AS5046 (16%) (as5046-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: AS5046 (16%) (as5046-il) Reynolds number: 200,000 Max Cl/Cd: 55.36 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-as5046-il-200000-n5.txt Download as CSV file: xf-as5046-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.250 -0.6429 0.09109 0.08709 -0.0395 1.0000 0.0134
-13.000 -0.6680 0.08274 0.07859 -0.0447 1.0000 0.0132
-12.750 -0.6912 0.07585 0.07155 -0.0484 1.0000 0.0131
-12.500 -0.7124 0.06997 0.06550 -0.0509 1.0000 0.0130
-12.250 -0.7317 0.06482 0.06016 -0.0525 1.0000 0.0129
-12.000 -0.7489 0.06024 0.05539 -0.0533 1.0000 0.0129
-11.750 -0.7639 0.05612 0.05107 -0.0534 1.0000 0.0128
-11.500 -0.7763 0.05243 0.04716 -0.0531 1.0000 0.0127
-11.250 -0.7858 0.04913 0.04365 -0.0522 1.0000 0.0127
-11.000 -0.7722 0.04456 0.03854 -0.0568 0.8751 0.0127
-10.750 -0.7662 0.04160 0.03511 -0.0570 0.8413 0.0127
-10.500 -0.7594 0.03914 0.03228 -0.0562 0.8254 0.0127
-10.250 -0.7491 0.03693 0.02974 -0.0553 0.8152 0.0128
-10.000 -0.7360 0.03495 0.02747 -0.0544 0.8078 0.0129
-9.750 -0.7191 0.03314 0.02539 -0.0537 0.8019 0.0131
-9.500 -0.6995 0.03150 0.02350 -0.0531 0.7971 0.0133
-9.250 -0.6783 0.03003 0.02182 -0.0525 0.7927 0.0135
-9.000 -0.6562 0.02874 0.02035 -0.0519 0.7886 0.0138
-8.750 -0.6344 0.02761 0.01906 -0.0513 0.7847 0.0141
-8.500 -0.6140 0.02655 0.01795 -0.0506 0.7812 0.0144
-8.250 -0.5945 0.02562 0.01699 -0.0500 0.7776 0.0148
-8.000 -0.5747 0.02478 0.01611 -0.0494 0.7743 0.0154
-7.750 -0.5546 0.02400 0.01525 -0.0489 0.7713 0.0163
-7.500 -0.5343 0.02325 0.01438 -0.0482 0.7686 0.0171
-7.250 -0.5160 0.02237 0.01348 -0.0476 0.7661 0.0179
-7.000 -0.4969 0.02156 0.01265 -0.0470 0.7633 0.0186
-6.750 -0.4772 0.02078 0.01184 -0.0465 0.7603 0.0194
-6.500 -0.4567 0.02005 0.01103 -0.0460 0.7575 0.0203
-6.250 -0.4357 0.01934 0.01026 -0.0456 0.7551 0.0215
-6.000 -0.4134 0.01873 0.00959 -0.0454 0.7528 0.0231
-5.750 -0.3900 0.01820 0.00898 -0.0452 0.7508 0.0258
-5.500 -0.3660 0.01771 0.00843 -0.0451 0.7488 0.0301
-5.250 -0.3422 0.01712 0.00786 -0.0449 0.7463 0.0372
-5.000 -0.3199 0.01629 0.00722 -0.0448 0.7437 0.0690
-4.750 -0.3068 0.01391 0.00607 -0.0450 0.7413 0.3052
-4.500 -0.2876 0.01274 0.00604 -0.0445 0.7391 0.5182
-4.250 -0.2599 0.01313 0.00654 -0.0440 0.7370 0.5801
-4.000 -0.2313 0.01372 0.00709 -0.0436 0.7349 0.6133
-3.750 -0.2029 0.01424 0.00753 -0.0432 0.7329 0.6295
