AS5048 (18%) (as5048-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: AS5048 (18%) (as5048-il) Reynolds number: 500,000 Max Cl/Cd: 81.45 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-as5048-il-500000.txt Download as CSV file: xf-as5048-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: AS5048 (18%)
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
------ -------- --------- --------- -------- -------- --------
-12.250 -0.7720 0.04169 0.03671 -0.0834 0.8820 0.0156
-12.000 -0.7639 0.03879 0.03328 -0.0833 0.8270 0.0152
-11.750 -0.7594 0.03634 0.03051 -0.0817 0.8115 0.0150
-11.500 -0.7508 0.03431 0.02820 -0.0804 0.8024 0.0150
-11.250 -0.7379 0.03242 0.02607 -0.0793 0.7959 0.0151
-11.000 -0.7212 0.03071 0.02413 -0.0784 0.7906 0.0152
-10.750 -0.6998 0.02914 0.02235 -0.0778 0.7863 0.0153
-10.500 -0.6768 0.02781 0.02087 -0.0772 0.7829 0.0154
-10.250 -0.6544 0.02671 0.01964 -0.0766 0.7795 0.0156
-10.000 -0.6331 0.02579 0.01859 -0.0760 0.7762 0.0159
-9.750 -0.6131 0.02501 0.01768 -0.0754 0.7730 0.0162
-9.500 -0.5893 0.02398 0.01662 -0.0744 0.7701 0.0166
-9.250 -0.5706 0.02313 0.01578 -0.0736 0.7674 0.0171
-9.000 -0.5526 0.02234 0.01498 -0.0728 0.7650 0.0175
-8.750 -0.5350 0.02156 0.01418 -0.0721 0.7626 0.0181
-8.500 -0.5176 0.02078 0.01336 -0.0713 0.7602 0.0187
-8.250 -0.4990 0.02012 0.01263 -0.0707 0.7579 0.0194
-8.000 -0.4860 0.01909 0.01156 -0.0694 0.7558 0.0203
-7.750 -0.4706 0.01829 0.01076 -0.0685 0.7536 0.0212
-7.500 -0.4543 0.01764 0.01007 -0.0674 0.7514 0.0222
-7.250 -0.4402 0.01707 0.00946 -0.0657 0.7495 0.0231
-7.000 -0.4266 0.01652 0.00887 -0.0638 0.7474 0.0239
-6.750 -0.4114 0.01586 0.00820 -0.0623 0.7455 0.0253
-6.500 -0.3915 0.01543 0.00775 -0.0614 0.7437 0.0270
-6.250 -0.3714 0.01497 0.00727 -0.0605 0.7419 0.0292
-6.000 -0.3501 0.01457 0.00685 -0.0597 0.7401 0.0322
-5.750 -0.3286 0.01417 0.00643 -0.0590 0.7382 0.0369
-5.500 -0.3110 0.01348 0.00589 -0.0577 0.7363 0.0688
-5.250 -0.3128 0.01134 0.00485 -0.0543 0.7344 0.2977
-5.000 -0.3037 0.00977 0.00415 -0.0521 0.7330 0.4837
-4.750 -0.2796 0.00956 0.00426 -0.0515 0.7314 0.5719
-4.500 -0.2512 0.00974 0.00445 -0.0515 0.7296 0.6012
-4.250 -0.2222 0.00995 0.00464 -0.0517 0.7277 0.6155
-4.000 -0.1930 0.01022 0.00491 -0.0518 0.7259 0.6271
-3.750 -0.1636 0.01046 0.00505 -0.0521 0.7241 0.6367
-3.500 -0.1341 0.01069 0.00531 -0.0523 0.7223 0.6426
