NACA 2421 (naca2421-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 2421 (naca2421-il) Reynolds number: 100,000 Max Cl/Cd: 41.06 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca2421-il-100000-n5.txt Download as CSV file: xf-naca2421-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 2421
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
------ -------- --------- --------- -------- -------- --------
-16.250 -0.8418 0.07787 0.07002 -0.0764 1.0000 0.1001
-16.000 -0.8575 0.07287 0.06490 -0.0784 1.0000 0.1015
-15.750 -0.8547 0.07052 0.06258 -0.0789 1.0000 0.1029
-15.500 -0.8645 0.06666 0.05862 -0.0802 1.0000 0.1045
-15.250 -0.8794 0.06237 0.05419 -0.0814 1.0000 0.1061
-15.000 -0.8955 0.05822 0.04985 -0.0823 1.0000 0.1078
-14.750 -0.9124 0.05430 0.04570 -0.0826 1.0000 0.1095
-14.500 -0.9078 0.05271 0.04416 -0.0820 1.0000 0.1110
-14.250 -0.9077 0.05084 0.04230 -0.0813 1.0000 0.1127
-14.000 -0.9114 0.04880 0.04020 -0.0803 1.0000 0.1145
-13.750 -0.9180 0.04671 0.03800 -0.0789 1.0000 0.1165
-13.500 -0.9268 0.04466 0.03580 -0.0770 1.0000 0.1186
-13.250 -0.9287 0.04326 0.03439 -0.0749 1.0000 0.1203
-13.000 -0.9303 0.04209 0.03324 -0.0725 1.0000 0.1220
-12.750 -0.9348 0.04091 0.03204 -0.0697 1.0000 0.1240
-12.500 -0.9420 0.03976 0.03083 -0.0663 1.0000 0.1260
-12.250 -0.9512 0.03869 0.02965 -0.0623 1.0000 0.1282
-12.000 -0.9603 0.03777 0.02867 -0.0581 1.0000 0.1301
-11.750 -0.9681 0.03709 0.02803 -0.0536 1.0000 0.1318
-11.500 -0.9789 0.03647 0.02741 -0.0485 1.0000 0.1335
-11.250 -0.9918 0.03592 0.02683 -0.0429 1.0000 0.1353
-11.000 -0.9709 0.03494 0.02571 -0.0433 0.9948 0.1395
-10.750 -0.9462 0.03405 0.02481 -0.0443 0.9897 0.1434
-10.500 -0.9219 0.03322 0.02396 -0.0450 0.9836 0.1477
-10.250 -0.8936 0.03236 0.02293 -0.0463 0.9787 0.1531
-10.000 -0.8704 0.03160 0.02225 -0.0466 0.9716 0.1572
-9.750 -0.8419 0.03085 0.02144 -0.0477 0.9659 0.1629
-9.500 -0.8154 0.03011 0.02068 -0.0484 0.9595 0.1681
-9.250 -0.7894 0.02945 0.02003 -0.0489 0.9523 0.1736
-9.000 -0.7557 0.02874 0.01924 -0.0507 0.9479 0.1805
-8.750 -0.7353 0.02819 0.01875 -0.0499 0.9387 0.1857
-8.500 -0.7036 0.02758 0.01806 -0.0512 0.9332 0.1932
-8.250 -0.6727 0.02699 0.01753 -0.0523 0.9279 0.1998
-8.000 -0.6506 0.02654 0.01703 -0.0516 0.9187 0.2069
-7.750 -0.6178 0.02597 0.01649 -0.0530 0.9138 0.2145
-7.500 -0.5932 0.02554 0.01603 -0.0526 0.9060 0.2225
-7.250 -0.5673 0.02508 0.01559 -0.0525 0.8982 0.2301
-7.000 -0.5339 0.02459 0.01505 -0.0537 0.8934 0.2399
-6.750 -0.5137 0.02424 0.01474 -0.0524 0.8837 0.2475
-6.500 -0.4849 0.02382 0.01428 -0.0527 0.8767 0.2576
-6.250 -0.4514 0.02332 0.01382 -0.0538 0.8721 0.2675
