AIRFOIL 3024 9.84% (s3024-il) Xfoil prediction polar at RE=500,000 Ncrit=9
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Airfoil: AIRFOIL 3024 9.84% (s3024-il) Reynolds number: 500,000 Max Cl/Cd: 110.05 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s3024-il-500000.txt Download as CSV file: xf-s3024-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.3309 0.09405 0.09186 -0.0392 1.0000 0.0180
-9.000 -0.3308 0.09099 0.08884 -0.0401 1.0000 0.0187
-8.750 -0.3359 0.08857 0.08648 -0.0397 0.9993 0.0188
-8.500 -0.3222 0.08380 0.08171 -0.0453 0.9906 0.0193
-8.250 -0.3050 0.07597 0.07388 -0.0577 0.9836 0.0206
-8.000 -0.2868 0.06918 0.06708 -0.0686 0.9742 0.0207
-7.750 -0.2728 0.06137 0.05921 -0.0804 0.9608 0.0207
-7.500 -0.2796 0.05561 0.05339 -0.0834 0.9471 0.0214
-7.250 -0.2739 0.05274 0.05045 -0.0843 0.9364 0.0217
-7.000 -0.2668 0.04959 0.04719 -0.0852 0.9274 0.0220
-6.750 -0.2578 0.04657 0.04406 -0.0859 0.9189 0.0226
-6.500 -0.2472 0.04291 0.04024 -0.0868 0.9111 0.0233
-6.250 -0.2354 0.03861 0.03568 -0.0874 0.9039 0.0251
-6.000 -0.2275 0.01719 0.01385 -0.0811 0.8817 0.0278
-5.750 -0.2094 0.01525 0.01189 -0.0809 0.8765 0.0286
-5.500 -0.1908 0.01361 0.01013 -0.0805 0.8719 0.0298
-5.250 -0.1699 0.01169 0.00798 -0.0804 0.8662 0.0324
-5.000 -0.1521 0.01799 0.01272 -0.0833 0.8742 0.0189
-4.750 -0.1274 0.01640 0.01086 -0.0826 0.8693 0.0189
-4.500 -0.1020 0.01502 0.00924 -0.0820 0.8639 0.0189
-4.250 -0.0767 0.01361 0.00759 -0.0812 0.8595 0.0182
-4.000 -0.0509 0.01262 0.00647 -0.0805 0.8547 0.0180
-3.750 -0.0249 0.01187 0.00563 -0.0800 0.8492 0.0183
-3.500 0.0012 0.01127 0.00494 -0.0795 0.8446 0.0190
-3.250 0.0277 0.01079 0.00439 -0.0791 0.8395 0.0199
-3.000 0.0545 0.01037 0.00391 -0.0788 0.8339 0.0209
-2.750 0.0809 0.00989 0.00335 -0.0783 0.8291 0.0234
-2.500 0.1082 0.00962 0.00306 -0.0781 0.8234 0.0280
-2.250 0.1343 0.00898 0.00267 -0.0777 0.8176 0.0874
-2.000 0.1607 0.00860 0.00249 -0.0775 0.8127 0.1598
-1.750 0.1871 0.00822 0.00238 -0.0774 0.8060 0.2437
-1.500 0.2128 0.00776 0.00228 -0.0772 0.8003 0.3595
-1.250 0.2376 0.00725 0.00223 -0.0767 0.7939 0.5079
-1.000 0.2604 0.00668 0.00219 -0.0757 0.7872 0.6767
-0.750 0.2805 0.00618 0.00221 -0.0735 0.7809 0.8430
-0.500 0.3237 0.00603 0.00219 -0.0760 0.7740 0.9636
-0.250 0.3738 0.00601 0.00206 -0.0807 0.7674 0.9897
0.000 0.4181 0.00598 0.00195 -0.0842 0.7590 1.0000
0.250 0.4431 0.00600 0.00190 -0.0836 0.7508 1.0000
0.500 0.4683 0.00603 0.00185 -0.0830 0.7419 1.0000
0.750 0.4936 0.00606 0.00183 -0.0824 0.7326 1.0000
1.000 0.5190 0.00611 0.00180 -0.0818 0.7234 1.0000
1.250 0.5444 0.00616 0.00179 -0.0813 0.7131 1.0000
1.500 0.5699 0.00621 0.00179 -0.0807 0.7021 1.0000
1.750 0.5954 0.00628 0.00181 -0.0802 0.6910 1.0000
2.000 0.6208 0.00636 0.00182 -0.0796 0.6790 1.0000
2.250 0.6461 0.00645 0.00186 -0.0791 0.6661 1.0000
2.500 0.6715 0.00655 0.00190 -0.0785 0.6520 1.0000
2.750 0.6968 0.00665 0.00195 -0.0780 0.6370 1.0000
3.000 0.7221 0.00678 0.00203 -0.0775 0.6208 1.0000
3.250 0.7472 0.00692 0.00211 -0.0769 0.6033 1.0000
3.500 0.7723 0.00708 0.00221 -0.0764 0.5851 1.0000
3.750 0.7970 0.00727 0.00232 -0.0758 0.5660 1.0000
