SELIG 3002-099-83 (s3002-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: SELIG 3002-099-83 (s3002-il) Reynolds number: 50,000 Max Cl/Cd: 35.29 at α=6.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s3002-il-50000.txt Download as CSV file: xf-s3002-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: SELIG 3002-099-83
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.3553 0.10544 0.09862 -0.0233 1.0000 0.2301
-8.250 -0.3432 0.10152 0.09475 -0.0224 1.0000 0.2401
-8.000 -0.3712 0.10203 0.09547 -0.0235 1.0000 0.2476
-7.750 -0.3513 0.09743 0.09088 -0.0217 1.0000 0.2617
-7.500 -0.3393 0.09371 0.08721 -0.0203 1.0000 0.2734
-7.250 -0.3406 0.09125 0.08486 -0.0192 1.0000 0.2845
-7.000 -0.3744 0.09189 0.08575 -0.0171 1.0000 0.2946
-6.750 -0.3681 0.08888 0.08282 -0.0148 1.0000 0.3098
-6.500 -0.3669 0.08636 0.08040 -0.0122 1.0000 0.3251
-6.250 -0.3708 0.08428 0.07842 -0.0091 1.0000 0.3407
-6.000 -0.3818 0.08276 0.07704 -0.0060 1.0000 0.3571
-5.750 -0.3606 0.07914 0.07343 -0.0024 1.0000 0.3830
-5.500 -0.3806 0.07847 0.07292 0.0019 1.0000 0.4036
-5.250 -0.3775 0.07635 0.07088 0.0065 1.0000 0.4346
-5.000 -0.3769 0.07449 0.06910 0.0112 1.0000 0.4662
-4.250 -0.3619 0.05079 0.04433 -0.0390 1.0000 0.1974
-4.000 -0.3209 0.04350 0.03608 -0.0461 1.0000 0.1487
-3.750 -0.2888 0.03928 0.03112 -0.0486 1.0000 0.1347
-3.500 -0.2592 0.03595 0.02721 -0.0500 1.0000 0.1285
-3.250 -0.2315 0.03363 0.02445 -0.0506 1.0000 0.1297
-3.000 -0.2038 0.03168 0.02209 -0.0509 1.0000 0.1330
-2.750 -0.1762 0.02993 0.01990 -0.0508 1.0000 0.1354
-2.500 -0.1510 0.02848 0.01823 -0.0505 1.0000 0.1430
-2.250 -0.1265 0.02741 0.01693 -0.0498 1.0000 0.1533
-2.000 -0.1046 0.02636 0.01591 -0.0486 1.0000 0.1673
-1.750 -0.0819 0.02537 0.01503 -0.0477 1.0000 0.1917
-1.500 -0.0540 0.02385 0.01398 -0.0478 1.0000 0.2676
-1.250 -0.0664 0.02118 0.01425 -0.0360 1.0000 0.8591
-1.000 -0.0498 0.02080 0.01351 -0.0342 1.0000 1.0000
-0.750 -0.0257 0.02123 0.01346 -0.0349 1.0000 1.0000
-0.500 -0.0023 0.02172 0.01359 -0.0357 1.0000 1.0000
-0.250 0.0204 0.02227 0.01383 -0.0364 1.0000 1.0000
0.000 0.0424 0.02288 0.01418 -0.0370 1.0000 1.0000
0.250 0.0638 0.02356 0.01463 -0.0376 1.0000 1.0000
0.500 0.1036 0.02468 0.01550 -0.0416 0.9907 1.0000
0.750 0.1573 0.02606 0.01663 -0.0479 0.9738 1.0000
1.000 0.2094 0.02731 0.01767 -0.0536 0.9566 1.0000
1.250 0.2533 0.02828 0.01851 -0.0577 0.9380 1.0000
1.500 0.2983 0.02922 0.01934 -0.0618 0.9192 1.0000
1.750 0.3449 0.03009 0.02013 -0.0658 0.9003 1.0000
2.000 0.3939 0.03085 0.02084 -0.0698 0.8818 1.0000
2.250 0.4310 0.03151 0.02147 -0.0719 0.8613 1.0000
2.500 0.4708 0.03207 0.02203 -0.0741 0.8409 1.0000
2.750 0.5174 0.03241 0.02240 -0.0768 0.8215 1.0000
3.000 0.5698 0.03242 0.02247 -0.0799 0.8032 1.0000
3.250 0.5980 0.03286 0.02295 -0.0798 0.7803 1.0000
3.500 0.6446 0.03261 0.02280 -0.0814 0.7609 1.0000
3.750 0.6918 0.03202 0.02229 -0.0824 0.7426 1.0000
4.000 0.7226 0.03200 0.02234 -0.0817 0.7203 1.0000
4.250 0.7622 0.03138 0.02182 -0.0814 0.6999 1.0000
4.500 0.8062 0.03032 0.02084 -0.0811 0.6809 1.0000
4.750 0.8333 0.03026 0.02087 -0.0796 0.6563 1.0000
5.000 0.8738 0.02923 0.01986 -0.0787 0.6352 1.0000
5.250 0.9005 0.02919 0.01988 -0.0772 0.6093 1.0000
5.500 0.9322 0.02885 0.01955 -0.0758 0.5843 1.0000
5.750 0.9645 0.02852 0.01916 -0.0745 0.5588 1.0000
6.000 0.9893 0.02884 0.01947 -0.0730 0.5310 1.0000
6.250 1.0146 0.02924 0.01987 -0.0715 0.5034 1.0000
6.500 1.0402 0.02971 0.02028 -0.0702 0.4764 1.0000
6.750 1.0667 0.03023 0.02066 -0.0689 0.4496 1.0000
7.000 1.0892 0.03111 0.02152 -0.0675 0.4229 1.0000
7.250 1.1101 0.03217 0.02262 -0.0661 0.3969 1.0000
7.500 1.1341 0.03316 0.02350 -0.0650 0.3724 1.0000
7.750 1.1541 0.03439 0.02477 -0.0636 0.3481 1.0000
8.000 1.1753 0.03573 0.02611 -0.0624 0.3256 1.0000
8.250 1.1940 0.03721 0.02765 -0.0610 0.3039 1.0000
8.500 1.2184 0.03851 0.02876 -0.0601 0.2836 1.0000
8.750 1.2328 0.04047 0.03097 -0.0585 0.2656 1.0000
9.000 1.2485 0.04244 0.03309 -0.0570 0.2488 1.0000
9.250 1.2641 0.04454 0.03536 -0.0556 0.2337 1.0000
9.500 1.2798 0.04681 0.03775 -0.0542 0.2205 1.0000
9.750 1.2970 0.04897 0.03997 -0.0531 0.2079 1.0000
10.000 1.3026 0.05207 0.04345 -0.0511 0.1988 1.0000
10.250 1.3068 0.05546 0.04713 -0.0493 0.1912 1.0000
10.500 1.3314 0.05749 0.04905 -0.0489 0.1805 1.0000
10.750 1.3107 0.06229 0.05448 -0.0458 0.1780 1.0000
11.000 1.2869 0.06741 0.06002 -0.0432 0.1766 1.0000
11.250 1.2549 0.07277 0.06566 -0.0408 0.1765 1.0000
11.500 1.2152 0.07901 0.07206 -0.0397 0.1776 1.0000
11.750 1.1728 0.08699 0.08014 -0.0412 0.1792 1.0000
12.000 1.1354 0.09642 0.08961 -0.0447 0.1806 1.0000
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Polar data table (+)
Polar graphs
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