AS5045 (15%) (as5045-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: AS5045 (15%) (as5045-il) Reynolds number: 500,000 Max Cl/Cd: 79.37 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-as5045-il-500000.txt Download as CSV file: xf-as5045-il-500000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.750 -0.5148 0.07714 0.07421 -0.0429 0.7762 0.0226
-11.500 -0.5576 0.06720 0.06413 -0.0477 0.7755 0.0221
-11.250 -0.7494 0.06820 0.06433 -0.0470 0.7804 0.0204
-11.000 -0.7537 0.06078 0.05694 -0.0477 0.7782 0.0209
-10.750 -0.7568 0.05764 0.05372 -0.0480 0.7754 0.0211
-10.500 -0.7609 0.05476 0.05074 -0.0481 0.7727 0.0212
-10.250 -0.7631 0.05224 0.04809 -0.0478 0.7702 0.0214
-10.000 -0.7591 0.04979 0.04551 -0.0476 0.7679 0.0217
-9.750 -0.7533 0.04734 0.04292 -0.0474 0.7657 0.0221
-9.500 -0.7455 0.04488 0.04028 -0.0471 0.7635 0.0227
-8.250 -0.6753 0.02780 0.02102 -0.0424 0.7541 0.0166
-8.000 -0.6501 0.02489 0.01811 -0.0421 0.7524 0.0159
-7.750 -0.6256 0.02323 0.01631 -0.0416 0.7506 0.0156
-7.500 -0.6007 0.02185 0.01484 -0.0412 0.7490 0.0155
-7.250 -0.5760 0.02068 0.01359 -0.0408 0.7473 0.0154
-7.000 -0.5511 0.01981 0.01266 -0.0405 0.7457 0.0157
-6.750 -0.5260 0.01908 0.01186 -0.0403 0.7440 0.0161
-6.500 -0.5010 0.01834 0.01107 -0.0401 0.7424 0.0163
-6.250 -0.4766 0.01753 0.01022 -0.0399 0.7407 0.0164
-6.000 -0.4517 0.01683 0.00947 -0.0398 0.7390 0.0165
-5.750 -0.4284 0.01577 0.00839 -0.0398 0.7373 0.0169
-5.500 -0.4028 0.01507 0.00766 -0.0401 0.7356 0.0175
-5.250 -0.3757 0.01453 0.00711 -0.0405 0.7343 0.0184
-5.000 -0.3479 0.01406 0.00662 -0.0409 0.7329 0.0196
-4.750 -0.3198 0.01359 0.00611 -0.0414 0.7312 0.0209
-4.500 -0.2914 0.01316 0.00567 -0.0419 0.7293 0.0236
-4.250 -0.2626 0.01273 0.00524 -0.0424 0.7275 0.0319
-4.000 -0.2343 0.00915 0.00371 -0.0467 0.7259 0.4867
-3.750 -0.2044 0.00908 0.00394 -0.0472 0.7242 0.5807
-3.500 -0.1745 0.00928 0.00409 -0.0474 0.7225 0.6039
-3.250 -0.1453 0.00970 0.00450 -0.0474 0.7207 0.6234
-3.000 -0.1169 0.01029 0.00511 -0.0470 0.7190 0.6395
-2.750 -0.0869 0.01051 0.00527 -0.0473 0.7171 0.6476
-2.500 -0.0577 0.01055 0.00532 -0.0475 0.7149 0.6511
-2.250 -0.0286 0.01065 0.00542 -0.0476 0.7124 0.6547
-2.000 0.0008 0.01074 0.00548 -0.0478 0.7100 0.6588
-1.750 0.0309 0.01079 0.00545 -0.0483 0.7076 0.6626
-1.500 0.0607 0.01081 0.00539 -0.0488 0.7053 0.6653
-1.250 0.0897 0.01085 0.00544 -0.0490 0.7027 0.6674
-1.000 0.1190 0.01085 0.00545 -0.0492 0.6997 0.6698
-0.750 0.1485 0.01084 0.00545 -0.0496 0.6965 0.6722
-0.500 0.1782 0.01083 0.00540 -0.0500 0.6933 0.6748
-0.250 0.2081 0.01083 0.00534 -0.0504 0.6902 0.6775
0.000 0.2382 0.01092 0.00536 -0.0509 0.6872 0.6802
0.250 0.2674 0.01078 0.00528 -0.0512 0.6835 0.6822
0.500 0.2967 0.01071 0.00523 -0.0515 0.6795 0.6838
0.750 0.3262 0.01066 0.00517 -0.0518 0.6759 0.6854
1.000 0.3557 0.01065 0.00512 -0.0521 0.6725 0.6872
1.250 0.3852 0.01058 0.00509 -0.0525 0.6679 0.6891
1.500 0.4149 0.01049 0.00500 -0.0529 0.6628 0.6908
1.750 0.4447 0.01040 0.00489 -0.0533 0.6584 0.6926
2.000 0.4746 0.01035 0.00483 -0.0537 0.6537 0.6945
2.250 0.5045 0.01026 0.00476 -0.0542 0.6477 0.6960
2.500 0.5339 0.01010 0.00461 -0.0545 0.6424 0.6974
2.750 0.5631 0.00998 0.00454 -0.0548 0.6363 0.6987
3.000 0.5924 0.00986 0.00446 -0.0550 0.6289 0.7002
3.250 0.6216 0.00976 0.00441 -0.0553 0.6211 0.7018
3.500 0.6508 0.00966 0.00433 -0.0555 0.6112 0.7034
