NREL's S817 Airfoil (s817-nr) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: NREL's S817 Airfoil (s817-nr) Reynolds number: 500,000 Max Cl/Cd: 105.3 at α=6.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s817-nr-500000.txt Download as CSV file: xf-s817-nr-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.1948 0.08709 0.08369 -0.1036 0.7770 0.0119
-10.250 -0.1967 0.08271 0.07932 -0.1062 0.7754 0.0121
-10.000 -0.2013 0.07805 0.07467 -0.1093 0.7737 0.0121
-9.750 -0.2117 0.07310 0.06968 -0.1127 0.7720 0.0122
-9.500 -0.2219 0.06931 0.06588 -0.1142 0.7704 0.0120
-9.250 -0.2346 0.06578 0.06232 -0.1147 0.7685 0.0120
-9.000 -0.2492 0.06254 0.05903 -0.1141 0.7667 0.0122
-8.750 -0.2615 0.05994 0.05637 -0.1123 0.7649 0.0121
-8.500 -0.2751 0.05754 0.05388 -0.1091 0.7632 0.0124
-8.250 -0.2776 0.05471 0.05087 -0.1065 0.7617 0.0128
-8.000 -0.2764 0.05218 0.04817 -0.1042 0.7603 0.0129
-7.750 -0.2737 0.04960 0.04541 -0.1020 0.7591 0.0130
-7.500 -0.2705 0.04679 0.04240 -0.0996 0.7578 0.0130
-7.250 -0.2788 0.04215 0.03762 -0.0970 0.7566 0.0135
-7.000 -0.2698 0.04005 0.03543 -0.0957 0.7555 0.0137
-6.750 -0.2585 0.03815 0.03342 -0.0945 0.7543 0.0142
-6.500 -0.2452 0.03614 0.03128 -0.0931 0.7529 0.0148
-6.250 -0.2301 0.03397 0.02892 -0.0915 0.7516 0.0155
-6.000 -0.2061 0.03284 0.02739 -0.0891 0.7504 0.0179
-5.750 -0.1975 0.02826 0.02251 -0.0870 0.7492 0.0187
-5.500 -0.1777 0.02671 0.02089 -0.0865 0.7482 0.0195
-5.250 -0.1562 0.02534 0.01938 -0.0859 0.7472 0.0211
-5.000 -0.1312 0.02181 0.01539 -0.0841 0.7463 0.0194
-4.750 -0.0952 0.01776 0.01084 -0.0839 0.7456 0.0139
-4.500 -0.0663 0.01659 0.00955 -0.0841 0.7448 0.0141
-4.250 -0.0398 0.01553 0.00839 -0.0838 0.7439 0.0140
-4.000 -0.0177 0.01486 0.00768 -0.0829 0.7429 0.0145
-3.750 0.0024 0.01431 0.00712 -0.0818 0.7419 0.0159
-3.500 0.0233 0.01390 0.00668 -0.0807 0.7409 0.0180
-3.250 0.0419 0.01341 0.00621 -0.0795 0.7398 0.0235
-3.000 0.0621 0.01302 0.00582 -0.0785 0.7388 0.0288
-2.750 0.0843 0.01273 0.00553 -0.0778 0.7378 0.0368
-2.500 0.1059 0.01237 0.00526 -0.0770 0.7368 0.0647
-2.250 0.1155 0.01104 0.00484 -0.0749 0.7356 0.3360
-2.000 0.1254 0.00990 0.00484 -0.0723 0.7344 0.6902
-1.750 0.1526 0.01020 0.00511 -0.0722 0.7333 0.7158
-1.500 0.1795 0.01065 0.00559 -0.0717 0.7324 0.7358
-1.250 0.2068 0.01100 0.00594 -0.0715 0.7316 0.7472
-1.000 0.2346 0.01127 0.00615 -0.0716 0.7309 0.7549
-0.750 0.2624 0.01143 0.00630 -0.0718 0.7301 0.7595
-0.500 0.2900 0.01169 0.00655 -0.0718 0.7294 0.7644
-0.250 0.3180 0.01192 0.00673 -0.0722 0.7285 0.7690
0.000 0.3455 0.01201 0.00680 -0.0726 0.7275 0.7714
0.250 0.3725 0.01203 0.00681 -0.0730 0.7264 0.7722
0.500 0.3995 0.01208 0.00687 -0.0734 0.7254 0.7729
0.750 0.4266 0.01214 0.00695 -0.0738 0.7243 0.7736
1.000 0.4539 0.01222 0.00703 -0.0742 0.7232 0.7743
1.250 0.4813 0.01229 0.00711 -0.0746 0.7219 0.7751
1.500 0.5089 0.01236 0.00719 -0.0750 0.7207 0.7760
1.750 0.5364 0.01245 0.00730 -0.0755 0.7197 0.7769
2.000 0.5642 0.01254 0.00741 -0.0760 0.7187 0.7779
2.250 0.5923 0.01262 0.00750 -0.0765 0.7177 0.7790
2.500 0.6207 0.01270 0.00759 -0.0771 0.7167 0.7801
2.750 0.6490 0.01280 0.00770 -0.0778 0.7158 0.7813
3.000 0.6773 0.01293 0.00787 -0.0784 0.7150 0.7826
3.250 0.7056 0.01313 0.00808 -0.0790 0.7140 0.7840
3.500 0.7293 0.01334 0.00836 -0.0789 0.7122 0.7855
