NACA 2410 (naca2410-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 2410 (naca2410-il) Reynolds number: 200,000 Max Cl/Cd: 61.97 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca2410-il-200000-n5.txt Download as CSV file: xf-naca2410-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 2410
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
------ -------- --------- --------- -------- -------- --------
-11.500 -0.5726 0.10935 0.10553 -0.0131 1.0000 0.0206
-11.250 -0.8170 0.04734 0.04308 -0.0569 1.0000 0.0184
-11.000 -0.8291 0.04366 0.03921 -0.0569 1.0000 0.0186
-10.750 -0.8248 0.04161 0.03707 -0.0564 1.0000 0.0189
-10.500 -0.8172 0.03985 0.03518 -0.0558 1.0000 0.0194
-10.250 -0.8104 0.03775 0.03289 -0.0549 1.0000 0.0199
-10.000 -0.8036 0.03542 0.03030 -0.0537 1.0000 0.0205
-9.750 -0.7960 0.03301 0.02758 -0.0523 1.0000 0.0213
-9.500 -0.7868 0.03066 0.02483 -0.0506 1.0000 0.0223
-9.250 -0.7748 0.02859 0.02231 -0.0490 1.0000 0.0236
-9.000 -0.7593 0.02736 0.02100 -0.0477 1.0000 0.0246
-8.750 -0.7415 0.02656 0.02014 -0.0465 1.0000 0.0256
-8.500 -0.7242 0.02551 0.01893 -0.0452 1.0000 0.0268
-8.250 -0.7066 0.02433 0.01752 -0.0438 1.0000 0.0284
-8.000 -0.6879 0.02336 0.01625 -0.0424 1.0000 0.0300
-7.750 -0.6700 0.02221 0.01502 -0.0411 1.0000 0.0315
-7.500 -0.6505 0.02150 0.01426 -0.0400 1.0000 0.0330
-7.250 -0.6305 0.02080 0.01345 -0.0388 1.0000 0.0348
-7.000 -0.6100 0.02013 0.01261 -0.0376 1.0000 0.0369
-6.750 -0.5893 0.01940 0.01173 -0.0365 1.0000 0.0384
-6.500 -0.5691 0.01855 0.01085 -0.0354 1.0000 0.0403
-6.250 -0.5356 0.01796 0.01020 -0.0370 0.9970 0.0430
-6.000 -0.5013 0.01733 0.00946 -0.0386 0.9941 0.0454
-5.750 -0.4679 0.01679 0.00879 -0.0399 0.9902 0.0476
-5.500 -0.4340 0.01599 0.00799 -0.0416 0.9866 0.0506
-5.250 -0.3996 0.01546 0.00742 -0.0432 0.9826 0.0533
-5.000 -0.3656 0.01499 0.00688 -0.0446 0.9778 0.0567
-4.750 -0.3294 0.01447 0.00633 -0.0465 0.9743 0.0611
-4.500 -0.2974 0.01403 0.00588 -0.0475 0.9685 0.0664
-4.250 -0.2624 0.01360 0.00544 -0.0491 0.9641 0.0741
-4.000 -0.2284 0.01320 0.00505 -0.0505 0.9594 0.0865
-3.750 -0.1972 0.01281 0.00474 -0.0513 0.9527 0.1052
-3.500 -0.1626 0.01242 0.00445 -0.0528 0.9480 0.1312
-3.250 -0.1336 0.01211 0.00422 -0.0531 0.9396 0.1579
-3.000 -0.1004 0.01178 0.00399 -0.0542 0.9335 0.1883
-2.750 -0.0716 0.01148 0.00381 -0.0545 0.9243 0.2218
-2.500 -0.0397 0.01109 0.00362 -0.0553 0.9173 0.2760
-2.250 -0.0124 0.01071 0.00348 -0.0553 0.9065 0.3364
-2.000 0.0163 0.01036 0.00333 -0.0554 0.8966 0.3943
-1.750 0.0450 0.00999 0.00319 -0.0555 0.8868 0.4613
-1.500 0.0711 0.00964 0.00310 -0.0549 0.8745 0.5387
-1.250 0.0969 0.00931 0.00304 -0.0542 0.8619 0.6195
-1.000 0.1218 0.00900 0.00300 -0.0531 0.8488 0.7010
-0.750 0.1461 0.00876 0.00299 -0.0516 0.8350 0.7792
-0.500 0.1727 0.00863 0.00299 -0.0505 0.8206 0.8493
-0.250 0.2058 0.00859 0.00296 -0.0509 0.8055 0.9051
0.000 0.2434 0.00860 0.00291 -0.0525 0.7894 0.9449
0.250 0.2822 0.00863 0.00285 -0.0545 0.7721 0.9724
0.500 0.3224 0.00867 0.00279 -0.0570 0.7537 0.9917
0.750 0.3566 0.00873 0.00274 -0.0583 0.7348 1.0000
1.000 0.3814 0.00881 0.00272 -0.0575 0.7153 1.0000
1.250 0.4062 0.00892 0.00272 -0.0568 0.6957 1.0000
1.500 0.4310 0.00904 0.00274 -0.0560 0.6763 1.0000
