AS5046 (16%) (as5046-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: AS5046 (16%) (as5046-il) Reynolds number: 200,000 Max Cl/Cd: 58.09 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-as5046-il-200000.txt Download as CSV file: xf-as5046-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.000 -0.4471 0.09529 0.09208 -0.0488 1.0000 0.0717
-11.750 -0.4853 0.08643 0.08316 -0.0539 1.0000 0.0717
-11.500 -0.5170 0.07946 0.07614 -0.0569 1.0000 0.0717
-11.250 -0.5470 0.07341 0.07002 -0.0588 1.0000 0.0716
-11.000 -0.5751 0.06815 0.06469 -0.0597 1.0000 0.0715
-10.750 -0.6670 0.07069 0.06700 -0.0551 1.0000 0.0649
-10.500 -0.6836 0.06709 0.06335 -0.0553 1.0000 0.0657
-10.250 -0.7023 0.06405 0.06024 -0.0545 1.0000 0.0665
-10.000 -0.7212 0.06160 0.05772 -0.0522 1.0000 0.0677
-9.750 -0.7474 0.06080 0.05641 -0.0508 0.9770 0.0716
-9.500 -0.7288 0.05396 0.04954 -0.0546 0.9431 0.0753
-9.250 -0.6986 0.05072 0.04615 -0.0584 0.9243 0.0803
-9.000 -0.6843 0.04695 0.04202 -0.0610 0.9068 0.0885
-8.750 -0.6626 0.03686 0.03022 -0.0578 0.8953 0.0416
-8.500 -0.6336 0.03185 0.02459 -0.0573 0.8870 0.0327
-8.250 -0.6081 0.03018 0.02225 -0.0566 0.8792 0.0302
-8.000 -0.5785 0.02798 0.01994 -0.0568 0.8728 0.0299
-7.750 -0.5498 0.02640 0.01819 -0.0567 0.8672 0.0300
-7.500 -0.5223 0.02516 0.01681 -0.0565 0.8618 0.0302
-7.250 -0.4947 0.02361 0.01533 -0.0563 0.8573 0.0311
-7.000 -0.4705 0.02272 0.01448 -0.0560 0.8530 0.0330
-6.750 -0.4466 0.02195 0.01365 -0.0554 0.8492 0.0346
-6.500 -0.4243 0.02114 0.01281 -0.0547 0.8452 0.0357
-6.250 -0.4055 0.02011 0.01181 -0.0538 0.8409 0.0371
-6.000 -0.3868 0.01922 0.01093 -0.0531 0.8368 0.0393
-5.750 -0.3656 0.01852 0.01016 -0.0526 0.8335 0.0426
-5.500 -0.3453 0.01769 0.00931 -0.0523 0.8305 0.0491
-5.250 -0.3246 0.01676 0.00844 -0.0519 0.8272 0.0654
-5.000 -0.3264 0.01293 0.00716 -0.0506 0.8232 0.5103
-4.750 -0.2995 0.01411 0.00850 -0.0490 0.8199 0.6071
-4.500 -0.2716 0.01536 0.00970 -0.0476 0.8172 0.6327
-4.250 -0.2445 0.01660 0.01091 -0.0460 0.8147 0.6506
-4.000 -0.2193 0.01817 0.01254 -0.0432 0.8115 0.6674
-3.750 -0.1938 0.01908 0.01346 -0.0411 0.8083 0.6752
-3.500 -0.1666 0.01920 0.01349 -0.0410 0.8051 0.6833
-3.250 -0.1400 0.01932 0.01351 -0.0406 0.8020 0.6890
-3.000 -0.1135 0.01961 0.01374 -0.0397 0.7992 0.6932
-2.750 -0.0853 0.01942 0.01343 -0.0410 0.7961 0.7026
-2.500 -0.0602 0.01955 0.01356 -0.0399 0.7925 0.7053
-2.250 -0.0343 0.01967 0.01365 -0.0393 0.7890 0.7089
-2.000 -0.0069 0.01963 0.01354 -0.0395 0.7855 0.7143
-1.750 0.0216 0.01948 0.01328 -0.0404 0.7825 0.7201
-1.500 0.0465 0.01955 0.01336 -0.0397 0.7786 0.7228
-1.250 0.0725 0.01956 0.01337 -0.0394 0.7743 0.7262
-1.000 0.1003 0.01948 0.01323 -0.0398 0.7701 0.7307
-0.750 0.1306 0.01932 0.01295 -0.0412 0.7663 0.7358
-0.500 0.1551 0.01933 0.01299 -0.0405 0.7616 0.7380
-0.250 0.1807 0.01932 0.01300 -0.0401 0.7562 0.7408
0.000 0.2083 0.01927 0.01290 -0.0401 0.7515 0.7441
0.250 0.2369 0.01922 0.01281 -0.0407 0.7467 0.7479
0.500 0.2666 0.01910 0.01266 -0.0419 0.7404 0.7517
0.750 0.2929 0.01898 0.01254 -0.0415 0.7354 0.7538
1.000 0.3202 0.01896 0.01250 -0.0413 0.7309 0.7558
1.250 0.3460 0.01892 0.01251 -0.0412 0.7240 0.7582
1.500 0.3748 0.01879 0.01237 -0.0415 0.7185 0.7609
1.750 0.4037 0.01871 0.01226 -0.0420 0.7124 0.7636
2.000 0.4332 0.01851 0.01206 -0.0426 0.7044 0.7661
