AS5048 (18%) (as5048-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: AS5048 (18%) (as5048-il) Reynolds number: 500,000 Max Cl/Cd: 71.03 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-as5048-il-500000-n5.txt Download as CSV file: xf-as5048-il-500000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-17.250 -0.7776 0.11328 0.11022 -0.0381 1.0000 0.0069
-17.000 -0.8228 0.09972 0.09637 -0.0453 1.0000 0.0068
-16.750 -0.8502 0.09074 0.08718 -0.0498 1.0000 0.0068
-16.500 -0.8708 0.08349 0.07974 -0.0531 1.0000 0.0068
-16.250 -0.8873 0.07736 0.07342 -0.0555 1.0000 0.0068
-16.000 -0.9000 0.07217 0.06807 -0.0572 1.0000 0.0069
-15.750 -0.9098 0.06764 0.06338 -0.0585 1.0000 0.0069
-15.500 -0.9180 0.06356 0.05915 -0.0593 1.0000 0.0070
-15.250 -0.9234 0.06004 0.05550 -0.0597 1.0000 0.0071
-15.000 -0.9257 0.05654 0.05183 -0.0605 0.9996 0.0072
-14.750 -0.9203 0.05306 0.04819 -0.0624 0.9957 0.0073
-14.500 -0.9159 0.05009 0.04506 -0.0632 0.9389 0.0074
-14.250 -0.8671 0.04542 0.04001 -0.0755 0.9066 0.0077
-14.000 -0.8386 0.04275 0.03673 -0.0807 0.8109 0.0079
-13.500 -0.8256 0.03951 0.03307 -0.0792 0.7771 0.0080
-13.250 -0.8177 0.03798 0.03138 -0.0784 0.7687 0.0081
-13.000 -0.8093 0.03646 0.02976 -0.0776 0.7626 0.0082
-12.750 -0.7993 0.03511 0.02833 -0.0770 0.7571 0.0084
-12.250 -0.7760 0.03273 0.02579 -0.0758 0.7488 0.0086
-12.000 -0.7634 0.03160 0.02460 -0.0752 0.7451 0.0088
-11.750 -0.7501 0.03054 0.02346 -0.0746 0.7416 0.0089
-11.500 -0.7367 0.02950 0.02234 -0.0739 0.7383 0.0091
-11.000 -0.7087 0.02751 0.02020 -0.0725 0.7329 0.0095
-10.750 -0.6943 0.02652 0.01916 -0.0718 0.7306 0.0098
-10.500 -0.6798 0.02557 0.01813 -0.0711 0.7283 0.0100
-10.250 -0.6647 0.02466 0.01714 -0.0704 0.7261 0.0103
-10.000 -0.6489 0.02381 0.01622 -0.0697 0.7240 0.0105
-9.750 -0.6357 0.02277 0.01516 -0.0689 0.7220 0.0108
-9.500 -0.6202 0.02192 0.01426 -0.0682 0.7201 0.0110
-9.250 -0.6035 0.02116 0.01346 -0.0677 0.7183 0.0114
-9.000 -0.5862 0.02044 0.01270 -0.0671 0.7166 0.0118
-8.750 -0.5686 0.01973 0.01196 -0.0665 0.7148 0.0124
-8.500 -0.5508 0.01907 0.01124 -0.0659 0.7129 0.0129
-8.250 -0.5342 0.01836 0.01049 -0.0650 0.7111 0.0134
-8.000 -0.5188 0.01765 0.00976 -0.0639 0.7095 0.0139
-7.750 -0.5027 0.01711 0.00920 -0.0626 0.7078 0.0145
-7.500 -0.4876 0.01667 0.00872 -0.0609 0.7063 0.0150
-7.250 -0.4693 0.01625 0.00825 -0.0598 0.7048 0.0157
-7.000 -0.4494 0.01585 0.00780 -0.0589 0.7033 0.0164
-6.750 -0.4295 0.01543 0.00735 -0.0580 0.7018 0.0174
-6.500 -0.4076 0.01510 0.00699 -0.0573 0.7002 0.0187
-6.250 -0.3852 0.01477 0.00664 -0.0567 0.6988 0.0200
-6.000 -0.3629 0.01441 0.00629 -0.0561 0.6975 0.0217
