
14.750 0.8453 0.08342 0.07476 0.0536 0.0511 1.0000
15.000 0.8290 0.08817 0.07974 0.0529 0.0509 1.0000
15.250 0.8023 0.09438 0.08623 0.0512 0.0512 1.0000
15.500 0.7655 0.10274 0.09489 0.0477 0.0518 1.0000
15.750 0.7191 0.11442 0.10682 0.0414 0.0530 1.0000
|
Polar data table (+)
Polar graphs
<< Back to NACA 66(3)-218 (naca663218-il)