AS5045 (15%) (as5045-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: AS5045 (15%) (as5045-il) Reynolds number: 500,000 Max Cl/Cd: 70.33 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-as5045-il-500000-n5.txt Download as CSV file: xf-as5045-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: AS5045 (15%)
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
------ -------- --------- --------- -------- -------- --------
-13.250 -0.7120 0.08781 0.08447 -0.0251 0.7431 0.0068
-13.000 -0.7501 0.07603 0.07247 -0.0328 0.7418 0.0067
-12.750 -0.7807 0.06761 0.06382 -0.0374 0.7402 0.0066
-12.500 -0.8072 0.06071 0.05669 -0.0402 0.7383 0.0066
-12.250 -0.8295 0.05488 0.05060 -0.0419 0.7365 0.0066
-12.000 -0.8472 0.04987 0.04534 -0.0427 0.7346 0.0066
-11.750 -0.8597 0.04559 0.04079 -0.0430 0.7328 0.0067
-11.500 -0.8672 0.04189 0.03682 -0.0428 0.7308 0.0067
-11.250 -0.8697 0.03870 0.03337 -0.0425 0.7288 0.0068
-11.000 -0.8676 0.03595 0.03036 -0.0419 0.7267 0.0069
-10.750 -0.8613 0.03357 0.02775 -0.0414 0.7246 0.0070
-10.500 -0.8519 0.03153 0.02547 -0.0407 0.7225 0.0071
-10.250 -0.8410 0.02982 0.02355 -0.0398 0.7207 0.0072
-10.000 -0.8257 0.02828 0.02180 -0.0393 0.7192 0.0073
-9.750 -0.8080 0.02689 0.02025 -0.0389 0.7177 0.0074
-9.500 -0.7890 0.02566 0.01886 -0.0385 0.7162 0.0075
-9.250 -0.7690 0.02457 0.01764 -0.0381 0.7147 0.0076
-9.000 -0.7482 0.02358 0.01653 -0.0377 0.7131 0.0076
-8.750 -0.7268 0.02266 0.01552 -0.0374 0.7115 0.0077
-8.500 -0.7059 0.02164 0.01441 -0.0370 0.7098 0.0078
-8.250 -0.6853 0.02063 0.01334 -0.0367 0.7082 0.0081
-8.000 -0.6627 0.01989 0.01256 -0.0366 0.7068 0.0083
-7.750 -0.6394 0.01922 0.01185 -0.0365 0.7055 0.0085
-7.500 -0.6156 0.01858 0.01115 -0.0365 0.7042 0.0088
-7.250 -0.5917 0.01791 0.01042 -0.0365 0.7030 0.0090
-7.000 -0.5673 0.01722 0.00969 -0.0366 0.7017 0.0092
-6.750 -0.5423 0.01657 0.00900 -0.0367 0.7002 0.0094
-6.500 -0.5167 0.01597 0.00835 -0.0369 0.6987 0.0096
-6.250 -0.4905 0.01542 0.00776 -0.0372 0.6973 0.0099
-6.000 -0.4638 0.01494 0.00722 -0.0375 0.6960 0.0102
-5.750 -0.4369 0.01441 0.00667 -0.0379 0.6947 0.0105
-5.500 -0.4094 0.01397 0.00620 -0.0383 0.6934 0.0111
-5.250 -0.3815 0.01361 0.00581 -0.0387 0.6921 0.0117
-5.000 -0.3532 0.01330 0.00545 -0.0391 0.6907 0.0125
-4.750 -0.3248 0.01300 0.00511 -0.0395 0.6893 0.0135
-4.500 -0.2962 0.01272 0.00481 -0.0399 0.6880 0.0155
