NACA 63(3)-218 (naca633218-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: NACA 63(3)-218 (naca633218-il) Reynolds number: 1,000,000 Max Cl/Cd: 75.91 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca633218-il-1000000-n5.txt Download as CSV file: xf-naca633218-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 63(3)-218
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-19.500 -1.1790 0.07809 0.07348 -0.0458 0.8212 0.0141
-19.250 -1.1820 0.07480 0.06993 -0.0469 0.7667 0.0144
-19.000 -1.1843 0.07134 0.06630 -0.0483 0.7385 0.0146
-18.750 -1.1862 0.06849 0.06298 -0.0491 0.6086 0.0147
-18.500 -1.1864 0.06612 0.05990 -0.0498 0.3184 0.0148
-18.250 -1.1849 0.06321 0.05691 -0.0509 0.3163 0.0152
-18.000 -1.1836 0.06036 0.05399 -0.0519 0.3144 0.0154
-17.750 -1.1816 0.05764 0.05120 -0.0528 0.3124 0.0157
-17.500 -1.1794 0.05501 0.04852 -0.0535 0.3101 0.0162
-17.250 -1.1757 0.05262 0.04607 -0.0541 0.3086 0.0164
-16.750 -1.1665 0.04817 0.04150 -0.0551 0.3061 0.0171
-16.500 -1.1607 0.04615 0.03943 -0.0554 0.3054 0.0175
-16.250 -1.1543 0.04423 0.03745 -0.0556 0.3050 0.0180
-16.000 -1.1469 0.04246 0.03561 -0.0557 0.3043 0.0183
-15.750 -1.1414 0.04055 0.03365 -0.0557 0.3039 0.0187
-15.500 -1.1353 0.03876 0.03182 -0.0557 0.3034 0.0191
-15.250 -1.1270 0.03722 0.03025 -0.0556 0.3029 0.0198
-15.000 -1.1192 0.03568 0.02867 -0.0554 0.3023 0.0204
-14.750 -1.1105 0.03428 0.02721 -0.0551 0.3016 0.0209
-14.500 -1.1012 0.03293 0.02581 -0.0547 0.3010 0.0213
-14.250 -1.0916 0.03165 0.02446 -0.0543 0.3006 0.0217
-14.000 -1.0825 0.03035 0.02312 -0.0538 0.2999 0.0221
-13.750 -1.0737 0.02906 0.02180 -0.0532 0.2994 0.0227
-13.500 -1.0639 0.02787 0.02057 -0.0526 0.2990 0.0232
-13.250 -1.0531 0.02680 0.01946 -0.0520 0.2986 0.0238
-13.000 -1.0417 0.02577 0.01839 -0.0513 0.2981 0.0244
-12.750 -1.0298 0.02481 0.01739 -0.0506 0.2975 0.0249
-12.500 -1.0174 0.02390 0.01643 -0.0498 0.2972 0.0253
-12.250 -1.0040 0.02309 0.01556 -0.0490 0.2968 0.0257
-12.000 -0.9929 0.02216 0.01460 -0.0480 0.2962 0.0264
-11.750 -0.9811 0.02129 0.01371 -0.0470 0.2959 0.0271
-11.500 -0.9687 0.02051 0.01289 -0.0460 0.2955 0.0277
-11.250 -0.9555 0.01980 0.01215 -0.0449 0.2951 0.0283
-11.000 -0.9419 0.01914 0.01145 -0.0437 0.2947 0.0289
-10.750 -0.9281 0.01853 0.01080 -0.0425 0.2944 0.0295
-10.500 -0.9144 0.01795 0.01018 -0.0411 0.2943 0.0300
-10.250 -0.9016 0.01744 0.00963 -0.0395 0.2942 0.0304
-10.000 -0.8939 0.01698 0.00914 -0.0369 0.2941 0.0311
-9.750 -0.8782 0.01658 0.00872 -0.0354 0.2940 0.0320
-9.500 -0.8593 0.01622 0.00833 -0.0345 0.2938 0.0329
-9.250 -0.8390 0.01589 0.00798 -0.0336 0.2937 0.0340
-9.000 -0.8172 0.01560 0.00766 -0.0330 0.2936 0.0352
-8.750 -0.7953 0.01528 0.00733 -0.0324 0.2934 0.0366
-8.500 -0.7727 0.01498 0.00701 -0.0319 0.2933 0.0383