-3.250 -0.1045 0.01096 0.00552 -0.0526 0.7205 0.6498
-3.000 -0.0749 0.01117 0.00569 -0.0529 0.7187 0.6555
-2.750 -0.0457 0.01137 0.00590 -0.0531 0.7168 0.6592
-2.500 -0.0169 0.01143 0.00595 -0.0534 0.7151 0.6625
-2.250 0.0120 0.01147 0.00596 -0.0537 0.7129 0.6660
-2.000 0.0411 0.01150 0.00595 -0.0541 0.7107 0.6691
-1.750 0.0701 0.01147 0.00589 -0.0545 0.7085 0.6715
-1.500 0.0992 0.01146 0.00588 -0.0548 0.7062 0.6735
-1.250 0.1286 0.01149 0.00589 -0.0552 0.7039 0.6756
-1.000 0.1583 0.01159 0.00594 -0.0557 0.7014 0.6779
-0.750 0.1867 0.01161 0.00596 -0.0559 0.6983 0.6805
-0.500 0.2150 0.01156 0.00591 -0.0561 0.6948 0.6829
-0.250 0.2439 0.01152 0.00585 -0.0565 0.6913 0.6850
0.000 0.2735 0.01152 0.00579 -0.0570 0.6884 0.6869
0.250 0.3030 0.01144 0.00569 -0.0575 0.6857 0.6885
0.500 0.3324 0.01146 0.00569 -0.0580 0.6828 0.6899
0.750 0.3600 0.01138 0.00567 -0.0580 0.6794 0.6914
1.000 0.3882 0.01133 0.00564 -0.0582 0.6757 0.6930
1.250 0.4172 0.01127 0.00559 -0.0585 0.6721 0.6946
1.500 0.4469 0.01120 0.00548 -0.0590 0.6680 0.6962
1.750 0.4744 0.01111 0.00539 -0.0590 0.6623 0.6979
2.000 0.5023 0.01098 0.00527 -0.0590 0.6562 0.6998
2.250 0.5315 0.01090 0.00516 -0.0594 0.6518 0.7015
2.500 0.5604 0.01087 0.00512 -0.0597 0.6476 0.7029
2.750 0.5881 0.01080 0.00510 -0.0598 0.6423 0.7042
3.000 0.6159 0.01063 0.00496 -0.0599 0.6368 0.7057
3.250 0.6440 0.01054 0.00487 -0.0600 0.6315 0.7073
3.500 0.6708 0.01045 0.00487 -0.0599 0.6245 0.7088
3.750 0.6984 0.01037 0.00480 -0.0599 0.6179 0.7103
4.000 0.7254 0.01030 0.00479 -0.0598 0.6088 0.7118
4.250 0.7522 0.01024 0.00472 -0.0596 0.5988 0.7133
4.500 0.7787 0.01020 0.00470 -0.0594 0.5862 0.7149
4.750 0.8045 0.01019 0.00469 -0.0591 0.5700 0.7167
5.000 0.8290 0.01026 0.00470 -0.0585 0.5478 0.7185
5.250 0.8511 0.01045 0.00476 -0.0575 0.5175 0.7201
5.500 0.8712 0.01074 0.00490 -0.0561 0.4831 0.7214
5.750 0.8905 0.01105 0.00510 -0.0547 0.4502 0.7230
6.000 0.9093 0.01143 0.00536 -0.0531 0.4185 0.7245
6.250 0.9274 0.01186 0.00566 -0.0515 0.3883 0.7261
6.500 0.9464 0.01225 0.00597 -0.0501 0.3608 0.7278
6.750 0.9643 0.01269 0.00631 -0.0485 0.3350 0.7298
7.000 0.9817 0.01314 0.00666 -0.0469 0.3089 0.7318
7.250 0.9984 0.01361 0.00703 -0.0451 0.2846 0.7338
7.500 1.0151 0.01407 0.00740 -0.0434 0.2628 0.7355
7.750 1.0292 0.01453 0.00777 -0.0412 0.2443 0.7371
8.000 1.0429 0.01494 0.00814 -0.0389 0.2284 0.7389
8.250 1.0582 0.01540 0.00858 -0.0370 0.2143 0.7408