-4.250 -0.2673 0.01243 0.00453 -0.0405 0.6869 0.0202
-4.000 -0.2384 0.01201 0.00421 -0.0411 0.6857 0.0412
-3.750 -0.2100 0.01059 0.00354 -0.0429 0.6842 0.2141
-3.500 -0.1796 0.00930 0.00295 -0.0450 0.6826 0.3890
-3.250 -0.1488 0.00850 0.00285 -0.0465 0.6811 0.5568
-3.000 -0.1188 0.00865 0.00305 -0.0468 0.6795 0.5989
-2.750 -0.0890 0.00874 0.00312 -0.0471 0.6779 0.6095
-2.500 -0.0588 0.00877 0.00308 -0.0476 0.6762 0.6156
-2.250 -0.0290 0.00882 0.00309 -0.0479 0.6745 0.6202
-2.000 0.0007 0.00888 0.00310 -0.0483 0.6727 0.6242
-1.750 0.0307 0.00890 0.00308 -0.0487 0.6706 0.6276
-1.500 0.0609 0.00890 0.00305 -0.0492 0.6680 0.6309
-1.250 0.0908 0.00889 0.00302 -0.0496 0.6652 0.6336
-1.000 0.1205 0.00889 0.00301 -0.0500 0.6622 0.6357
-0.750 0.1502 0.00889 0.00299 -0.0503 0.6594 0.6380
-0.500 0.1799 0.00892 0.00298 -0.0507 0.6567 0.6407
-0.250 0.2098 0.00892 0.00298 -0.0511 0.6534 0.6434
0.000 0.2397 0.00890 0.00295 -0.0516 0.6494 0.6455
0.250 0.2697 0.00888 0.00291 -0.0520 0.6456 0.6473
0.500 0.2995 0.00886 0.00286 -0.0525 0.6420 0.6488
0.750 0.3292 0.00883 0.00285 -0.0528 0.6380 0.6500
1.000 0.3588 0.00880 0.00286 -0.0532 0.6326 0.6514
1.250 0.3884 0.00877 0.00283 -0.0536 0.6271 0.6528
1.500 0.4180 0.00875 0.00283 -0.0539 0.6208 0.6541
1.750 0.4476 0.00872 0.00281 -0.0543 0.6131 0.6555
2.000 0.4772 0.00870 0.00281 -0.0546 0.6048 0.6570
2.250 0.5065 0.00869 0.00278 -0.0550 0.5946 0.6586
2.500 0.5359 0.00870 0.00278 -0.0553 0.5812 0.6602
2.750 0.5648 0.00874 0.00277 -0.0555 0.5642 0.6616
3.000 0.5934 0.00882 0.00279 -0.0557 0.5402 0.6629
3.250 0.6210 0.00902 0.00285 -0.0558 0.5077 0.6641
3.500 0.6477 0.00930 0.00298 -0.0557 0.4704 0.6654
3.750 0.6739 0.00966 0.00318 -0.0557 0.4300 0.6667
4.000 0.6999 0.01006 0.00343 -0.0556 0.3917 0.6680
4.250 0.7263 0.01041 0.00367 -0.0556 0.3602 0.6692
4.500 0.7528 0.01075 0.00391 -0.0556 0.3316 0.6705
4.750 0.7790 0.01111 0.00417 -0.0556 0.3031 0.6718
5.000 0.8053 0.01145 0.00443 -0.0555 0.2791 0.6734
5.250 0.8312 0.01183 0.00471 -0.0555 0.2537 0.6750
5.500 0.8565 0.01226 0.00502 -0.0554 0.2254 0.6764
5.750 0.8820 0.01267 0.00533 -0.0553 0.2026 0.6778
6.000 0.9078 0.01303 0.00563 -0.0552 0.1853 0.6791
6.500 0.9584 0.01377 0.00628 -0.0549 0.1537 0.6816
6.750 0.9835 0.01414 0.00663 -0.0547 0.1408 0.6830
7.000 1.0081 0.01454 0.00700 -0.0545 0.1280 0.6845
7.250 1.0325 0.01496 0.00739 -0.0542 0.1163 0.6859
7.500 1.0568 0.01537 0.00778 -0.0539 0.1056 0.6874