3.750 0.6801 0.00957 0.00427 -0.0558 0.5976 0.7050
4.000 0.7089 0.00951 0.00420 -0.0560 0.5801 0.7065
4.250 0.7375 0.00953 0.00418 -0.0562 0.5572 0.7081
4.500 0.7651 0.00966 0.00419 -0.0562 0.5250 0.7098
4.750 0.7913 0.00997 0.00432 -0.0561 0.4834 0.7114
5.000 0.8168 0.01032 0.00451 -0.0559 0.4431 0.7129
5.250 0.8417 0.01074 0.00477 -0.0557 0.4014 0.7142
5.500 0.8660 0.01123 0.00509 -0.0554 0.3587 0.7156
5.750 0.8907 0.01168 0.00540 -0.0552 0.3224 0.7171
6.000 0.9155 0.01213 0.00573 -0.0550 0.2914 0.7187
6.250 0.9401 0.01259 0.00608 -0.0548 0.2619 0.7205
6.500 0.9645 0.01307 0.00644 -0.0545 0.2354 0.7224
6.750 0.9893 0.01350 0.00679 -0.0543 0.2121 0.7241
7.000 1.0133 0.01400 0.00718 -0.0541 0.1905 0.7257
7.250 1.0377 0.01445 0.00757 -0.0539 0.1721 0.7272
7.500 1.0616 0.01488 0.00795 -0.0536 0.1553 0.7287
7.750 1.0849 0.01534 0.00838 -0.0532 0.1398 0.7305
8.000 1.1078 0.01582 0.00883 -0.0527 0.1258 0.7324
8.250 1.1304 0.01633 0.00931 -0.0522 0.1132 0.7343
8.500 1.1523 0.01688 0.00983 -0.0516 0.1019 0.7362
8.750 1.1734 0.01748 0.01039 -0.0510 0.0916 0.7381
9.000 1.1952 0.01800 0.01092 -0.0504 0.0834 0.7400
9.250 1.2154 0.01863 0.01155 -0.0496 0.0759 0.7419
9.500 1.2344 0.01931 0.01221 -0.0487 0.0695 0.7437
9.750 1.2531 0.01993 0.01291 -0.0477 0.0646 0.7458
10.000 1.2706 0.02060 0.01360 -0.0466 0.0601 0.7480
10.250 1.2841 0.02149 0.01452 -0.0450 0.0561 0.7504
10.500 1.2979 0.02209 0.01521 -0.0433 0.0534 0.7530
10.750 1.3108 0.02295 0.01610 -0.0417 0.0506 0.7556
11.000 1.3170 0.02442 0.01759 -0.0399 0.0477 0.7580
11.250 1.3327 0.02526 0.01855 -0.0392 0.0460 0.7605
11.500 1.3463 0.02632 0.01972 -0.0385 0.0439 0.7631
11.750 1.3575 0.02767 0.02112 -0.0379 0.0421 0.7660
12.000 1.3621 0.02966 0.02316 -0.0370 0.0401 0.7691
12.250 1.3727 0.03114 0.02474 -0.0364 0.0387 0.7723
12.500 1.3855 0.03242 0.02612 -0.0360 0.0372 0.7756
12.750 1.3964 0.03384 0.02764 -0.0356 0.0356 0.7791
13.000 1.4038 0.03558 0.02945 -0.0350 0.0342 0.7831
13.250 1.4017 0.03821 0.03213 -0.0340 0.0328 0.7875
13.500 1.4117 0.03975 0.03381 -0.0336 0.0319 0.7923
13.750 1.4204 0.04140 0.03560 -0.0332 0.0308 0.7980
14.000 1.4270 0.04327 0.03757 -0.0327 0.0297 0.8045
14.250 1.4322 0.04527 0.03969 -0.0324 0.0288 0.8121
14.500 1.4338 0.04766 0.04217 -0.0320 0.0279 0.8220
14.750 1.4278 0.05078 0.04541 -0.0313 0.0270 0.8357
15.000 1.4287 0.05315 0.04803 -0.0308 0.0264 0.8653
15.250 1.4244 0.05511 0.05024 -0.0290 0.0259 1.0000
15.500 1.4268 0.05782 0.05305 -0.0293 0.0251 1.0000
15.750 1.4282 0.06075 0.05607 -0.0297 0.0244 1.0000
16.000 1.4287 0.06389 0.05929 -0.0302 0.0237 1.0000
16.250 1.4273 0.06736 0.06283 -0.0310 0.0231 1.0000
16.500 1.4215 0.07143 0.06697 -0.0319 0.0225 1.0000
16.750 1.4103 0.07620 0.07180 -0.0329 0.0218 1.0000
17.000 1.4087 0.08008 0.07584 -0.0342 0.0214 1.0000
17.250 1.4049 0.08433 0.08022 -0.0356 0.0209 1.0000
17.500 1.3997 0.08884 0.08485 -0.0373 0.0204 1.0000
17.750 1.3934 0.09356 0.08968 -0.0391 0.0198 1.0000
18.000 1.3859 0.09856 0.09478 -0.0411 0.0194 1.0000
18.250 1.3776 0.10377 0.10010 -0.0434 0.0190 1.0000
18.500 1.3680 0.10924 0.10565 -0.0458 0.0186 1.0000
18.750 1.3567 0.11492 0.11140 -0.0484 0.0181 1.0000
19.000 1.3442 0.12073 0.11728 -0.0509 0.0177 1.0000
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Polar data table (+)
Polar graphs
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