AS5046 (16%) (as5046-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: AS5046 (16%) (as5046-il) Reynolds number: 500,000 Max Cl/Cd: 69.67 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-as5046-il-500000-n5.txt Download as CSV file: xf-as5046-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: AS5046 (16%)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.500 -0.7011 0.11763 0.11503 -0.0189 1.0000 0.0067
-15.250 -0.7851 0.09188 0.08879 -0.0337 1.0000 0.0065
-15.000 -0.8093 0.08288 0.07962 -0.0389 1.0000 0.0064
-14.750 -0.8303 0.07531 0.07186 -0.0430 1.0000 0.0064
-14.500 -0.8488 0.06881 0.06517 -0.0461 1.0000 0.0064
-14.250 -0.8648 0.06329 0.05947 -0.0483 1.0000 0.0064
-14.000 -0.8750 0.05808 0.05403 -0.0512 0.9331 0.0064
-13.750 -0.8759 0.05322 0.04855 -0.0553 0.8206 0.0065
-13.500 -0.8829 0.04992 0.04494 -0.0554 0.7966 0.0065
-13.250 -0.8870 0.04690 0.04168 -0.0554 0.7841 0.0065
-13.000 -0.8905 0.04391 0.03846 -0.0552 0.7758 0.0065
-12.750 -0.8909 0.04126 0.03561 -0.0548 0.7688 0.0066
-12.500 -0.8878 0.03902 0.03320 -0.0543 0.7634 0.0066
-12.250 -0.8814 0.03713 0.03118 -0.0539 0.7586 0.0067
-12.000 -0.8727 0.03552 0.02945 -0.0535 0.7540 0.0068
-11.750 -0.8627 0.03403 0.02784 -0.0530 0.7499 0.0069
-11.500 -0.8512 0.03266 0.02636 -0.0526 0.7464 0.0070
-11.250 -0.8387 0.03134 0.02494 -0.0522 0.7430 0.0071
-11.000 -0.8252 0.03008 0.02356 -0.0517 0.7399 0.0072
-10.750 -0.8107 0.02886 0.02223 -0.0511 0.7372 0.0074
-10.500 -0.7955 0.02769 0.02093 -0.0505 0.7346 0.0075
-10.000 -0.7633 0.02544 0.01847 -0.0491 0.7303 0.0077
-9.750 -0.7465 0.02439 0.01733 -0.0485 0.7281 0.0078
-9.500 -0.7296 0.02338 0.01624 -0.0479 0.7257 0.0080
-9.250 -0.7126 0.02242 0.01519 -0.0472 0.7233 0.0081
-9.000 -0.6966 0.02152 0.01422 -0.0464 0.7212 0.0082
-8.750 -0.6807 0.02071 0.01332 -0.0455 0.7193 0.0084
-8.500 -0.6617 0.01994 0.01247 -0.0450 0.7175 0.0086
-8.250 -0.6418 0.01926 0.01171 -0.0445 0.7158 0.0087
-8.000 -0.6229 0.01841 0.01083 -0.0440 0.7143 0.0090
-7.750 -0.6015 0.01776 0.01016 -0.0437 0.7125 0.0092
-7.500 -0.5790 0.01720 0.00957 -0.0434 0.7106 0.0095
-7.250 -0.5558 0.01666 0.00900 -0.0433 0.7087 0.0099
-7.000 -0.5320 0.01616 0.00846 -0.0431 0.7070 0.0103
-6.750 -0.5077 0.01568 0.00793 -0.0430 0.7055 0.0107
-6.500 -0.4827 0.01526 0.00745 -0.0430 0.7039 0.0112
-6.250 -0.4578 0.01479 0.00697 -0.0430 0.7024 0.0119
-6.000 -0.4318 0.01445 0.00660 -0.0431 0.7009 0.0129
-5.750 -0.4054 0.01414 0.00623 -0.0432 0.6993 0.0140
-5.500 -0.3791 0.01375 0.00583 -0.0433 0.6978 0.0155
-5.250 -0.3520 0.01343 0.00549 -0.0435 0.6963 0.0172