8.500 1.0742 0.01589 0.00906 -0.0353 0.2022 0.7428
8.750 1.0890 0.01646 0.00959 -0.0335 0.1912 0.7448
9.000 1.1059 0.01695 0.01010 -0.0321 0.1817 0.7470
9.250 1.1214 0.01752 0.01067 -0.0305 0.1728 0.7495
9.500 1.1364 0.01814 0.01128 -0.0290 0.1644 0.7519
9.750 1.1522 0.01875 0.01191 -0.0277 0.1570 0.7541
10.000 1.1658 0.01945 0.01262 -0.0262 0.1489 0.7564
10.250 1.1810 0.02011 0.01334 -0.0250 0.1416 0.7589
10.500 1.1936 0.02098 0.01421 -0.0236 0.1338 0.7615
10.750 1.2084 0.02178 0.01506 -0.0226 0.1265 0.7642
11.000 1.2197 0.02287 0.01614 -0.0215 0.1185 0.7671
11.250 1.2346 0.02378 0.01709 -0.0208 0.1112 0.7700
11.500 1.2454 0.02501 0.01832 -0.0198 0.1038 0.7730
11.750 1.2584 0.02609 0.01945 -0.0191 0.0969 0.7764
12.000 1.2684 0.02741 0.02080 -0.0182 0.0906 0.7802
12.250 1.2795 0.02868 0.02210 -0.0175 0.0848 0.7845
12.500 1.2879 0.03018 0.02362 -0.0166 0.0795 0.7889
12.750 1.2985 0.03147 0.02499 -0.0158 0.0749 0.7941
13.000 1.3032 0.03323 0.02678 -0.0147 0.0704 0.8001
13.250 1.3143 0.03452 0.02817 -0.0141 0.0671 0.8070
13.500 1.3221 0.03605 0.02978 -0.0133 0.0637 0.8164
13.750 1.3238 0.03805 0.03187 -0.0122 0.0604 0.8300
14.000 1.3304 0.03927 0.03334 -0.0107 0.0583 0.8658
14.250 1.3137 0.04002 0.03430 -0.0044 0.0571 1.0000
14.500 1.3204 0.04183 0.03613 -0.0039 0.0546 1.0000
14.750 1.3213 0.04416 0.03848 -0.0032 0.0522 1.0000
15.000 1.3268 0.04614 0.04052 -0.0028 0.0504 1.0000
15.250 1.3336 0.04805 0.04252 -0.0025 0.0486 1.0000
15.500 1.3382 0.05023 0.04474 -0.0023 0.0468 1.0000
15.750 1.3387 0.05285 0.04739 -0.0021 0.0452 1.0000
16.000 1.3347 0.05598 0.05058 -0.0018 0.0436 1.0000
16.250 1.3407 0.05820 0.05290 -0.0019 0.0425 1.0000
16.500 1.3444 0.06067 0.05546 -0.0020 0.0411 1.0000
16.750 1.3461 0.06345 0.05831 -0.0022 0.0398 1.0000
17.000 1.3443 0.06666 0.06157 -0.0026 0.0387 1.0000
17.250 1.3370 0.07055 0.06551 -0.0030 0.0375 1.0000
17.500 1.3351 0.07390 0.06896 -0.0035 0.0366 1.0000
17.750 1.3356 0.07706 0.07223 -0.0042 0.0357 1.0000
18.000 1.3341 0.08051 0.07578 -0.0050 0.0348 1.0000
18.250 1.3315 0.08413 0.07948 -0.0059 0.0340 1.0000
18.500 1.3272 0.08802 0.08346 -0.0070 0.0332 1.0000
18.750 1.3206 0.09228 0.08779 -0.0083 0.0325 1.0000
19.000 1.3117 0.09680 0.09236 -0.0096 0.0317 1.0000
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Polar data table (+)
Polar graphs
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