NREL's S817 Airfoil (s817-nr) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: NREL's S817 Airfoil (s817-nr) Reynolds number: 1,000,000 Max Cl/Cd: 137.26 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s817-nr-1000000.txt Download as CSV file: xf-s817-nr-1000000.csv |
XFOIL Version 6.96
Calculated polar for: NREL's S817 Airfoil
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.500 -0.1507 0.09332 0.09059 -0.0882 0.7384 0.0064
-11.250 -0.1495 0.08916 0.08643 -0.0900 0.7376 0.0064
-6.000 -0.2328 0.01747 0.01185 -0.0812 0.7185 0.0051
-5.750 -0.2061 0.01583 0.00996 -0.0810 0.7176 0.0057
-5.500 -0.1792 0.01478 0.00874 -0.0809 0.7167 0.0061
-5.250 -0.1530 0.01425 0.00810 -0.0808 0.7158 0.0063
-5.000 -0.1289 0.01319 0.00691 -0.0804 0.7148 0.0066
-4.750 -0.1075 0.01247 0.00613 -0.0795 0.7138 0.0069
-4.500 -0.0860 0.01194 0.00557 -0.0787 0.7132 0.0071
-4.250 -0.0624 0.01164 0.00526 -0.0783 0.7126 0.0077
-4.000 -0.0379 0.01141 0.00502 -0.0781 0.7119 0.0085
-3.750 -0.0141 0.01113 0.00471 -0.0776 0.7111 0.0092
-3.500 0.0054 0.01052 0.00406 -0.0764 0.7102 0.0107
-3.250 0.0289 0.01020 0.00373 -0.0759 0.7093 0.0150
-3.000 0.0547 0.01003 0.00355 -0.0759 0.7084 0.0178
-2.750 0.0798 0.00980 0.00333 -0.0758 0.7075 0.0231
-2.500 0.1051 0.00957 0.00314 -0.0757 0.7067 0.0368
-2.250 0.1303 0.00932 0.00301 -0.0756 0.7060 0.0742
-2.000 0.1509 0.00865 0.00280 -0.0750 0.7052 0.2298
-1.750 0.1614 0.00685 0.00239 -0.0732 0.7043 0.6709
-1.500 0.1901 0.00692 0.00246 -0.0736 0.7036 0.6915
-1.250 0.2190 0.00703 0.00255 -0.0740 0.7028 0.7049
-1.000 0.2478 0.00718 0.00269 -0.0744 0.7020 0.7170
-0.750 0.2768 0.00733 0.00282 -0.0749 0.7011 0.7240
-0.500 0.3060 0.00747 0.00290 -0.0755 0.7002 0.7269
-0.250 0.3347 0.00756 0.00300 -0.0760 0.6994 0.7312
0.000 0.3635 0.00762 0.00308 -0.0765 0.6989 0.7344
0.250 0.3924 0.00768 0.00314 -0.0771 0.6983 0.7374
0.500 0.4213 0.00769 0.00314 -0.0777 0.6976 0.7382
0.750 0.4503 0.00771 0.00316 -0.0783 0.6968 0.7390
1.000 0.4793 0.00774 0.00319 -0.0790 0.6960 0.7398
1.250 0.5082 0.00777 0.00322 -0.0796 0.6953 0.7405
1.500 0.5372 0.00781 0.00327 -0.0803 0.6945 0.7412
1.750 0.5661 0.00785 0.00332 -0.0809 0.6936 0.7419
2.000 0.5949 0.00786 0.00334 -0.0815 0.6927 0.7430
2.250 0.6237 0.00788 0.00339 -0.0822 0.6918 0.7440
2.500 0.6526 0.00791 0.00345 -0.0828 0.6910 0.7451
2.750 0.6815 0.00796 0.00353 -0.0834 0.6902 0.7461
3.000 0.7104 0.00801 0.00360 -0.0841 0.6893 0.7473
3.250 0.7395 0.00804 0.00366 -0.0847 0.6882 0.7484
3.500 0.7690 0.00811 0.00372 -0.0854 0.6856 0.7496
3.750 0.7956 0.00792 0.00360 -0.0854 0.6809 0.7508
4.000 0.8239 0.00766 0.00332 -0.0857 0.6742 0.7520
4.250 0.8498 0.00745 0.00313 -0.0855 0.6653 0.7532
4.500 0.8765 0.00730 0.00295 -0.0855 0.6564 0.7545
4.750 0.9026 0.00722 0.00296 -0.0855 0.6498 0.7556
5.000 0.9293 0.00721 0.00295 -0.0856 0.6436 0.7567
5.250 0.9553 0.00715 0.00298 -0.0856 0.6342 0.7583
5.500 0.9800 0.00714 0.00300 -0.0852 0.6193 0.7599