-5.000 -0.3250 0.01310 0.00517 -0.0437 0.6948 0.0202
-4.750 -0.2976 0.01280 0.00487 -0.0439 0.6933 0.0255
-4.500 -0.2705 0.01239 0.00456 -0.0442 0.6917 0.0442
-4.250 -0.2470 0.01116 0.00392 -0.0448 0.6900 0.1774
-4.000 -0.2222 0.00972 0.00324 -0.0459 0.6882 0.3557
-3.750 -0.1950 0.00866 0.00288 -0.0469 0.6867 0.5205
-3.500 -0.1655 0.00864 0.00301 -0.0473 0.6851 0.5766
-3.250 -0.1357 0.00876 0.00311 -0.0476 0.6835 0.5989
-3.000 -0.1059 0.00885 0.00316 -0.0480 0.6817 0.6091
-2.750 -0.0759 0.00890 0.00317 -0.0484 0.6798 0.6161
-2.500 -0.0459 0.00891 0.00313 -0.0488 0.6776 0.6210
-2.250 -0.0163 0.00894 0.00316 -0.0492 0.6754 0.6245
-2.000 0.0135 0.00896 0.00315 -0.0496 0.6730 0.6280
-1.750 0.0433 0.00898 0.00312 -0.0500 0.6706 0.6314
-1.500 0.0733 0.00900 0.00307 -0.0505 0.6680 0.6345
-1.250 0.1031 0.00902 0.00303 -0.0509 0.6652 0.6369
-1.000 0.1325 0.00899 0.00303 -0.0512 0.6617 0.6390
-0.750 0.1620 0.00899 0.00304 -0.0516 0.6576 0.6415
-0.500 0.1916 0.00899 0.00302 -0.0519 0.6538 0.6438
-0.250 0.2212 0.00899 0.00298 -0.0523 0.6506 0.6458
0.000 0.2509 0.00899 0.00297 -0.0527 0.6474 0.6477
0.250 0.2807 0.00897 0.00296 -0.0532 0.6434 0.6494
0.500 0.3104 0.00896 0.00293 -0.0536 0.6390 0.6510
0.750 0.3401 0.00895 0.00288 -0.0540 0.6344 0.6526
1.000 0.3693 0.00890 0.00287 -0.0543 0.6274 0.6539
1.250 0.3984 0.00886 0.00282 -0.0545 0.6186 0.6551
1.500 0.4276 0.00884 0.00282 -0.0549 0.6099 0.6564
1.750 0.4566 0.00884 0.00280 -0.0551 0.6012 0.6578
2.000 0.4857 0.00884 0.00282 -0.0554 0.5902 0.6593
2.250 0.5145 0.00886 0.00282 -0.0556 0.5777 0.6607
2.500 0.5431 0.00890 0.00283 -0.0558 0.5635 0.6621
2.750 0.5710 0.00899 0.00285 -0.0559 0.5430 0.6635
3.000 0.5980 0.00915 0.00291 -0.0558 0.5150 0.6651
3.250 0.6245 0.00937 0.00301 -0.0557 0.4862 0.6666
3.500 0.6507 0.00965 0.00315 -0.0555 0.4567 0.6680
3.750 0.6764 0.00997 0.00333 -0.0553 0.4251 0.6692
4.000 0.7020 0.01027 0.00353 -0.0551 0.3955 0.6704
4.250 0.7275 0.01057 0.00374 -0.0549 0.3682 0.6716
4.500 0.7526 0.01091 0.00399 -0.0546 0.3405 0.6729
4.750 0.7774 0.01128 0.00424 -0.0543 0.3126 0.6744
5.000 0.8025 0.01161 0.00450 -0.0540 0.2880 0.6758
5.250 0.8277 0.01193 0.00475 -0.0538 0.2678 0.6772
5.500 0.8526 0.01228 0.00502 -0.0535 0.2480 0.6786
5.750 0.8775 0.01262 0.00529 -0.0532 0.2297 0.6800
6.000 0.9022 0.01295 0.00558 -0.0529 0.2134 0.6814
6.250 0.9265 0.01332 0.00588 -0.0526 0.1967 0.6829
6.500 0.9507 0.01369 0.00620 -0.0522 0.1823 0.6844
6.750 0.9749 0.01405 0.00652 -0.0518 0.1708 0.6859
7.000 0.9994 0.01435 0.00683 -0.0515 0.1612 0.6873
