AIRFOIL 3024 9.84% (s3024-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: AIRFOIL 3024 9.84% (s3024-il) Reynolds number: 200,000 Max Cl/Cd: 80.9 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s3024-il-200000.txt Download as CSV file: xf-s3024-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: AIRFOIL 3024 9.84%
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.3538 0.09294 0.08974 -0.0403 1.0000 0.0444
-8.250 -0.3785 0.09246 0.08936 -0.0366 1.0000 0.0446
-8.000 -0.4012 0.09182 0.08881 -0.0331 1.0000 0.0446
-7.750 -0.3959 0.08681 0.08381 -0.0432 0.9943 0.0449
-7.500 -0.3846 0.07943 0.07644 -0.0493 0.9889 0.0457
-7.250 -0.3673 0.07688 0.07388 -0.0470 0.9868 0.0470
-7.000 -0.3464 0.07305 0.07003 -0.0513 0.9824 0.0485
-6.750 -0.3255 0.06842 0.06535 -0.0579 0.9763 0.0510
-6.250 -0.2803 0.05343 0.04987 -0.0794 0.9621 0.0582
-6.000 -0.2518 0.05114 0.04764 -0.0813 0.9600 0.0610
-5.750 -0.2319 0.04785 0.04416 -0.0837 0.9525 0.0663
-5.500 -0.2046 0.04283 0.03883 -0.0886 0.9481 0.0728
-5.250 -0.1709 0.03993 0.03574 -0.0919 0.9456 0.0794
-5.000 -0.1561 0.03682 0.03232 -0.0918 0.9368 0.0864
-4.750 -0.1252 0.02701 0.02118 -0.0918 0.9326 0.0415
-4.500 -0.1004 0.02453 0.01787 -0.0901 0.9260 0.0351
-4.250 -0.0725 0.02183 0.01486 -0.0902 0.9213 0.0342
-4.000 -0.0393 0.02005 0.01278 -0.0909 0.9181 0.0341
-3.750 -0.0138 0.01901 0.01154 -0.0901 0.9121 0.0348
-3.500 0.0129 0.01759 0.01011 -0.0899 0.9067 0.0379
-3.250 0.0442 0.01677 0.00925 -0.0902 0.9031 0.0415
-3.000 0.0672 0.01618 0.00859 -0.0890 0.8960 0.0445
-2.750 0.0937 0.01530 0.00772 -0.0885 0.8907 0.0536
-2.500 0.1202 0.01399 0.00691 -0.0881 0.8869 0.1578
-2.250 0.1404 0.01347 0.00682 -0.0869 0.8784 0.2754
-2.000 0.1634 0.01255 0.00668 -0.0860 0.8738 0.4762
-1.750 0.1783 0.01182 0.00675 -0.0830 0.8662 0.6902
-1.500 0.2316 0.01122 0.00662 -0.0863 0.8637 0.9372
-1.250 0.3121 0.01091 0.00607 -0.0967 0.8627 1.0000
-1.000 0.3356 0.01082 0.00582 -0.0954 0.8572 1.0000
-0.750 0.3558 0.01088 0.00578 -0.0940 0.8477 1.0000
-0.500 0.3799 0.01080 0.00555 -0.0928 0.8421 1.0000
-0.250 0.4014 0.01084 0.00551 -0.0915 0.8327 1.0000
0.000 0.4256 0.01078 0.00534 -0.0904 0.8261 1.0000
0.250 0.4485 0.01078 0.00526 -0.0892 0.8172 1.0000
0.500 0.4724 0.01075 0.00514 -0.0881 0.8093 1.0000
0.750 0.4968 0.01069 0.00499 -0.0870 0.8010 1.0000
1.000 0.5206 0.01069 0.00494 -0.0860 0.7916 1.0000
1.250 0.5464 0.01059 0.00474 -0.0851 0.7842 1.0000
1.500 0.5702 0.01061 0.00473 -0.0842 0.7735 1.0000
1.750 0.5953 0.01059 0.00466 -0.0833 0.7639 1.0000
2.000 0.6214 0.01053 0.00453 -0.0826 0.7551 1.0000
2.250 0.6459 0.01055 0.00453 -0.0817 0.7435 1.0000
2.500 0.6710 0.01055 0.00451 -0.0809 0.7320 1.0000
2.750 0.6966 0.01055 0.00447 -0.0802 0.7205 1.0000
3.000 0.7223 0.01055 0.00443 -0.0795 0.7085 1.0000
3.250 0.7479 0.01058 0.00442 -0.0788 0.6955 1.0000
3.500 0.7731 0.01062 0.00443 -0.0781 0.6810 1.0000
3.750 0.7980 0.01069 0.00448 -0.0773 0.6653 1.0000