5.750 0.9988 0.00728 0.00306 -0.0837 0.5814 0.7614
6.000 0.9930 0.00822 0.00357 -0.0774 0.4918 0.7634
6.250 0.9762 0.00925 0.00424 -0.0691 0.4176 0.7658
6.500 0.9607 0.01033 0.00505 -0.0613 0.3557 0.7683
6.750 0.9478 0.01155 0.00598 -0.0545 0.2969 0.7706
7.000 0.9373 0.01284 0.00704 -0.0487 0.2426 0.7733
7.250 0.9315 0.01415 0.00816 -0.0440 0.1944 0.7759
7.500 0.9303 0.01542 0.00926 -0.0403 0.1535 0.7784
7.750 0.9322 0.01665 0.01032 -0.0373 0.1192 0.7808
8.000 0.9395 0.01766 0.01123 -0.0350 0.0951 0.7832
8.250 0.9496 0.01858 0.01207 -0.0332 0.0777 0.7854
8.500 0.9611 0.01942 0.01288 -0.0317 0.0648 0.7878
8.750 0.9728 0.02025 0.01369 -0.0301 0.0542 0.7905
9.000 0.9848 0.02109 0.01452 -0.0287 0.0454 0.7931
9.250 0.9994 0.02182 0.01528 -0.0276 0.0414 0.7958
9.500 1.0113 0.02271 0.01612 -0.0262 0.0338 0.7986
9.750 1.0276 0.02336 0.01680 -0.0255 0.0316 0.8012
10.000 1.0415 0.02412 0.01758 -0.0244 0.0284 0.8044
10.250 1.0546 0.02498 0.01849 -0.0232 0.0262 0.8076
10.500 1.0698 0.02573 0.01929 -0.0224 0.0243 0.8111
10.750 1.0854 0.02646 0.02006 -0.0216 0.0226 0.8146
11.000 1.0996 0.02727 0.02091 -0.0207 0.0210 0.8185
11.250 1.1114 0.02826 0.02193 -0.0195 0.0184 0.8227
11.500 1.1275 0.02898 0.02271 -0.0189 0.0176 0.8272
11.750 1.1428 0.02976 0.02353 -0.0182 0.0160 0.8317
12.000 1.1565 0.03063 0.02444 -0.0174 0.0144 0.8368
12.250 1.1684 0.03169 0.02556 -0.0164 0.0132 0.8426
12.500 1.1843 0.03243 0.02635 -0.0159 0.0117 0.8488
12.750 1.1975 0.03338 0.02734 -0.0151 0.0103 0.8564
13.000 1.2100 0.03437 0.02837 -0.0143 0.0076 0.8652
13.250 1.2215 0.03544 0.02951 -0.0133 0.0065 0.8764
13.500 1.2269 0.03693 0.03105 -0.0118 0.0026 0.8924
13.750 1.2326 0.03815 0.03247 -0.0099 0.0018 0.9355
14.000 1.2471 0.03974 0.03421 -0.0104 0.0013 1.0000
14.250 1.2570 0.04117 0.03571 -0.0097 0.0011 1.0000
14.500 1.2658 0.04275 0.03737 -0.0089 0.0010 1.0000
14.750 1.2683 0.04495 0.03972 -0.0077 0.0008 1.0000
15.000 1.2757 0.04676 0.04163 -0.0070 0.0007 1.0000
15.250 1.2833 0.04855 0.04351 -0.0064 0.0007 1.0000
15.500 1.2895 0.05051 0.04558 -0.0058 0.0007 1.0000
15.750 1.2947 0.05263 0.04780 -0.0053 0.0007 1.0000
16.000 1.2981 0.05499 0.05028 -0.0048 0.0007 1.0000
16.250 1.3018 0.05738 0.05277 -0.0044 0.0007 1.0000
16.500 1.3021 0.06020 0.05574 -0.0040 0.0007 1.0000
16.750 1.3006 0.06330 0.05897 -0.0037 0.0006 1.0000
17.000 1.3022 0.06612 0.06191 -0.0037 0.0007 1.0000
17.250 1.2968 0.06992 0.06586 -0.0038 0.0006 1.0000
17.500 1.2965 0.07318 0.06922 -0.0041 0.0007 1.0000
17.750 1.2911 0.07722 0.07341 -0.0046 0.0006 1.0000
18.000 1.2801 0.08222 0.07858 -0.0055 0.0006 1.0000
18.250 1.2723 0.08693 0.08343 -0.0067 0.0006 1.0000
18.500 1.2617 0.09228 0.08894 -0.0082 0.0006 1.0000
18.750 1.2480 0.09833 0.09515 -0.0103 0.0006 1.0000
19.000 1.2335 0.10479 0.10177 -0.0129 0.0006 1.0000
19.250 1.2159 0.11211 0.10927 -0.0162 0.0006 1.0000
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