NACA 0024 (naca0024-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 0024 (naca0024-il) Reynolds number: 100,000 Max Cl/Cd: 34.7 at α=8.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca0024-il-100000.txt Download as CSV file: xf-naca0024-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 0024
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.750 -0.3738 0.15984 0.15298 -0.0193 1.0000 0.2448
-14.500 -0.4340 0.15746 0.15061 -0.0231 1.0000 0.2518
-14.250 -1.0669 0.05481 0.04656 -0.0535 1.0000 0.2186
-14.000 -1.0216 0.05559 0.04753 -0.0539 1.0000 0.2233
-13.750 -0.9997 0.05532 0.04734 -0.0533 1.0000 0.2278
-13.500 -1.0497 0.05057 0.04234 -0.0495 1.0000 0.2309
-13.250 -1.0996 0.04692 0.03841 -0.0437 1.0000 0.2336
-13.000 -1.1086 0.04520 0.03663 -0.0403 1.0000 0.2373
-12.750 -1.0679 0.04553 0.03718 -0.0412 1.0000 0.2427
-12.500 -1.0876 0.04391 0.03546 -0.0363 1.0000 0.2465
-12.250 -1.1240 0.04219 0.03357 -0.0288 1.0000 0.2495
-12.000 -1.1682 0.04097 0.03213 -0.0190 1.0000 0.2516
-11.750 -1.1067 0.04093 0.03244 -0.0237 1.0000 0.2585
-11.500 -1.1235 0.04020 0.03167 -0.0175 1.0000 0.2622
-11.250 -1.1559 0.03941 0.03076 -0.0086 1.0000 0.2652
-11.000 -1.1895 0.03842 0.02956 0.0004 1.0000 0.2683
-10.750 -1.1572 0.03816 0.02956 -0.0004 1.0000 0.2741
-10.500 -1.1584 0.03771 0.02913 0.0039 1.0000 0.2789
-10.250 -1.1753 0.03691 0.02819 0.0104 1.0000 0.2833
-10.000 -1.1826 0.03610 0.02728 0.0155 1.0000 0.2881
-9.750 -1.1628 0.03596 0.02735 0.0166 1.0000 0.2937
-9.500 -1.1651 0.03543 0.02677 0.0210 1.0000 0.2992
-9.250 -1.1794 0.03460 0.02568 0.0270 1.0000 0.3045
-9.000 -1.1569 0.03440 0.02573 0.0276 1.0000 0.3104
-8.750 -1.1508 0.03406 0.02541 0.0306 1.0000 0.3165
-8.500 -1.1572 0.03336 0.02448 0.0354 1.0000 0.3229
-8.250 -1.1389 0.03314 0.02446 0.0365 1.0000 0.3289
-8.000 -1.1023 0.03290 0.02420 0.0339 0.9933 0.3388
-7.750 -1.0619 0.03259 0.02393 0.0307 0.9855 0.3480
-7.500 -1.0208 0.03242 0.02374 0.0274 0.9774 0.3586
-7.250 -0.9847 0.03209 0.02346 0.0252 0.9681 0.3677
-7.000 -0.9421 0.03191 0.02328 0.0218 0.9604 0.3788
-6.750 -0.9108 0.03157 0.02299 0.0207 0.9497 0.3878
-6.500 -0.8664 0.03137 0.02279 0.0171 0.9424 0.3994
-6.250 -0.8391 0.03105 0.02251 0.0168 0.9309 0.4083
-6.000 -0.7940 0.03082 0.02230 0.0134 0.9237 0.4201
-5.750 -0.7679 0.03053 0.02206 0.0134 0.9120 0.4292
-5.500 -0.7245 0.03028 0.02183 0.0104 0.9045 0.4410
-5.250 -0.6950 0.03001 0.02161 0.0100 0.8938 0.4506
-5.000 -0.6561 0.02974 0.02137 0.0080 0.8851 0.4621
-4.750 -0.6006 0.02933 0.02104 0.0031 0.8807 0.4741
-4.500 -0.5864 0.02919 0.02089 0.0055 0.8662 0.4838
-4.250 -0.5335 0.02873 0.02051 0.0013 0.8611 0.4958
-4.000 -0.5082 0.02851 0.02028 0.0018 0.8500 0.5070
-3.750 -0.4679 0.02812 0.01997 0.0000 0.8416 0.5178
-3.500 -0.4239 0.02753 0.01934 -0.0024 0.8365 0.5312
-3.250 -0.4013 0.02748 0.01940 -0.0011 0.8228 0.5401
-3.000 -0.3626 0.02696 0.01885 -0.0024 0.8159 0.5531
-2.750 -0.3270 0.02671 0.01869 -0.0032 0.8065 0.5633
-2.500 -0.3014 0.02641 0.01838 -0.0024 0.7953 0.5753
-2.250 -0.2529 0.02589 0.01792 -0.0050 0.7896 0.5865
-2.000 -0.2404 0.02591 0.01795 -0.0021 0.7747 0.5977
-1.750 -0.1964 0.02545 0.01751 -0.0040 0.7676 0.6089
-1.500 -0.1793 0.02547 0.01755 -0.0018 0.7540 0.6204
-1.250 -0.1402 0.02511 0.01721 -0.0029 0.7453 0.6316