4.000 0.8218 0.00747 0.00246 -0.0752 0.5459 1.0000
4.250 0.8463 0.00769 0.00261 -0.0746 0.5250 1.0000
4.500 0.8706 0.00793 0.00277 -0.0740 0.5031 1.0000
4.750 0.8948 0.00819 0.00295 -0.0734 0.4804 1.0000
5.000 0.9187 0.00846 0.00316 -0.0727 0.4571 1.0000
5.250 0.9421 0.00878 0.00339 -0.0720 0.4327 1.0000
5.500 0.9656 0.00909 0.00362 -0.0713 0.4078 1.0000
5.750 0.9887 0.00943 0.00388 -0.0706 0.3829 1.0000
6.000 1.0112 0.00982 0.00418 -0.0698 0.3559 1.0000
6.250 1.0329 0.01026 0.00449 -0.0689 0.3253 1.0000
6.500 1.0539 0.01076 0.00483 -0.0679 0.2928 1.0000
6.750 1.0750 0.01125 0.00520 -0.0670 0.2636 1.0000
7.000 1.0961 0.01173 0.00557 -0.0660 0.2376 1.0000
7.250 1.1169 0.01222 0.00596 -0.0651 0.2141 1.0000
7.500 1.1373 0.01274 0.00638 -0.0640 0.1897 1.0000
7.750 1.1573 0.01327 0.00682 -0.0630 0.1663 1.0000
8.000 1.1765 0.01384 0.00730 -0.0618 0.1456 1.0000
8.250 1.1949 0.01445 0.00781 -0.0605 0.1224 1.0000
8.500 1.2115 0.01517 0.00839 -0.0590 0.0973 1.0000
8.750 1.2258 0.01602 0.00907 -0.0571 0.0709 1.0000
9.000 1.2330 0.01727 0.01006 -0.0542 0.0343 1.0000
9.250 1.2400 0.01836 0.01103 -0.0511 0.0193 1.0000
9.500 1.2524 0.01912 0.01184 -0.0489 0.0165 1.0000
9.750 1.2649 0.01991 0.01268 -0.0468 0.0150 1.0000
10.000 1.2761 0.02080 0.01364 -0.0446 0.0141 1.0000
10.250 1.2844 0.02191 0.01485 -0.0422 0.0133 1.0000
10.500 1.2935 0.02299 0.01602 -0.0400 0.0130 1.0000
10.750 1.3029 0.02407 0.01721 -0.0380 0.0125 1.0000
11.000 1.3104 0.02531 0.01855 -0.0360 0.0122 1.0000
11.250 1.3173 0.02664 0.01997 -0.0340 0.0117 1.0000
11.500 1.3231 0.02810 0.02153 -0.0321 0.0116 1.0000
11.750 1.3288 0.02961 0.02312 -0.0304 0.0111 1.0000
12.000 1.3331 0.03129 0.02490 -0.0287 0.0108 1.0000
12.250 1.3351 0.03325 0.02695 -0.0271 0.0107 1.0000
12.500 1.3352 0.03548 0.02927 -0.0256 0.0105 1.0000
12.750 1.3347 0.03786 0.03178 -0.0242 0.0103 1.0000
13.000 1.3339 0.04037 0.03439 -0.0230 0.0102 1.0000
13.250 1.3314 0.04318 0.03731 -0.0219 0.0100 1.0000
13.500 1.3287 0.04618 0.04043 -0.0209 0.0099 1.0000
13.750 1.3259 0.04934 0.04371 -0.0200 0.0098 1.0000
14.000 1.3276 0.05202 0.04652 -0.0195 0.0097 1.0000
14.250 1.3287 0.05484 0.04947 -0.0193 0.0097 1.0000
14.500 1.3290 0.05786 0.05262 -0.0191 0.0097 1.0000
14.750 1.3284 0.06112 0.05602 -0.0191 0.0097 1.0000
15.000 1.3263 0.06464 0.05970 -0.0196 0.0096 1.0000
15.250 1.3232 0.06842 0.06363 -0.0201 0.0096 1.0000
15.500 1.3185 0.07260 0.06798 -0.0210 0.0095 1.0000
15.750 1.3124 0.07710 0.07265 -0.0222 0.0095 1.0000
16.000 1.3049 0.08196 0.07768 -0.0237 0.0095 1.0000
16.250 1.2961 0.08722 0.08310 -0.0258 0.0095 1.0000
16.500 1.2851 0.09308 0.08917 -0.0283 0.0095 1.0000
16.750 1.2736 0.09920 0.09545 -0.0311 0.0095 1.0000
17.000 1.2618 0.10562 0.10204 -0.0344 0.0095 1.0000
17.250 1.2473 0.11277 0.10937 -0.0382 0.0095 1.0000
17.500 1.2337 0.12005 0.11682 -0.0424 0.0095 1.0000
17.750 1.2179 0.12795 0.12487 -0.0469 0.0096 1.0000
18.000 1.2043 0.13582 0.13290 -0.0519 0.0095 1.0000
18.250 1.1871 0.14474 0.14198 -0.0575 0.0096 1.0000
18.500 1.1668 0.15457 0.15194 -0.0636 0.0097 1.0000
18.750 0.8282 0.19365 0.19194 -0.0858 0.0129 1.0000
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