3.750 0.7530 0.01353 0.00863 -0.0787 0.7101 0.7867
4.000 0.7787 0.01358 0.00877 -0.0787 0.7076 0.7879
4.250 0.8114 0.01316 0.00837 -0.0797 0.7038 0.7889
4.500 0.8474 0.01250 0.00766 -0.0811 0.6979 0.7900
4.750 0.8770 0.01178 0.00696 -0.0812 0.6887 0.7913
5.000 0.9051 0.01116 0.00634 -0.0811 0.6782 0.7928
5.250 0.9361 0.01071 0.00587 -0.0817 0.6704 0.7942
5.500 0.9583 0.01060 0.00589 -0.0809 0.6636 0.7960
5.750 0.9858 0.01035 0.00566 -0.0810 0.6561 0.7978
6.000 1.0071 0.01019 0.00560 -0.0799 0.6451 0.7996
6.250 1.0282 0.01003 0.00551 -0.0788 0.6300 0.8014
6.500 1.0446 0.00992 0.00546 -0.0767 0.6014 0.8033
6.750 1.0385 0.01029 0.00550 -0.0700 0.5270 0.8060
7.000 1.0118 0.01133 0.00620 -0.0599 0.4629 0.8096
7.250 0.9875 0.01282 0.00738 -0.0512 0.4020 0.8133
7.500 0.9658 0.01457 0.00885 -0.0439 0.3426 0.8167
7.750 0.9479 0.01649 0.01050 -0.0378 0.2830 0.8200
8.000 0.9356 0.01842 0.01214 -0.0330 0.2237 0.8234
8.250 0.9294 0.02018 0.01362 -0.0293 0.1698 0.8269
8.500 0.9287 0.02172 0.01493 -0.0264 0.1262 0.8302
8.750 0.9328 0.02299 0.01607 -0.0240 0.0969 0.8333
9.000 0.9399 0.02413 0.01714 -0.0221 0.0774 0.8366
9.250 0.9495 0.02519 0.01817 -0.0205 0.0649 0.8403
9.500 0.9595 0.02627 0.01922 -0.0190 0.0562 0.8441
9.750 0.9720 0.02714 0.02017 -0.0178 0.0509 0.8480
10.000 0.9824 0.02818 0.02123 -0.0163 0.0459 0.8523
10.250 0.9934 0.02925 0.02237 -0.0151 0.0422 0.8571
10.500 1.0068 0.03013 0.02333 -0.0140 0.0393 0.8617
10.750 1.0177 0.03118 0.02445 -0.0128 0.0363 0.8669
11.000 1.0226 0.03276 0.02609 -0.0110 0.0334 0.8729
11.250 1.0361 0.03363 0.02709 -0.0100 0.0322 0.8793
11.500 1.0499 0.03454 0.02809 -0.0091 0.0302 0.8873
11.750 1.0628 0.03541 0.02904 -0.0082 0.0279 0.8974
12.000 1.0668 0.03697 0.03068 -0.0063 0.0251 0.9112
12.250 1.0793 0.03799 0.03191 -0.0053 0.0243 0.9401
12.500 1.1098 0.03812 0.03206 -0.0076 0.0207 1.0000
12.750 1.1180 0.03978 0.03372 -0.0068 0.0183 1.0000
13.000 1.1393 0.04032 0.03431 -0.0073 0.0166 1.0000
13.250 1.1536 0.04144 0.03547 -0.0070 0.0152 1.0000
13.500 1.1638 0.04291 0.03695 -0.0064 0.0136 1.0000
13.750 1.1769 0.04415 0.03829 -0.0061 0.0123 1.0000
14.000 1.1920 0.04521 0.03939 -0.0060 0.0106 1.0000
14.250 1.2025 0.04673 0.04094 -0.0055 0.0090 1.0000
14.500 1.2127 0.04829 0.04254 -0.0051 0.0064 1.0000
14.750 1.2181 0.05036 0.04466 -0.0043 0.0040 1.0000
15.000 1.2200 0.05281 0.04721 -0.0035 0.0029 1.0000
15.250 1.2226 0.05529 0.04983 -0.0029 0.0028 1.0000
15.500 1.2272 0.05762 0.05228 -0.0025 0.0027 1.0000
15.750 1.2301 0.06018 0.05498 -0.0021 0.0024 1.0000
16.000 1.2309 0.06304 0.05800 -0.0018 0.0023 1.0000
16.250 1.2308 0.06610 0.06120 -0.0017 0.0023 1.0000
16.500 1.2299 0.06933 0.06457 -0.0017 0.0021 1.0000
16.750 1.2277 0.07282 0.06820 -0.0019 0.0020 1.0000
17.000 1.2240 0.07662 0.07216 -0.0023 0.0020 1.0000
17.250 1.2186 0.08077 0.07646 -0.0030 0.0019 1.0000
17.500 1.2126 0.08517 0.08104 -0.0039 0.0020 1.0000
17.750 1.2043 0.09010 0.08612 -0.0053 0.0019 1.0000
18.000 1.1925 0.09573 0.09192 -0.0070 0.0018 1.0000
18.250 1.1821 0.10137 0.09773 -0.0091 0.0018 1.0000
18.500 1.1685 0.10780 0.10433 -0.0118 0.0018 1.0000
18.750 1.1542 0.11464 0.11134 -0.0150 0.0018 1.0000
19.000 1.1398 0.12178 0.11865 -0.0187 0.0018 1.0000
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