7.750 1.0808 0.01578 0.00819 -0.0536 0.0960 0.6888
8.000 1.1043 0.01623 0.00863 -0.0532 0.0874 0.6903
8.500 1.1503 0.01717 0.00955 -0.0523 0.0726 0.6933
8.750 1.1723 0.01769 0.01007 -0.0518 0.0666 0.6948
9.000 1.1945 0.01817 0.01058 -0.0512 0.0612 0.6964
9.250 1.2152 0.01872 0.01115 -0.0505 0.0562 0.6981
9.500 1.2361 0.01923 0.01170 -0.0498 0.0523 0.6998
9.750 1.2553 0.01984 0.01234 -0.0489 0.0484 0.7014
10.000 1.2746 0.02041 0.01297 -0.0480 0.0457 0.7031
10.250 1.2925 0.02104 0.01364 -0.0470 0.0428 0.7049
10.500 1.3062 0.02177 0.01439 -0.0453 0.0403 0.7067
10.750 1.3197 0.02248 0.01517 -0.0437 0.0386 0.7086
11.000 1.3345 0.02326 0.01603 -0.0424 0.0370 0.7104
11.500 1.3602 0.02529 0.01817 -0.0403 0.0334 0.7140
11.750 1.3725 0.02647 0.01944 -0.0396 0.0321 0.7160
12.000 1.3859 0.02763 0.02070 -0.0391 0.0309 0.7181
12.250 1.3984 0.02890 0.02206 -0.0386 0.0295 0.7204
12.500 1.4095 0.03031 0.02353 -0.0381 0.0281 0.7229
12.750 1.4183 0.03194 0.02520 -0.0375 0.0267 0.7255
13.250 1.4399 0.03480 0.02827 -0.0365 0.0245 0.7306
13.500 1.4484 0.03644 0.02999 -0.0360 0.0234 0.7333
13.750 1.4551 0.03826 0.03187 -0.0354 0.0225 0.7362
14.000 1.4603 0.04023 0.03392 -0.0348 0.0217 0.7392
14.250 1.4669 0.04208 0.03589 -0.0343 0.0210 0.7423
14.500 1.4724 0.04404 0.03797 -0.0339 0.0202 0.7456
14.750 1.4765 0.04617 0.04020 -0.0335 0.0195 0.7493
15.000 1.4791 0.04850 0.04263 -0.0331 0.0188 0.7534
15.250 1.4799 0.05103 0.04526 -0.0328 0.0183 0.7578
15.500 1.4783 0.05390 0.04823 -0.0327 0.0177 0.7624
15.750 1.4794 0.05660 0.05107 -0.0327 0.0173 0.7682
16.000 1.4797 0.05951 0.05412 -0.0329 0.0168 0.7748
16.250 1.4791 0.06265 0.05741 -0.0333 0.0163 0.7828
16.500 1.4773 0.06605 0.06096 -0.0338 0.0158 0.7932
17.000 1.4692 0.07374 0.06899 -0.0356 0.0150 0.8328
17.250 1.4566 0.07740 0.07297 -0.0351 0.0147 1.0000
17.500 1.4473 0.08237 0.07805 -0.0367 0.0143 1.0000
17.750 1.4385 0.08738 0.08318 -0.0385 0.0140 1.0000
18.000 1.4290 0.09254 0.08847 -0.0404 0.0138 1.0000
18.250 1.4182 0.09802 0.09409 -0.0425 0.0135 1.0000
18.500 1.4062 0.10384 0.10004 -0.0450 0.0132 1.0000
18.750 1.3929 0.10994 0.10627 -0.0476 0.0130 1.0000
19.000 1.3782 0.11637 0.11282 -0.0506 0.0127 1.0000
19.250 1.3631 0.12301 0.11959 -0.0538 0.0125 1.0000
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Polar data table (+)
Polar graphs
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