-8.250 -0.7494 0.01470 0.00672 -0.0314 0.2931 0.0403
-8.000 -0.7257 0.01441 0.00643 -0.0311 0.2930 0.0434
-7.750 -0.7016 0.01414 0.00615 -0.0307 0.2928 0.0468
-7.500 -0.6771 0.01386 0.00588 -0.0305 0.2927 0.0510
-7.250 -0.6522 0.01360 0.00563 -0.0303 0.2925 0.0564
-6.750 -0.6020 0.01302 0.00510 -0.0299 0.2914 0.0738
-6.500 -0.5767 0.01271 0.00485 -0.0298 0.2908 0.0864
-6.250 -0.5513 0.01239 0.00459 -0.0297 0.2904 0.1021
-6.000 -0.5255 0.01210 0.00436 -0.0297 0.2902 0.1194
-5.750 -0.4992 0.01183 0.00416 -0.0297 0.2900 0.1374
-5.500 -0.4729 0.01154 0.00395 -0.0297 0.2898 0.1574
-5.250 -0.4465 0.01124 0.00374 -0.0298 0.2896 0.1821
-5.000 -0.4201 0.01091 0.00352 -0.0298 0.2894 0.2121
-4.750 -0.3937 0.01055 0.00331 -0.0300 0.2892 0.2493
-4.500 -0.3669 0.01022 0.00312 -0.0301 0.2890 0.2865
-4.250 -0.3398 0.00991 0.00295 -0.0303 0.2888 0.3234
-4.000 -0.3128 0.00957 0.00279 -0.0305 0.2886 0.3725
-3.750 -0.2846 0.00939 0.00271 -0.0308 0.2883 0.4021
-3.500 -0.2560 0.00928 0.00265 -0.0310 0.2876 0.4233
-3.250 -0.2271 0.00922 0.00261 -0.0313 0.2871 0.4374
-3.000 -0.1979 0.00921 0.00258 -0.0316 0.2867 0.4472
-2.750 -0.1689 0.00917 0.00256 -0.0319 0.2863 0.4566
-2.500 -0.1398 0.00917 0.00255 -0.0322 0.2861 0.4665
-2.250 -0.1108 0.00914 0.00255 -0.0325 0.2857 0.4778
-2.000 -0.0816 0.00916 0.00255 -0.0328 0.2854 0.4844
-1.750 -0.0525 0.00917 0.00256 -0.0331 0.2851 0.4900
-1.500 -0.0234 0.00919 0.00257 -0.0334 0.2847 0.4955
-1.250 0.0058 0.00924 0.00260 -0.0337 0.2843 0.5001
-1.000 0.0347 0.00927 0.00263 -0.0340 0.2839 0.5049
-0.750 0.0638 0.00930 0.00266 -0.0342 0.2835 0.5103
-0.500 0.0931 0.00931 0.00267 -0.0346 0.2833 0.5157
-0.250 0.1225 0.00933 0.00269 -0.0349 0.2831 0.5206
0.000 0.1517 0.00933 0.00271 -0.0352 0.2828 0.5259
0.250 0.1810 0.00934 0.00273 -0.0355 0.2824 0.5308
0.500 0.2103 0.00937 0.00276 -0.0358 0.2820 0.5352
0.750 0.2396 0.00940 0.00278 -0.0361 0.2815 0.5389
1.000 0.2688 0.00941 0.00282 -0.0364 0.2809 0.5432
1.250 0.2980 0.00943 0.00285 -0.0367 0.2802 0.5478
1.500 0.3272 0.00946 0.00289 -0.0370 0.2795 0.5525
2.000 0.3856 0.00951 0.00297 -0.0376 0.2777 0.5612
2.250 0.4149 0.00952 0.00300 -0.0379 0.2764 0.5657
2.500 0.4442 0.00954 0.00302 -0.0382 0.2748 0.5702
2.750 0.4733 0.00958 0.00305 -0.0385 0.2733 0.5741
3.000 0.5024 0.00960 0.00311 -0.0388 0.2718 0.5787
3.250 0.5314 0.00963 0.00318 -0.0391 0.2693 0.5841
3.500 0.5617 0.00957 0.00302 -0.0395 0.2279 0.5893
4.000 0.6134 0.01015 0.00347 -0.0393 0.2007 0.5982
4.250 0.6403 0.01034 0.00367 -0.0392 0.1964 0.6032
4.500 0.6680 0.01047 0.00382 -0.0393 0.1939 0.6080
4.750 0.6950 0.01065 0.00401 -0.0393 0.1899 0.6124
5.000 0.7215 0.01085 0.00423 -0.0392 0.1857 0.6180
5.250 0.7487 0.01099 0.00439 -0.0393 0.1815 0.6237