4.000 0.8228 0.01078 0.00458 -0.0765 0.6483 1.0000
4.250 0.8474 0.01089 0.00466 -0.0758 0.6302 1.0000
4.500 0.8721 0.01102 0.00474 -0.0750 0.6114 1.0000
4.750 0.8962 0.01120 0.00487 -0.0741 0.5911 1.0000
5.000 0.9199 0.01141 0.00505 -0.0733 0.5691 1.0000
5.250 0.9433 0.01166 0.00524 -0.0723 0.5465 1.0000
5.500 0.9661 0.01195 0.00547 -0.0714 0.5225 1.0000
5.750 0.9883 0.01227 0.00574 -0.0703 0.4970 1.0000
6.000 1.0101 0.01264 0.00606 -0.0692 0.4712 1.0000
6.250 1.0312 0.01305 0.00639 -0.0681 0.4449 1.0000
6.500 1.0516 0.01350 0.00676 -0.0668 0.4184 1.0000
6.750 1.0716 0.01397 0.00719 -0.0656 0.3912 1.0000
7.000 1.0911 0.01448 0.00764 -0.0643 0.3646 1.0000
7.250 1.1098 0.01504 0.00812 -0.0629 0.3381 1.0000
7.500 1.1273 0.01563 0.00863 -0.0613 0.3100 1.0000
7.750 1.1439 0.01627 0.00917 -0.0597 0.2816 1.0000
8.000 1.1600 0.01693 0.00977 -0.0580 0.2546 1.0000
8.250 1.1754 0.01763 0.01039 -0.0563 0.2305 1.0000
8.500 1.1909 0.01832 0.01102 -0.0546 0.2056 1.0000
8.750 1.2050 0.01906 0.01170 -0.0528 0.1815 1.0000
9.000 1.2167 0.01987 0.01242 -0.0506 0.1577 1.0000
9.250 1.2282 0.02067 0.01319 -0.0484 0.1369 1.0000
9.500 1.2386 0.02158 0.01405 -0.0461 0.1169 1.0000
9.750 1.2466 0.02272 0.01508 -0.0437 0.0895 1.0000
10.000 1.2444 0.02471 0.01676 -0.0403 0.0520 1.0000
10.250 1.2411 0.02684 0.01876 -0.0369 0.0385 1.0000
10.500 1.2458 0.02840 0.02041 -0.0346 0.0330 1.0000
10.750 1.2447 0.03044 0.02249 -0.0320 0.0298 1.0000
11.000 1.2498 0.03210 0.02428 -0.0301 0.0280 1.0000
11.250 1.2534 0.03393 0.02625 -0.0283 0.0265 1.0000
11.500 1.2566 0.03589 0.02829 -0.0266 0.0255 1.0000
11.750 1.2587 0.03803 0.03051 -0.0250 0.0246 1.0000
12.000 1.2602 0.04037 0.03292 -0.0235 0.0239 1.0000
12.250 1.2620 0.04301 0.03562 -0.0220 0.0232 1.0000
12.500 1.2696 0.04519 0.03792 -0.0207 0.0228 1.0000
12.750 1.2780 0.04735 0.04024 -0.0196 0.0224 1.0000
13.000 1.2867 0.04964 0.04268 -0.0185 0.0221 1.0000
13.250 1.2932 0.05213 0.04537 -0.0176 0.0217 1.0000
13.500 1.2976 0.05488 0.04834 -0.0168 0.0213 1.0000
13.750 1.2986 0.05770 0.05136 -0.0162 0.0207 1.0000
14.000 1.2984 0.06087 0.05473 -0.0158 0.0203 1.0000
14.250 1.2960 0.06435 0.05841 -0.0157 0.0201 1.0000
14.500 1.2909 0.06822 0.06251 -0.0158 0.0199 1.0000
14.750 1.2824 0.07271 0.06725 -0.0163 0.0200 1.0000
15.000 1.2710 0.07767 0.07246 -0.0173 0.0199 1.0000
15.250 1.2568 0.08326 0.07830 -0.0190 0.0200 1.0000
15.500 1.2401 0.08953 0.08483 -0.0214 0.0201 1.0000
15.750 1.2215 0.09643 0.09197 -0.0246 0.0203 1.0000
16.000 1.2014 0.10405 0.09983 -0.0286 0.0205 1.0000
16.250 1.1788 0.11272 0.10873 -0.0336 0.0207 1.0000
16.500 1.1564 0.12190 0.11811 -0.0394 0.0209 1.0000
16.750 1.1319 0.13226 0.12866 -0.0462 0.0212 1.0000
17.000 1.1048 0.14411 0.14067 -0.0540 0.0216 1.0000
17.250 1.0752 0.15780 0.15447 -0.0630 0.0222 1.0000
17.500 1.0503 0.17083 0.16753 -0.0707 0.0229 1.0000
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