AG455ct -02f rot. (ag455ct02r-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: AG455ct -02f rot. (ag455ct02r-il) Reynolds number: 50,000 Max Cl/Cd: 33.95 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ag455ct02r-il-50000-n5.txt Download as CSV file: xf-ag455ct02r-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: AG455ct -02f rot.
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.4520 0.09707 0.09077 0.0068 1.0000 0.1037
-8.000 -0.4531 0.09048 0.08415 0.0031 1.0000 0.0639
-7.750 -0.4576 0.08516 0.07887 -0.0004 1.0000 0.0531
-7.500 -0.4541 0.08089 0.07463 -0.0008 1.0000 0.0507
-7.250 -0.5395 0.08761 0.08111 0.0014 1.0000 0.0522
-7.000 -0.5305 0.08295 0.07646 -0.0015 1.0000 0.0491
-6.500 -0.5034 0.06997 0.06327 -0.0159 1.0000 0.0414
-6.250 -0.4898 0.06542 0.05866 -0.0181 1.0000 0.0406
-6.000 -0.4741 0.06059 0.05366 -0.0210 1.0000 0.0398
-5.750 -0.4559 0.05560 0.04845 -0.0241 1.0000 0.0395
-5.500 -0.4354 0.05065 0.04318 -0.0269 1.0000 0.0398
-5.250 -0.4128 0.04589 0.03797 -0.0293 1.0000 0.0405
-5.000 -0.3886 0.04163 0.03317 -0.0309 1.0000 0.0413
-4.750 -0.3634 0.03784 0.02881 -0.0318 1.0000 0.0418
-4.500 -0.3374 0.03441 0.02483 -0.0321 1.0000 0.0421
-4.250 -0.3114 0.03121 0.02121 -0.0323 1.0000 0.0428
-4.000 -0.2855 0.02860 0.01830 -0.0322 1.0000 0.0446
-3.750 -0.2591 0.02674 0.01614 -0.0319 1.0000 0.0496
-3.500 -0.2312 0.02488 0.01377 -0.0313 1.0000 0.0548
-3.250 -0.2053 0.02301 0.01188 -0.0306 1.0000 0.0597
-3.000 -0.1787 0.02163 0.01035 -0.0300 1.0000 0.0714
-2.750 -0.1522 0.02030 0.00894 -0.0293 1.0000 0.0865
-2.500 -0.1254 0.01904 0.00772 -0.0290 1.0000 0.1217
-2.250 -0.0995 0.01745 0.00673 -0.0290 1.0000 0.2239
-2.000 -0.0802 0.01541 0.00624 -0.0277 1.0000 0.5190
-1.750 -0.0464 0.01398 0.00570 -0.0262 1.0000 1.0000
-1.500 -0.0211 0.01395 0.00528 -0.0258 1.0000 1.0000
-1.250 0.0040 0.01394 0.00493 -0.0255 1.0000 1.0000
-1.000 0.0286 0.01396 0.00469 -0.0251 1.0000 1.0000
-0.750 0.0530 0.01400 0.00454 -0.0247 1.0000 1.0000
-0.500 0.0768 0.01407 0.00446 -0.0243 1.0000 1.0000
-0.250 0.1000 0.01419 0.00446 -0.0240 1.0000 1.0000
0.000 0.1237 0.01437 0.00453 -0.0240 0.9984 1.0000
0.250 0.1734 0.01458 0.00460 -0.0288 0.9654 1.0000
0.500 0.2195 0.01476 0.00467 -0.0326 0.9301 1.0000
0.750 0.2621 0.01492 0.00472 -0.0353 0.8934 1.0000
1.000 0.3006 0.01508 0.00478 -0.0369 0.8573 1.0000
1.250 0.3329 0.01529 0.00487 -0.0371 0.8215 1.0000
1.500 0.3615 0.01554 0.00499 -0.0365 0.7887 1.0000
1.750 0.3878 0.01583 0.00513 -0.0354 0.7581 1.0000
2.000 0.4130 0.01617 0.00534 -0.0342 0.7289 1.0000
2.250 0.4379 0.01655 0.00560 -0.0330 0.7009 1.0000
2.500 0.4628 0.01691 0.00596 -0.0321 0.6706 1.0000
2.750 0.4876 0.01723 0.00625 -0.0311 0.6410 1.0000
3.000 0.5124 0.01755 0.00653 -0.0300 0.6114 1.0000
3.250 0.5371 0.01786 0.00680 -0.0290 0.5816 1.0000
3.500 0.5619 0.01819 0.00708 -0.0280 0.5515 1.0000
3.750 0.5867 0.01855 0.00748 -0.0271 0.5197 1.0000
4.000 0.6114 0.01894 0.00784 -0.0262 0.4879 1.0000
4.250 0.6361 0.01937 0.00824 -0.0253 0.4563 1.0000
4.500 0.6607 0.01986 0.00868 -0.0245 0.4246 1.0000
4.750 0.6858 0.02040 0.00929 -0.0239 0.3921 1.0000
5.000 0.7106 0.02099 0.00988 -0.0233 0.3605 1.0000
5.250 0.7351 0.02165 0.01053 -0.0226 0.3300 1.0000
5.500 0.7594 0.02239 0.01126 -0.0221 0.3008 1.0000
5.750 0.7834 0.02319 0.01206 -0.0215 0.2724 1.0000
6.000 0.8071 0.02407 0.01304 -0.0210 0.2451 1.0000
6.250 0.8307 0.02503 0.01408 -0.0204 0.2193 1.0000
6.500 0.8538 0.02609 0.01523 -0.0199 0.1952 1.0000
6.750 0.8763 0.02724 0.01641 -0.0193 0.1736 1.0000
7.000 0.8986 0.02853 0.01784 -0.0187 0.1533 1.0000
7.250 0.9198 0.02988 0.01924 -0.0182 0.1351 1.0000
7.500 0.9414 0.03150 0.02110 -0.0175 0.1188 1.0000
7.750 0.9618 0.03318 0.02298 -0.0169 0.1036 1.0000
8.000 0.9815 0.03513 0.02511 -0.0161 0.0916 1.0000
8.250 1.0003 0.03716 0.02725 -0.0154 0.0818 1.0000
8.500 1.0178 0.03924 0.02961 -0.0148 0.0719 1.0000
8.750 1.0342 0.04248 0.03331 -0.0140 0.0661 1.0000
9.000 1.0488 0.04490 0.03602 -0.0134 0.0598 1.0000
9.250 1.0587 0.04844 0.04002 -0.0128 0.0549 1.0000
9.500 1.0646 0.05267 0.04477 -0.0124 0.0520 1.0000
9.750 1.0669 0.05690 0.04939 -0.0122 0.0500 1.0000
10.000 1.0689 0.06047 0.05317 -0.0121 0.0480 1.0000
10.250 1.0665 0.06444 0.05725 -0.0122 0.0464 1.0000
10.500 1.0499 0.06962 0.06276 -0.0133 0.0461 1.0000
10.750 1.0315 0.07534 0.06867 -0.0162 0.0462 1.0000
11.000 1.0135 0.08203 0.07550 -0.0209 0.0465 1.0000
|
Polar data table (+)
Polar graphs
<< Back to AG455ct -02f rot. (ag455ct02r-il)