-5.750 -0.3393 0.01412 0.00598 -0.0557 0.6961 0.0239
-5.500 -0.3160 0.01380 0.00567 -0.0552 0.6948 0.0285
-5.250 -0.2936 0.01340 0.00534 -0.0546 0.6933 0.0427
-5.000 -0.2786 0.01244 0.00477 -0.0532 0.6917 0.1271
-4.750 -0.2647 0.01130 0.00418 -0.0516 0.6901 0.2483
-4.500 -0.2498 0.01008 0.00356 -0.0503 0.6885 0.3877
-4.250 -0.2300 0.00923 0.00321 -0.0495 0.6872 0.5047
-4.000 -0.2033 0.00910 0.00328 -0.0494 0.6859 0.5653
-3.750 -0.1742 0.00915 0.00331 -0.0498 0.6844 0.5879
-3.500 -0.1447 0.00923 0.00336 -0.0502 0.6829 0.6007
-3.250 -0.1155 0.00929 0.00342 -0.0505 0.6816 0.6105
-3.000 -0.0861 0.00936 0.00343 -0.0509 0.6801 0.6198
-2.750 -0.0569 0.00941 0.00350 -0.0512 0.6783 0.6248
-2.500 -0.0274 0.00944 0.00350 -0.0516 0.6765 0.6286
-2.250 0.0021 0.00946 0.00348 -0.0520 0.6746 0.6321
-2.000 0.0316 0.00948 0.00343 -0.0525 0.6727 0.6352
-1.750 0.0611 0.00948 0.00341 -0.0529 0.6708 0.6376
-1.500 0.0905 0.00950 0.00341 -0.0533 0.6690 0.6399
-1.250 0.1200 0.00954 0.00343 -0.0537 0.6671 0.6425
-1.000 0.1494 0.00957 0.00344 -0.0542 0.6649 0.6448
-0.750 0.1783 0.00955 0.00343 -0.0545 0.6618 0.6469
-0.500 0.2071 0.00952 0.00338 -0.0548 0.6580 0.6487
-0.250 0.2361 0.00950 0.00333 -0.0551 0.6544 0.6504
0.000 0.2654 0.00949 0.00328 -0.0555 0.6515 0.6521
0.250 0.2947 0.00950 0.00326 -0.0559 0.6488 0.6536
0.500 0.3234 0.00947 0.00327 -0.0562 0.6455 0.6548
0.750 0.3521 0.00944 0.00328 -0.0565 0.6417 0.6561
1.000 0.3809 0.00943 0.00327 -0.0568 0.6378 0.6576
1.250 0.4096 0.00942 0.00326 -0.0570 0.6341 0.6590
1.500 0.4381 0.00941 0.00326 -0.0573 0.6290 0.6603
1.750 0.4660 0.00936 0.00323 -0.0573 0.6204 0.6617
2.000 0.4938 0.00933 0.00320 -0.0574 0.6115 0.6632
2.250 0.5218 0.00933 0.00319 -0.0575 0.6029 0.6649
2.500 0.5500 0.00934 0.00320 -0.0577 0.5946 0.6664
2.750 0.5776 0.00935 0.00320 -0.0577 0.5852 0.6678
3.000 0.6051 0.00938 0.00321 -0.0578 0.5721 0.6690
3.250 0.6314 0.00945 0.00322 -0.0576 0.5549 0.6702
3.500 0.6567 0.00954 0.00326 -0.0571 0.5351 0.6715
3.750 0.6812 0.00969 0.00335 -0.0566 0.5120 0.6729
4.000 0.7042 0.00993 0.00349 -0.0558 0.4853 0.6743
4.250 0.7264 0.01024 0.00368 -0.0548 0.4557 0.6756
4.500 0.7487 0.01054 0.00389 -0.0540 0.4279 0.6769
4.750 0.7709 0.01087 0.00412 -0.0531 0.4030 0.6783
5.000 0.7927 0.01120 0.00437 -0.0521 0.3771 0.6797
5.250 0.8137 0.01157 0.00463 -0.0511 0.3518 0.6811
5.500 0.8344 0.01196 0.00491 -0.0500 0.3260 0.6827
5.750 0.8549 0.01235 0.00520 -0.0489 0.3026 0.6844
6.000 0.8759 0.01270 0.00548 -0.0479 0.2824 0.6859
6.250 0.8962 0.01308 0.00578 -0.0467 0.2624 0.6871
6.500 0.9160 0.01343 0.00609 -0.0455 0.2448 0.6884
6.750 0.9356 0.01379 0.00641 -0.0443 0.2292 0.6898