-6.000 -0.4334 0.02309 0.01354 -0.0520 0.8607 0.2771
-5.750 -0.4030 0.02263 0.01314 -0.0524 0.8543 0.2871
-5.500 -0.3770 0.02232 0.01276 -0.0521 0.8462 0.2981
-5.250 -0.3525 0.02197 0.01250 -0.0514 0.8370 0.3075
-5.000 -0.3194 0.02157 0.01202 -0.0522 0.8312 0.3195
-4.750 -0.2992 0.02132 0.01186 -0.0507 0.8201 0.3287
-4.500 -0.2691 0.02098 0.01147 -0.0510 0.8126 0.3405
-4.250 -0.2435 0.02068 0.01124 -0.0504 0.8037 0.3511
-4.000 -0.2171 0.02042 0.01095 -0.0500 0.7940 0.3628
-3.750 -0.1858 0.02005 0.01062 -0.0504 0.7871 0.3752
-3.500 -0.1642 0.01989 0.01049 -0.0491 0.7753 0.3868
-3.250 -0.1330 0.01957 0.01016 -0.0494 0.7676 0.4010
-3.000 -0.1107 0.01942 0.01008 -0.0483 0.7561 0.4136
-2.750 -0.0813 0.01916 0.00981 -0.0483 0.7473 0.4289
-2.500 -0.0574 0.01902 0.00971 -0.0474 0.7364 0.4446
-2.250 -0.0298 0.01881 0.00955 -0.0470 0.7268 0.4614
-2.000 -0.0049 0.01869 0.00947 -0.0462 0.7164 0.4795
-1.750 0.0211 0.01855 0.00938 -0.0456 0.7063 0.4994
-1.500 0.0469 0.01844 0.00931 -0.0449 0.6964 0.5202
-1.250 0.0718 0.01837 0.00928 -0.0441 0.6860 0.5408
-1.000 0.0991 0.01828 0.00919 -0.0437 0.6771 0.5611
-0.750 0.1228 0.01826 0.00922 -0.0427 0.6663 0.5805
-0.500 0.1520 0.01818 0.00913 -0.0425 0.6582 0.5997
-0.250 0.1746 0.01821 0.00925 -0.0413 0.6473 0.6177
0.000 0.2025 0.01818 0.00921 -0.0410 0.6387 0.6366
0.250 0.2266 0.01823 0.00930 -0.0400 0.6291 0.6556
0.500 0.2526 0.01825 0.00934 -0.0394 0.6203 0.6748
0.750 0.2797 0.01830 0.00941 -0.0389 0.6118 0.6930
1.000 0.3044 0.01839 0.00956 -0.0380 0.6021 0.7111
1.250 0.3335 0.01843 0.00957 -0.0378 0.5945 0.7299
1.500 0.3565 0.01858 0.00979 -0.0367 0.5849 0.7487
1.750 0.3834 0.01869 0.00990 -0.0361 0.5768 0.7678
2.000 0.4109 0.01886 0.01008 -0.0356 0.5685 0.7854
2.250 0.4368 0.01904 0.01031 -0.0349 0.5593 0.8033
2.500 0.4669 0.01919 0.01038 -0.0349 0.5517 0.8213
2.750 0.4898 0.01941 0.01068 -0.0338 0.5410 0.8401
3.000 0.5197 0.01959 0.01077 -0.0337 0.5315 0.8578
3.250 0.5471 0.01986 0.01110 -0.0333 0.5201 0.8747
3.500 0.5793 0.02009 0.01125 -0.0338 0.5109 0.8911
3.750 0.6079 0.02039 0.01158 -0.0339 0.5015 0.9077
4.000 0.6401 0.02066 0.01181 -0.0346 0.4924 0.9223
4.250 0.6770 0.02096 0.01209 -0.0363 0.4834 0.9329
4.500 0.7089 0.02124 0.01236 -0.0373 0.4739 0.9456
4.750 0.7493 0.02153 0.01258 -0.0399 0.4650 0.9541
5.000 0.7844 0.02183 0.01291 -0.0416 0.4550 0.9642
5.250 0.8239 0.02209 0.01308 -0.0441 0.4463 0.9725
5.500 0.8595 0.02240 0.01345 -0.0462 0.4357 0.9814
5.750 0.8977 0.02267 0.01362 -0.0485 0.4269 0.9897
6.000 0.9341 0.02301 0.01402 -0.0509 0.4158 0.9975
6.250 0.9535 0.02322 0.01413 -0.0497 0.4082 1.0000
6.500 0.9570 0.02347 0.01444 -0.0457 0.4000 1.0000
