NREL's S804 Airfoil (s804-nr) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: NREL's S804 Airfoil (s804-nr) Reynolds number: 50,000 Max Cl/Cd: 22.22 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s804-nr-50000-n5.txt Download as CSV file: xf-s804-nr-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NREL's S804 Airfoil
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.2914 0.10307 0.09609 -0.0532 1.0000 0.0663
-10.250 -0.3137 0.09540 0.08851 -0.0565 1.0000 0.0654
-10.000 -0.3314 0.08931 0.08251 -0.0585 1.0000 0.0651
-9.750 -0.3557 0.08319 0.07648 -0.0606 1.0000 0.0647
-9.500 -0.3901 0.07731 0.07069 -0.0623 1.0000 0.0641
-9.250 -0.4310 0.07301 0.06649 -0.0621 1.0000 0.0635
-9.000 -0.4619 0.06644 0.05978 -0.0687 0.9864 0.0629
-8.750 -0.4690 0.05902 0.05195 -0.0790 0.9619 0.0632
-8.500 -0.4616 0.05347 0.04588 -0.0855 0.9424 0.0642
-8.250 -0.4462 0.04911 0.04100 -0.0900 0.9250 0.0661
-8.000 -0.4132 0.04673 0.03853 -0.0931 0.9128 0.0686
-7.750 -0.3867 0.04385 0.03529 -0.0958 0.8981 0.0710
-7.500 -0.3583 0.04100 0.03195 -0.0980 0.8837 0.0735
-7.250 -0.3236 0.03933 0.03029 -0.0999 0.8708 0.0771
-7.000 -0.2852 0.03722 0.02777 -0.1025 0.8597 0.0820
-6.750 -0.2532 0.03586 0.02646 -0.1032 0.8451 0.0858
-6.500 -0.2199 0.03447 0.02482 -0.1041 0.8312 0.0920
-6.250 -0.1856 0.03323 0.02357 -0.1053 0.8184 0.0990
-6.000 -0.1549 0.03207 0.02234 -0.1058 0.8041 0.1071
-5.750 -0.1297 0.03107 0.02129 -0.1058 0.7883 0.1176
-5.500 -0.1041 0.03000 0.02022 -0.1061 0.7736 0.1320
-5.250 -0.0759 0.02879 0.01901 -0.1071 0.7605 0.1553
-5.000 -0.0532 0.02764 0.01804 -0.1076 0.7457 0.1883
-4.750 -0.0289 0.02648 0.01721 -0.1085 0.7320 0.2435
-4.500 -0.0013 0.02592 0.01715 -0.1087 0.7204 0.3241
-4.250 0.0213 0.02637 0.01779 -0.1071 0.7062 0.3887
-4.000 0.0492 0.02689 0.01814 -0.1063 0.6944 0.4363
-3.750 0.0768 0.02736 0.01837 -0.1057 0.6825 0.4721
-3.500 0.1002 0.02799 0.01887 -0.1038 0.6710 0.4957
-3.250 0.1257 0.02844 0.01914 -0.1022 0.6607 0.5173
-3.000 0.1493 0.02880 0.01934 -0.1009 0.6499 0.5366
-2.750 0.1747 0.02908 0.01943 -0.0997 0.6405 0.5538
-2.500 0.1961 0.02942 0.01968 -0.0976 0.6309 0.5664
-2.250 0.2216 0.02952 0.01960 -0.0969 0.6218 0.5814
-2.000 0.2477 0.02963 0.01952 -0.0963 0.6138 0.5950
-1.750 0.2691 0.02980 0.01962 -0.0949 0.6047 0.6053
-1.500 0.2999 0.02973 0.01930 -0.0956 0.5977 0.6188
-1.250 0.3194 0.02995 0.01949 -0.0938 0.5894 0.6265
-1.000 0.3464 0.02997 0.01935 -0.0940 0.5817 0.6373
-0.750 0.3744 0.02994 0.01914 -0.0937 0.5761 0.6454
-0.500 0.3948 0.03019 0.01938 -0.0928 0.5681 0.6536
-0.250 0.4227 0.03026 0.01931 -0.0934 0.5617 0.6624
0.000 0.4497 0.03029 0.01920 -0.0930 0.5568 0.6692
0.250 0.4733 0.03059 0.01945 -0.0931 0.5499 0.6771
0.500 0.4981 0.03080 0.01960 -0.0930 0.5435 0.6841
0.750 0.5253 0.03089 0.01957 -0.0929 0.5386 0.6906
1.000 0.5541 0.03111 0.01967 -0.0936 0.5336 0.6983
1.250 0.5739 0.03160 0.02021 -0.0930 0.5273 0.7045
1.500 0.5981 0.03193 0.02050 -0.0927 0.5225 0.7113
1.750 0.6292 0.03215 0.02059 -0.0938 0.5185 0.7190
2.000 0.6551 0.03242 0.02080 -0.0936 0.5148 0.7253
2.250 0.6702 0.03325 0.02174 -0.0925 0.5088 0.7325
2.500 0.6946 0.03380 0.02228 -0.0928 0.5039 0.7406
2.750 0.7189 0.03410 0.02255 -0.0923 0.5001 0.7474
3.000 0.7498 0.03433 0.02268 -0.0930 0.4970 0.7559
3.250 0.7631 0.03539 0.02386 -0.0918 0.4925 0.7637
3.500 0.7748 0.03656 0.02515 -0.0905 0.4877 0.7725
3.750 0.7940 0.03736 0.02599 -0.0900 0.4836 0.7816
4.000 0.8179 0.03783 0.02645 -0.0897 0.4804 0.7913
4.250 0.8462 0.03809 0.02668 -0.0898 0.4777 0.8017
4.500 0.8480 0.03992 0.02867 -0.0878 0.4727 0.8131
4.750 0.8412 0.04209 0.03105 -0.0849 0.4675 0.8245
5.000 0.8487 0.04352 0.03257 -0.0833 0.4637 0.8380
5.250 0.8665 0.04427 0.03337 -0.0824 0.4608 0.8540
5.500 0.8929 0.04455 0.03366 -0.0822 0.4586 0.8742
6.000 0.8064 0.05509 0.04471 -0.0757 0.4427 1.0000
6.250 0.8396 0.05589 0.04546 -0.0775 0.4406 1.0000
6.500 0.8767 0.05622 0.04572 -0.0790 0.4389 1.0000
7.000 0.8161 0.07025 0.05992 -0.0816 0.4217 1.0000
7.250 0.8484 0.07070 0.06031 -0.0822 0.4200 1.0000
8.250 0.8197 0.08874 0.07849 -0.0863 0.3954 1.0000
8.750 0.8419 0.09375 0.08352 -0.0874 0.3865 1.0000
9.000 0.8688 0.09461 0.08438 -0.0875 0.3840 1.0000
9.250 0.8448 0.10083 0.09068 -0.0891 0.3756 1.0000
9.500 0.8559 0.10329 0.09318 -0.0896 0.3706 1.0000
9.750 0.8788 0.10448 0.09438 -0.0896 0.3674 1.0000
10.000 0.9067 0.10516 0.09506 -0.0895 0.3651 1.0000
10.250 0.8766 0.11204 0.10206 -0.0916 0.3546 1.0000
10.500 0.8968 0.11344 0.10349 -0.0916 0.3507 1.0000
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