5.500 0.7757 0.01114 0.00456 -0.0392 0.1770 0.6290
5.750 0.8022 0.01132 0.00475 -0.0392 0.1736 0.6337
6.000 0.8289 0.01146 0.00493 -0.0391 0.1704 0.6391
6.250 0.8559 0.01160 0.00510 -0.0391 0.1662 0.6450
6.750 0.9079 0.01196 0.00547 -0.0388 0.1518 0.6561
7.000 0.9313 0.01230 0.00571 -0.0383 0.1303 0.6620
7.250 0.9529 0.01274 0.00605 -0.0376 0.1101 0.6674
7.500 0.9745 0.01313 0.00640 -0.0368 0.0974 0.6731
7.750 0.9956 0.01353 0.00677 -0.0360 0.0860 0.6798
8.000 1.0152 0.01397 0.00717 -0.0349 0.0743 0.6858
8.250 1.0334 0.01444 0.00759 -0.0337 0.0637 0.6914
8.500 1.0495 0.01492 0.00805 -0.0321 0.0540 0.6984
8.750 1.0626 0.01534 0.00847 -0.0299 0.0481 0.7051
9.000 1.0751 0.01581 0.00895 -0.0278 0.0435 0.7113
9.250 1.0875 0.01633 0.00949 -0.0257 0.0403 0.7182
9.500 1.1013 0.01685 0.01003 -0.0240 0.0381 0.7251
9.750 1.1137 0.01745 0.01067 -0.0222 0.0360 0.7323
10.000 1.1265 0.01808 0.01134 -0.0207 0.0342 0.7400
10.250 1.1397 0.01874 0.01204 -0.0192 0.0328 0.7470
10.500 1.1515 0.01949 0.01283 -0.0177 0.0313 0.7547
10.750 1.1632 0.02030 0.01368 -0.0163 0.0303 0.7627
11.000 1.1752 0.02112 0.01457 -0.0150 0.0294 0.7713
11.250 1.1874 0.02198 0.01548 -0.0139 0.0287 0.7803
11.500 1.1989 0.02290 0.01646 -0.0127 0.0280 0.7889
11.750 1.2093 0.02392 0.01754 -0.0116 0.0271 0.7990
12.000 1.2192 0.02500 0.01870 -0.0104 0.0266 0.8099
12.500 1.2360 0.02747 0.02130 -0.0083 0.0251 0.8349
12.750 1.2453 0.02866 0.02259 -0.0073 0.0248 0.8504
13.000 1.2535 0.02990 0.02394 -0.0063 0.0243 0.8705
13.250 1.2592 0.03116 0.02536 -0.0049 0.0238 0.9088
13.750 1.2809 0.03427 0.02865 -0.0051 0.0225 1.0000
14.000 1.2878 0.03599 0.03041 -0.0047 0.0220 1.0000
14.250 1.2934 0.03790 0.03234 -0.0044 0.0215 1.0000
14.500 1.3007 0.03973 0.03422 -0.0042 0.0209 1.0000
14.750 1.3077 0.04161 0.03616 -0.0040 0.0205 1.0000
15.000 1.3146 0.04355 0.03814 -0.0040 0.0199 1.0000
15.250 1.3200 0.04570 0.04035 -0.0040 0.0195 1.0000
15.500 1.3252 0.04793 0.04262 -0.0041 0.0190 1.0000
15.750 1.3301 0.05022 0.04495 -0.0043 0.0184 1.0000
16.000 1.3333 0.05276 0.04753 -0.0046 0.0178 1.0000
16.250 1.3381 0.05518 0.05000 -0.0049 0.0175 1.0000
16.500 1.3427 0.05767 0.05254 -0.0053 0.0171 1.0000
16.750 1.3463 0.06032 0.05525 -0.0059 0.0166 1.0000
17.000 1.3502 0.06297 0.05796 -0.0065 0.0162 1.0000
17.250 1.3529 0.06583 0.06087 -0.0072 0.0157 1.0000
17.500 1.3551 0.06882 0.06390 -0.0080 0.0152 1.0000
17.750 1.3571 0.07183 0.06695 -0.0088 0.0147 1.0000
18.000 1.3587 0.07499 0.07018 -0.0098 0.0145 1.0000
18.250 1.3612 0.07807 0.07332 -0.0108 0.0142 1.0000
18.500 1.3630 0.08129 0.07660 -0.0119 0.0138 1.0000
18.750 1.3646 0.08459 0.07997 -0.0131 0.0136 1.0000
19.000 1.3661 0.08790 0.08333 -0.0144 0.0132 1.0000
|
Polar data table (+)
Polar graphs
<< Back to NACA 63(3)-218 (naca633218-il)