-3.500 -0.1737 0.01431 0.00748 -0.0436 0.7309 0.6374
-3.250 -0.1453 0.01447 0.00760 -0.0435 0.7285 0.6415
-3.000 -0.1166 0.01455 0.00762 -0.0437 0.7259 0.6466
-2.750 -0.0868 0.01451 0.00743 -0.0444 0.7233 0.6527
-2.500 -0.0585 0.01458 0.00747 -0.0443 0.7209 0.6553
-2.250 -0.0299 0.01464 0.00748 -0.0444 0.7185 0.6582
-2.000 -0.0009 0.01468 0.00744 -0.0447 0.7163 0.6614
-1.750 0.0283 0.01467 0.00737 -0.0452 0.7137 0.6651
-1.500 0.0580 0.01461 0.00724 -0.0459 0.7106 0.6693
-1.250 0.0862 0.01463 0.00726 -0.0460 0.7073 0.6713
-1.000 0.1147 0.01465 0.00726 -0.0461 0.7042 0.6735
-0.750 0.1436 0.01466 0.00723 -0.0463 0.7013 0.6759
-0.500 0.1727 0.01466 0.00717 -0.0467 0.6983 0.6782
-0.250 0.2013 0.01462 0.00715 -0.0470 0.6937 0.6808
0.000 0.2305 0.01457 0.00706 -0.0475 0.6891 0.6835
0.250 0.2604 0.01451 0.00692 -0.0481 0.6850 0.6860
0.500 0.2890 0.01447 0.00687 -0.0483 0.6811 0.6874
0.750 0.3168 0.01445 0.00691 -0.0484 0.6757 0.6890
1.000 0.3453 0.01441 0.00689 -0.0485 0.6709 0.6907
1.250 0.3744 0.01436 0.00682 -0.0488 0.6668 0.6924
1.500 0.4028 0.01433 0.00683 -0.0490 0.6614 0.6942
1.750 0.4313 0.01427 0.00680 -0.0492 0.6548 0.6964
2.000 0.4606 0.01416 0.00664 -0.0495 0.6488 0.6986
2.250 0.4887 0.01407 0.00661 -0.0497 0.6389 0.7006
2.500 0.5179 0.01395 0.00646 -0.0501 0.6309 0.7025
2.750 0.5456 0.01387 0.00646 -0.0501 0.6210 0.7038
3.000 0.5734 0.01380 0.00646 -0.0501 0.6115 0.7054
3.250 0.6013 0.01371 0.00639 -0.0501 0.6011 0.7071
3.500 0.6291 0.01367 0.00640 -0.0501 0.5879 0.7088
3.750 0.6568 0.01362 0.00639 -0.0501 0.5732 0.7105
4.000 0.6843 0.01358 0.00633 -0.0500 0.5550 0.7122
4.250 0.7111 0.01360 0.00629 -0.0499 0.5310 0.7141
4.500 0.7371 0.01370 0.00628 -0.0496 0.5031 0.7163
4.750 0.7619 0.01392 0.00635 -0.0491 0.4716 0.7184
5.000 0.7852 0.01422 0.00652 -0.0485 0.4389 0.7200
5.250 0.8077 0.01459 0.00678 -0.0477 0.4074 0.7214
5.750 0.8517 0.01546 0.00743 -0.0462 0.3475 0.7246
6.000 0.8735 0.01592 0.00781 -0.0454 0.3205 0.7265
6.250 0.8951 0.01641 0.00821 -0.0447 0.2965 0.7287
6.500 0.9171 0.01687 0.00862 -0.0440 0.2751 0.7310
6.750 0.9389 0.01735 0.00905 -0.0434 0.2552 0.7331
7.000 0.9603 0.01786 0.00950 -0.0427 0.2370 0.7351
7.250 0.9806 0.01835 0.00998 -0.0419 0.2206 0.7367
7.500 1.0005 0.01886 0.01048 -0.0409 0.2056 0.7385
7.750 1.0203 0.01939 0.01101 -0.0400 0.1923 0.7404
8.000 1.0395 0.01993 0.01155 -0.0390 0.1809 0.7425
8.250 1.0577 0.02051 0.01213 -0.0379 0.1701 0.7448