1.750 0.4558 0.00918 0.00277 -0.0553 0.6567 1.0000
2.000 0.4806 0.00932 0.00284 -0.0546 0.6365 1.0000
2.250 0.5054 0.00949 0.00291 -0.0539 0.6166 1.0000
2.500 0.5303 0.00966 0.00299 -0.0532 0.5972 1.0000
2.750 0.5553 0.00984 0.00311 -0.0525 0.5772 1.0000
3.000 0.5802 0.01004 0.00323 -0.0519 0.5571 1.0000
3.250 0.6050 0.01026 0.00336 -0.0512 0.5362 1.0000
3.500 0.6295 0.01049 0.00352 -0.0505 0.5110 1.0000
3.750 0.6540 0.01075 0.00368 -0.0497 0.4854 1.0000
4.000 0.6782 0.01102 0.00386 -0.0490 0.4580 1.0000
4.250 0.7021 0.01133 0.00406 -0.0482 0.4254 1.0000
4.500 0.7251 0.01171 0.00427 -0.0474 0.3854 1.0000
4.750 0.7479 0.01214 0.00452 -0.0465 0.3416 1.0000
5.000 0.7706 0.01262 0.00483 -0.0457 0.2984 1.0000
5.250 0.7926 0.01318 0.00519 -0.0448 0.2524 1.0000
5.500 0.8143 0.01382 0.00560 -0.0440 0.2065 1.0000
5.750 0.8362 0.01447 0.00606 -0.0431 0.1663 1.0000
6.000 0.8578 0.01515 0.00659 -0.0423 0.1314 1.0000
6.250 0.8794 0.01583 0.00713 -0.0415 0.1032 1.0000
6.500 0.9013 0.01650 0.00771 -0.0406 0.0827 1.0000
6.750 0.9230 0.01715 0.00832 -0.0397 0.0692 1.0000
7.000 0.9448 0.01779 0.00897 -0.0388 0.0609 1.0000
7.250 0.9659 0.01849 0.00966 -0.0379 0.0550 1.0000
7.500 0.9873 0.01913 0.01037 -0.0369 0.0518 1.0000
7.750 1.0083 0.01979 0.01110 -0.0359 0.0492 1.0000
8.000 1.0284 0.02051 0.01189 -0.0348 0.0467 1.0000
8.250 1.0463 0.02143 0.01283 -0.0335 0.0442 1.0000
8.500 1.0656 0.02222 0.01370 -0.0323 0.0425 1.0000
8.750 1.0847 0.02300 0.01459 -0.0311 0.0408 1.0000
9.000 1.1033 0.02380 0.01547 -0.0299 0.0388 1.0000
9.250 1.1209 0.02465 0.01638 -0.0286 0.0370 1.0000
9.500 1.1356 0.02579 0.01756 -0.0270 0.0353 1.0000
9.750 1.1511 0.02688 0.01875 -0.0255 0.0339 1.0000
10.000 1.1677 0.02778 0.01980 -0.0241 0.0324 1.0000
10.250 1.1824 0.02877 0.02091 -0.0225 0.0308 1.0000
10.500 1.1950 0.02976 0.02198 -0.0207 0.0294 1.0000
10.750 1.2059 0.03087 0.02314 -0.0188 0.0282 1.0000
11.000 1.2144 0.03245 0.02479 -0.0168 0.0269 1.0000
11.250 1.2256 0.03367 0.02622 -0.0150 0.0259 1.0000
11.500 1.2352 0.03505 0.02779 -0.0133 0.0247 1.0000
11.750 1.2434 0.03647 0.02935 -0.0117 0.0236 1.0000
12.000 1.2506 0.03792 0.03091 -0.0102 0.0226 1.0000
12.250 1.2563 0.03949 0.03256 -0.0088 0.0218 1.0000
12.500 1.2595 0.04151 0.03465 -0.0076 0.0211 1.0000
12.750 1.2623 0.04375 0.03712 -0.0064 0.0204 1.0000
13.000 1.2634 0.04627 0.03988 -0.0054 0.0197 1.0000
13.250 1.2627 0.04902 0.04288 -0.0047 0.0190 1.0000
13.500 1.2608 0.05197 0.04603 -0.0045 0.0184 1.0000
13.750 1.2581 0.05508 0.04933 -0.0046 0.0179 1.0000
14.000 1.2547 0.05842 0.05282 -0.0051 0.0174 1.0000
14.250 1.2507 0.06196 0.05650 -0.0061 0.0170 1.0000
14.500 1.2456 0.06581 0.06048 -0.0073 0.0167 1.0000
14.750 1.2394 0.06998 0.06477 -0.0089 0.0164 1.0000
15.000 1.2306 0.07468 0.06959 -0.0109 0.0162 1.0000
15.250 1.2190 0.08005 0.07508 -0.0132 0.0160 1.0000
15.500 1.2022 0.08671 0.08198 -0.0165 0.0159 1.0000
15.750 1.1831 0.09415 0.08964 -0.0204 0.0158 1.0000
16.000 1.1624 0.10231 0.09801 -0.0249 0.0157 1.0000
16.250 1.1396 0.11135 0.10725 -0.0301 0.0157 1.0000
16.500 1.1143 0.12145 0.11752 -0.0361 0.0158 1.0000
16.750 1.0860 0.13294 0.12918 -0.0430 0.0160 1.0000
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