2.250 0.4644 0.01824 0.01172 -0.0432 0.6983 0.7686
2.500 0.4895 0.01804 0.01160 -0.0427 0.6888 0.7705
2.750 0.5191 0.01777 0.01129 -0.0428 0.6830 0.7723
3.000 0.5454 0.01762 0.01122 -0.0427 0.6738 0.7743
3.250 0.5754 0.01733 0.01091 -0.0429 0.6672 0.7765
3.500 0.6030 0.01715 0.01080 -0.0431 0.6578 0.7792
3.750 0.6341 0.01682 0.01045 -0.0437 0.6505 0.7816
4.000 0.6631 0.01658 0.01029 -0.0442 0.6398 0.7836
4.250 0.6925 0.01619 0.00990 -0.0443 0.6309 0.7854
4.500 0.7192 0.01585 0.00965 -0.0440 0.6189 0.7873
4.750 0.7459 0.01555 0.00943 -0.0436 0.6049 0.7896
5.000 0.7733 0.01525 0.00918 -0.0434 0.5885 0.7919
5.250 0.8008 0.01499 0.00892 -0.0433 0.5685 0.7941
5.500 0.8275 0.01484 0.00873 -0.0431 0.5412 0.7963
5.750 0.8531 0.01484 0.00858 -0.0428 0.5070 0.7986
6.000 0.8766 0.01509 0.00864 -0.0422 0.4672 0.8010
6.250 0.8964 0.01545 0.00884 -0.0409 0.4292 0.8033
6.500 0.9156 0.01595 0.00916 -0.0396 0.3934 0.8056
6.750 0.9349 0.01650 0.00957 -0.0385 0.3600 0.8079
7.000 0.9542 0.01708 0.01002 -0.0375 0.3294 0.8104
7.250 0.9740 0.01767 0.01051 -0.0367 0.3023 0.8130
7.500 0.9932 0.01833 0.01104 -0.0358 0.2793 0.8158
7.750 1.0125 0.01888 0.01156 -0.0349 0.2590 0.8185
8.000 1.0302 0.01945 0.01210 -0.0336 0.2419 0.8214
8.250 1.0481 0.02005 0.01268 -0.0325 0.2269 0.8243
8.500 1.0655 0.02071 0.01331 -0.0314 0.2134 0.8274
8.750 1.0826 0.02141 0.01396 -0.0303 0.2007 0.8306
9.000 1.1005 0.02203 0.01462 -0.0294 0.1884 0.8339
9.250 1.1136 0.02265 0.01530 -0.0275 0.1776 0.8371
9.500 1.1247 0.02345 0.01608 -0.0255 0.1678 0.8412
9.750 1.1389 0.02422 0.01690 -0.0241 0.1573 0.8459
10.000 1.1532 0.02509 0.01784 -0.0230 0.1472 0.8506
10.250 1.1635 0.02611 0.01885 -0.0214 0.1384 0.8554
10.500 1.1761 0.02705 0.01990 -0.0203 0.1293 0.8609
10.750 1.1877 0.02822 0.02111 -0.0193 0.1210 0.8670
11.000 1.1962 0.02942 0.02234 -0.0179 0.1138 0.8739
11.500 1.2138 0.03193 0.02500 -0.0154 0.1010 0.8941
11.750 1.2189 0.03310 0.02632 -0.0132 0.0959 0.9144
12.000 1.2211 0.03416 0.02751 -0.0110 0.0915 1.0000
12.250 1.2330 0.03593 0.02920 -0.0109 0.0865 1.0000
12.500 1.2459 0.03753 0.03093 -0.0111 0.0820 1.0000
12.750 1.2562 0.03926 0.03266 -0.0111 0.0781 1.0000
13.000 1.2668 0.04104 0.03444 -0.0105 0.0745 1.0000
13.250 1.2761 0.04284 0.03637 -0.0103 0.0713 1.0000
13.500 1.2846 0.04465 0.03822 -0.0100 0.0683 1.0000
13.750 1.2961 0.04640 0.03986 -0.0091 0.0652 1.0000
14.000 1.3006 0.04857 0.04225 -0.0088 0.0632 1.0000
14.250 1.3060 0.05070 0.04452 -0.0085 0.0609 1.0000
14.500 1.3119 0.05275 0.04662 -0.0082 0.0588 1.0000
14.750 1.3209 0.05464 0.04844 -0.0076 0.0566 1.0000
15.000 1.3241 0.05718 0.05114 -0.0071 0.0549 1.0000
15.250 1.3231 0.06000 0.05418 -0.0070 0.0535 1.0000
15.500 1.3225 0.06284 0.05719 -0.0070 0.0520 1.0000
15.750 1.3231 0.06559 0.06003 -0.0070 0.0506 1.0000
16.000 1.3266 0.06804 0.06251 -0.0071 0.0492 1.0000
16.250 1.3338 0.07050 0.06495 -0.0064 0.0475 1.0000
16.500 1.3234 0.07462 0.06932 -0.0072 0.0469 1.0000
16.750 1.3126 0.07906 0.07401 -0.0084 0.0461 1.0000
17.000 1.3018 0.08377 0.07894 -0.0098 0.0454 1.0000
17.250 1.2905 0.08875 0.08412 -0.0115 0.0446 1.0000
17.500 1.2781 0.09405 0.08962 -0.0136 0.0439 1.0000
17.750 1.2649 0.09969 0.09544 -0.0162 0.0433 1.0000
|
Polar data table (+)
Polar graphs
<< Back to AS5046 (16%) (as5046-il)