8.500 1.0769 0.02104 0.01271 -0.0370 0.1603 0.7475
8.750 1.0943 0.02165 0.01334 -0.0358 0.1514 0.7502
9.000 1.1094 0.02225 0.01397 -0.0343 0.1424 0.7525
9.250 1.1235 0.02284 0.01463 -0.0326 0.1345 0.7548
9.500 1.1370 0.02361 0.01543 -0.0310 0.1263 0.7572
9.750 1.1530 0.02432 0.01622 -0.0299 0.1181 0.7599
10.000 1.1664 0.02522 0.01715 -0.0287 0.1107 0.7628
10.250 1.1806 0.02613 0.01810 -0.0277 0.1030 0.7658
10.500 1.1933 0.02718 0.01921 -0.0267 0.0963 0.7687
10.750 1.2053 0.02829 0.02039 -0.0257 0.0899 0.7716
11.000 1.2168 0.02951 0.02168 -0.0249 0.0844 0.7751
11.250 1.2280 0.03080 0.02304 -0.0242 0.0790 0.7791
11.500 1.2377 0.03227 0.02455 -0.0235 0.0746 0.7834
11.750 1.2484 0.03361 0.02603 -0.0228 0.0703 0.7876
12.000 1.2561 0.03523 0.02771 -0.0220 0.0666 0.7923
12.250 1.2645 0.03682 0.02940 -0.0213 0.0634 0.7975
12.500 1.2730 0.03839 0.03109 -0.0206 0.0603 0.8031
12.750 1.2787 0.04020 0.03299 -0.0199 0.0576 0.8097
13.250 1.2892 0.04389 0.03696 -0.0184 0.0530 0.8279
13.500 1.2931 0.04578 0.03901 -0.0175 0.0508 0.8423
13.750 1.2927 0.04776 0.04115 -0.0161 0.0492 0.8702
14.000 1.2843 0.04968 0.04322 -0.0137 0.0480 1.0000
14.250 1.2877 0.05206 0.04570 -0.0136 0.0464 1.0000
14.500 1.2911 0.05448 0.04823 -0.0135 0.0447 1.0000
14.750 1.2929 0.05711 0.05097 -0.0136 0.0432 1.0000
15.000 1.2929 0.06005 0.05399 -0.0139 0.0419 1.0000
15.250 1.2909 0.06333 0.05733 -0.0144 0.0408 1.0000
15.500 1.2895 0.06662 0.06071 -0.0149 0.0397 1.0000
15.750 1.2897 0.06983 0.06408 -0.0155 0.0385 1.0000
16.000 1.2884 0.07332 0.06769 -0.0163 0.0374 1.0000
16.250 1.2860 0.07705 0.07155 -0.0174 0.0364 1.0000
16.500 1.2825 0.08103 0.07563 -0.0187 0.0355 1.0000
16.750 1.2775 0.08527 0.07995 -0.0201 0.0347 1.0000
17.000 1.2714 0.08969 0.08444 -0.0216 0.0340 1.0000
17.250 1.2664 0.09411 0.08899 -0.0232 0.0333 1.0000
17.500 1.2610 0.09868 0.09372 -0.0250 0.0326 1.0000
17.750 1.2546 0.10349 0.09868 -0.0271 0.0318 1.0000
18.000 1.2476 0.10845 0.10378 -0.0293 0.0311 1.0000
18.250 1.2404 0.11356 0.10900 -0.0317 0.0305 1.0000
18.500 1.2330 0.11877 0.11433 -0.0344 0.0299 1.0000
18.750 1.2257 0.12403 0.11968 -0.0371 0.0293 1.0000
19.000 1.2191 0.12913 0.12487 -0.0398 0.0288 1.0000
19.250 1.2139 0.13393 0.12970 -0.0424 0.0283 1.0000
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Polar data table (+)
Polar graphs
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