7.000 0.9543 0.01417 0.00675 -0.0429 0.2138 0.6912
7.250 0.9708 0.01455 0.00709 -0.0410 0.1998 0.6926
7.500 0.9866 0.01494 0.00745 -0.0391 0.1882 0.6941
7.750 1.0034 0.01535 0.00784 -0.0374 0.1779 0.6956
8.000 1.0221 0.01574 0.00824 -0.0361 0.1694 0.6973
8.250 1.0393 0.01622 0.00870 -0.0347 0.1609 0.6991
8.500 1.0580 0.01664 0.00914 -0.0335 0.1535 0.7010
8.750 1.0744 0.01718 0.00965 -0.0320 0.1459 0.7027
9.250 1.1074 0.01824 0.01074 -0.0292 0.1317 0.7057
9.500 1.1246 0.01875 0.01131 -0.0281 0.1255 0.7073
9.750 1.1391 0.01944 0.01199 -0.0266 0.1185 0.7090
10.000 1.1549 0.02008 0.01268 -0.0255 0.1119 0.7108
10.250 1.1681 0.02092 0.01351 -0.0241 0.1046 0.7127
10.500 1.1829 0.02171 0.01434 -0.0231 0.0981 0.7146
10.750 1.1955 0.02270 0.01533 -0.0220 0.0917 0.7166
11.000 1.2094 0.02366 0.01631 -0.0212 0.0857 0.7185
11.250 1.2214 0.02480 0.01745 -0.0202 0.0802 0.7204
11.500 1.2350 0.02584 0.01854 -0.0195 0.0755 0.7225
11.750 1.2462 0.02707 0.01980 -0.0187 0.0707 0.7247
12.000 1.2591 0.02819 0.02098 -0.0180 0.0669 0.7272
12.250 1.2704 0.02944 0.02227 -0.0173 0.0628 0.7298
12.500 1.2808 0.03077 0.02364 -0.0165 0.0593 0.7323
12.750 1.2921 0.03203 0.02495 -0.0158 0.0561 0.7348
13.000 1.3012 0.03347 0.02641 -0.0150 0.0529 0.7373
13.250 1.3107 0.03488 0.02789 -0.0143 0.0504 0.7399
13.500 1.3203 0.03630 0.02938 -0.0136 0.0480 0.7429
13.750 1.3283 0.03784 0.03098 -0.0129 0.0457 0.7462
14.000 1.3347 0.03954 0.03274 -0.0121 0.0437 0.7497
14.250 1.3433 0.04108 0.03436 -0.0115 0.0420 0.7534
14.500 1.3504 0.04278 0.03615 -0.0109 0.0402 0.7574
14.750 1.3561 0.04462 0.03807 -0.0103 0.0386 0.7624
15.000 1.3601 0.04667 0.04019 -0.0098 0.0371 0.7681
15.250 1.3669 0.04853 0.04217 -0.0094 0.0360 0.7752
15.500 1.3729 0.05051 0.04428 -0.0092 0.0347 0.7850
15.750 1.3772 0.05271 0.04661 -0.0089 0.0336 0.7986
16.000 1.3801 0.05500 0.04907 -0.0087 0.0325 0.8238
16.500 1.3610 0.05884 0.05331 -0.0027 0.0310 1.0000
16.750 1.3644 0.06138 0.05595 -0.0029 0.0302 1.0000
17.000 1.3666 0.06410 0.05875 -0.0031 0.0292 1.0000
17.250 1.3667 0.06710 0.06183 -0.0035 0.0283 1.0000
17.500 1.3653 0.07035 0.06515 -0.0040 0.0275 1.0000
17.750 1.3621 0.07390 0.06878 -0.0047 0.0268 1.0000
18.000 1.3576 0.07770 0.07267 -0.0055 0.0262 1.0000
18.250 1.3555 0.08125 0.07633 -0.0063 0.0256 1.0000
18.500 1.3517 0.08506 0.08025 -0.0074 0.0251 1.0000
18.750 1.3465 0.08910 0.08440 -0.0085 0.0245 1.0000
19.000 1.3401 0.09340 0.08880 -0.0099 0.0240 1.0000
19.250 1.3325 0.09794 0.09344 -0.0115 0.0235 1.0000
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Polar data table (+)
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