7.250 1.0231 0.01469 0.00716 -0.0510 0.1520 0.6886
7.500 1.0467 0.01504 0.00752 -0.0506 0.1431 0.6900
7.750 1.0701 0.01539 0.00788 -0.0501 0.1347 0.6914
8.250 1.1152 0.01617 0.00866 -0.0489 0.1178 0.6944
8.500 1.1367 0.01661 0.00908 -0.0481 0.1093 0.6960
8.750 1.1573 0.01708 0.00954 -0.0473 0.1004 0.6977
9.000 1.1779 0.01754 0.01001 -0.0464 0.0926 0.6995
9.250 1.1970 0.01807 0.01053 -0.0453 0.0854 0.7013
9.500 1.2153 0.01861 0.01106 -0.0442 0.0785 0.7029
9.750 1.2314 0.01914 0.01162 -0.0426 0.0731 0.7046
10.000 1.2453 0.01970 0.01222 -0.0407 0.0681 0.7063
10.250 1.2606 0.02035 0.01290 -0.0392 0.0637 0.7081
10.500 1.2759 0.02103 0.01362 -0.0379 0.0593 0.7099
10.750 1.2897 0.02184 0.01445 -0.0364 0.0554 0.7119
11.000 1.3045 0.02262 0.01529 -0.0353 0.0522 0.7139
11.250 1.3175 0.02358 0.01628 -0.0341 0.0490 0.7159
11.500 1.3304 0.02460 0.01735 -0.0331 0.0464 0.7178
11.750 1.3436 0.02567 0.01848 -0.0323 0.0439 0.7198
12.000 1.3556 0.02689 0.01976 -0.0316 0.0417 0.7218
12.250 1.3670 0.02819 0.02113 -0.0309 0.0397 0.7241
12.500 1.3795 0.02943 0.02247 -0.0304 0.0380 0.7267
12.750 1.3903 0.03082 0.02392 -0.0298 0.0363 0.7295
13.000 1.3994 0.03236 0.02551 -0.0291 0.0346 0.7323
13.250 1.4083 0.03394 0.02716 -0.0285 0.0334 0.7351
13.500 1.4180 0.03544 0.02877 -0.0280 0.0322 0.7379
13.750 1.4262 0.03706 0.03048 -0.0274 0.0308 0.7409
14.000 1.4329 0.03885 0.03235 -0.0268 0.0296 0.7443
14.250 1.4372 0.04087 0.03444 -0.0262 0.0286 0.7477
14.500 1.4427 0.04279 0.03646 -0.0256 0.0277 0.7513
14.750 1.4482 0.04474 0.03853 -0.0252 0.0269 0.7554
15.000 1.4521 0.04688 0.04078 -0.0248 0.0260 0.7601
15.250 1.4545 0.04918 0.04318 -0.0244 0.0252 0.7653
15.500 1.4555 0.05171 0.04581 -0.0242 0.0244 0.7711
15.750 1.4543 0.05461 0.04881 -0.0241 0.0236 0.7783
16.000 1.4561 0.05726 0.05160 -0.0242 0.0231 0.7872
16.250 1.4570 0.06010 0.05462 -0.0244 0.0225 0.7999
16.500 1.4566 0.06316 0.05787 -0.0248 0.0219 0.8208
16.750 1.4449 0.06562 0.06068 -0.0225 0.0215 1.0000
17.000 1.4421 0.06924 0.06438 -0.0233 0.0209 1.0000
17.250 1.4371 0.07323 0.06846 -0.0243 0.0204 1.0000
17.500 1.4301 0.07763 0.07296 -0.0255 0.0199 1.0000
17.750 1.4207 0.08249 0.07792 -0.0270 0.0196 1.0000
18.000 1.4142 0.08699 0.08255 -0.0285 0.0192 1.0000
18.250 1.4058 0.09183 0.08752 -0.0302 0.0189 1.0000
18.500 1.3960 0.09699 0.09280 -0.0321 0.0186 1.0000
18.750 1.3853 0.10238 0.09831 -0.0343 0.0183 1.0000
19.000 1.3732 0.10807 0.10412 -0.0367 0.0180 1.0000
19.250 1.3603 0.11394 0.11011 -0.0393 0.0177 1.0000
|
Polar data table (+)
Polar graphs
<< Back to AS5046 (16%) (as5046-il)