-1.000 -0.1188 0.02512 0.01724 -0.0013 0.7327 0.6432
-0.750 -0.0841 0.02488 0.01700 -0.0017 0.7228 0.6543
-0.500 -0.0592 0.02491 0.01704 -0.0007 0.7109 0.6661
-0.250 -0.0280 0.02476 0.01688 -0.0006 0.7000 0.6772
0.000 0.0000 0.02484 0.01698 0.0000 0.6887 0.6887
0.250 0.0280 0.02476 0.01688 0.0006 0.6772 0.7000
0.500 0.0592 0.02491 0.01704 0.0007 0.6661 0.7109
0.750 0.0841 0.02488 0.01700 0.0017 0.6543 0.7228
1.000 0.1188 0.02512 0.01724 0.0013 0.6432 0.7327
1.250 0.1402 0.02511 0.01721 0.0029 0.6316 0.7453
1.500 0.1793 0.02547 0.01755 0.0018 0.6204 0.7540
1.750 0.1964 0.02545 0.01751 0.0040 0.6089 0.7676
2.000 0.2404 0.02591 0.01794 0.0021 0.5977 0.7747
2.250 0.2529 0.02589 0.01792 0.0050 0.5865 0.7897
2.500 0.3014 0.02641 0.01838 0.0024 0.5753 0.7953
2.750 0.3269 0.02670 0.01869 0.0032 0.5633 0.8066
3.000 0.3626 0.02696 0.01885 0.0025 0.5531 0.8159
3.250 0.4012 0.02748 0.01940 0.0011 0.5401 0.8229
3.500 0.4238 0.02753 0.01934 0.0024 0.5312 0.8365
3.750 0.4679 0.02812 0.01997 0.0000 0.5178 0.8416
4.000 0.5080 0.02850 0.02027 -0.0018 0.5070 0.8501
4.250 0.5335 0.02873 0.02051 -0.0013 0.4959 0.8611
4.500 0.5863 0.02919 0.02089 -0.0055 0.4838 0.8662
4.750 0.6006 0.02933 0.02104 -0.0031 0.4741 0.8808
5.000 0.6561 0.02974 0.02136 -0.0080 0.4621 0.8852
5.250 0.6947 0.03000 0.02160 -0.0099 0.4506 0.8939
5.500 0.7245 0.03027 0.02182 -0.0105 0.4410 0.9046
5.750 0.7677 0.03052 0.02205 -0.0134 0.4292 0.9121
6.000 0.7941 0.03081 0.02229 -0.0134 0.4201 0.9238
6.250 0.8390 0.03104 0.02251 -0.0168 0.4083 0.9310
6.500 0.8665 0.03136 0.02278 -0.0172 0.3994 0.9425
6.750 0.9108 0.03156 0.02298 -0.0207 0.3878 0.9498
7.000 0.9423 0.03190 0.02327 -0.0219 0.3788 0.9605
7.250 0.9848 0.03207 0.02345 -0.0252 0.3677 0.9682
7.500 1.0210 0.03241 0.02373 -0.0275 0.3586 0.9775
7.750 1.0621 0.03257 0.02392 -0.0307 0.3480 0.9856
8.000 1.1026 0.03289 0.02418 -0.0339 0.3388 0.9934
8.250 1.1386 0.03312 0.02445 -0.0364 0.3289 1.0000
8.500 1.1571 0.03335 0.02446 -0.0354 0.3229 1.0000
8.750 1.1506 0.03405 0.02540 -0.0306 0.3166 1.0000
9.000 1.1566 0.03438 0.02572 -0.0275 0.3104 1.0000
9.250 1.1793 0.03458 0.02566 -0.0270 0.3045 1.0000
9.500 1.1649 0.03542 0.02675 -0.0209 0.2992 1.0000
9.750 1.1626 0.03595 0.02733 -0.0166 0.2937 1.0000
10.000 1.1823 0.03609 0.02727 -0.0154 0.2881 1.0000
10.250 1.1752 0.03689 0.02816 -0.0104 0.2834 1.0000
10.500 1.1583 0.03769 0.02910 -0.0039 0.2789 1.0000
10.750 1.1571 0.03815 0.02954 0.0004 0.2741 1.0000
11.000 1.1895 0.03840 0.02954 -0.0004 0.2683 1.0000
11.250 1.1560 0.03939 0.03074 0.0086 0.2652 1.0000
11.500 1.1238 0.04018 0.03165 0.0174 0.2622 1.0000
11.750 1.1071 0.04091 0.03241 0.0237 0.2585 1.0000
12.000 1.1684 0.04095 0.03212 0.0189 0.2516 1.0000
12.250 1.1244 0.04218 0.03354 0.0287 0.2494 1.0000
12.500 1.0881 0.04388 0.03543 0.0363 0.2464 1.0000
12.750 1.0690 0.04548 0.03713 0.0411 0.2426 1.0000
13.000 1.1120 0.04510 0.03651 0.0399 0.2371 1.0000
13.250 1.1001 0.04691 0.03840 0.0436 0.2336 1.0000
13.500 1.0508 0.05053 0.04231 0.0494 0.2308 1.0000
13.750 1.0028 0.05515 0.04717 0.0530 0.2276 1.0000
14.000 1.0307 0.05503 0.04693 0.0534 0.2230 1.0000
14.250 1.0674 0.05483 0.04659 0.0533 0.2186 1.0000
14.500 0.4349 0.15759 0.15074 0.0228 0.2518 1.0000
14.750 0.3756 0.15997 0.15311 0.0189 0.2446 1.0000
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