6.750 0.9630 0.02368 0.01461 -0.0420 0.3924 1.0000
7.000 0.9690 0.02394 0.01483 -0.0383 0.3850 1.0000
7.250 0.9724 0.02424 0.01513 -0.0342 0.3769 1.0000
7.500 0.9804 0.02450 0.01529 -0.0308 0.3698 1.0000
7.750 0.9799 0.02485 0.01568 -0.0260 0.3617 1.0000
8.000 0.9838 0.02518 0.01597 -0.0220 0.3542 1.0000
8.250 0.9907 0.02559 0.01635 -0.0187 0.3465 1.0000
8.500 0.9968 0.02609 0.01686 -0.0154 0.3382 1.0000
8.750 1.0079 0.02656 0.01724 -0.0129 0.3309 1.0000
9.000 1.0150 0.02722 0.01796 -0.0101 0.3223 1.0000
9.250 1.0258 0.02781 0.01849 -0.0079 0.3147 1.0000
9.500 1.0348 0.02855 0.01927 -0.0056 0.3067 1.0000
9.750 1.0446 0.02929 0.02002 -0.0035 0.2989 1.0000
10.000 1.0548 0.03009 0.02079 -0.0016 0.2915 1.0000
10.250 1.0631 0.03101 0.02177 0.0003 0.2836 1.0000
10.500 1.0738 0.03186 0.02254 0.0020 0.2769 1.0000
10.750 1.0809 0.03298 0.02376 0.0038 0.2690 1.0000
11.000 1.0898 0.03399 0.02473 0.0054 0.2623 1.0000
11.250 1.0971 0.03521 0.02600 0.0069 0.2552 1.0000
11.500 1.1041 0.03646 0.02726 0.0084 0.2484 1.0000
11.750 1.1118 0.03772 0.02850 0.0097 0.2422 1.0000
12.000 1.1168 0.03925 0.03010 0.0110 0.2353 1.0000
12.250 1.1243 0.04057 0.03136 0.0121 0.2294 1.0000
12.500 1.1284 0.04231 0.03317 0.0132 0.2230 1.0000
12.750 1.1329 0.04401 0.03489 0.0142 0.2170 1.0000
13.000 1.1395 0.04558 0.03642 0.0151 0.2116 1.0000
13.250 1.1410 0.04770 0.03867 0.0158 0.2056 1.0000
13.500 1.1457 0.04953 0.04048 0.0165 0.2003 1.0000
13.750 1.1493 0.05156 0.04255 0.0171 0.1952 1.0000
14.000 1.1495 0.05402 0.04511 0.0175 0.1897 1.0000
14.250 1.1542 0.05598 0.04706 0.0179 0.1849 1.0000
14.500 1.1541 0.05861 0.04978 0.0181 0.1800 1.0000
14.750 1.1528 0.06143 0.05270 0.0181 0.1750 1.0000
15.000 1.1574 0.06352 0.05476 0.0182 0.1707 1.0000
15.250 1.1532 0.06685 0.05823 0.0180 0.1660 1.0000
15.500 1.1506 0.07003 0.06149 0.0176 0.1614 1.0000
15.750 1.1555 0.07221 0.06362 0.0175 0.1575 1.0000
16.000 1.1468 0.07635 0.06794 0.0168 0.1530 1.0000
16.250 1.1432 0.07983 0.07149 0.0161 0.1488 1.0000
16.500 1.1488 0.08201 0.07360 0.0158 0.1453 1.0000
16.750 1.1358 0.08701 0.07881 0.0144 0.1411 1.0000
17.000 1.1314 0.09076 0.08263 0.0134 0.1372 1.0000
17.250 1.1386 0.09276 0.08455 0.0131 0.1341 1.0000
17.500 1.1207 0.09873 0.09075 0.0111 0.1301 1.0000
17.750 1.1150 0.10287 0.09496 0.0097 0.1265 1.0000
18.000 1.1245 0.10457 0.09658 0.0093 0.1236 1.0000
18.250 1.1016 0.11160 0.10385 0.0064 0.1200 1.0000
18.500 1.0926 0.11645 0.10879 0.0044 0.1166 1.0000
18.750 1.1044 0.11781 0.11008 0.0040 0.1140 1.0000
19.000 1.0734 0.12662 0.11912 -0.0001 0.1104 1.0000
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