NREL's S817 Airfoil (s817-nr) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: NREL's S817 Airfoil (s817-nr) Reynolds number: 1,000,000 Max Cl/Cd: 126.03 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s817-nr-1000000-n5.txt Download as CSV file: xf-s817-nr-1000000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.750 -0.1560 0.09725 0.09437 -0.0848 0.7110 0.0038
-7.750 -0.4063 0.01791 0.01227 -0.0802 0.6990 0.0023
-7.500 -0.3821 0.01605 0.01012 -0.0800 0.6984 0.0025
-7.250 -0.3577 0.01547 0.00947 -0.0799 0.6976 0.0028
-7.000 -0.3332 0.01484 0.00874 -0.0798 0.6969 0.0029
-6.750 -0.3086 0.01440 0.00825 -0.0796 0.6961 0.0030
-6.500 -0.2845 0.01390 0.00768 -0.0793 0.6953 0.0032
-6.250 -0.2613 0.01331 0.00701 -0.0789 0.6944 0.0032
-6.000 -0.2376 0.01294 0.00659 -0.0785 0.6936 0.0034
-5.750 -0.2148 0.01251 0.00610 -0.0780 0.6928 0.0035
-5.500 -0.1925 0.01208 0.00561 -0.0773 0.6920 0.0037
-5.250 -0.1699 0.01172 0.00520 -0.0767 0.6911 0.0038
-5.000 -0.1473 0.01137 0.00480 -0.0761 0.6901 0.0040
-4.750 -0.1232 0.01114 0.00454 -0.0758 0.6892 0.0041
-4.500 -0.1010 0.01078 0.00413 -0.0751 0.6883 0.0045
-4.250 -0.0766 0.01056 0.00391 -0.0749 0.6875 0.0052
-4.000 -0.0519 0.01036 0.00368 -0.0747 0.6867 0.0058
-3.750 -0.0277 0.01011 0.00340 -0.0743 0.6859 0.0070
-3.500 -0.0023 0.00994 0.00321 -0.0742 0.6851 0.0088
-3.250 0.0233 0.00975 0.00302 -0.0742 0.6845 0.0111
-3.000 0.0495 0.00959 0.00286 -0.0743 0.6840 0.0127
-2.750 0.0756 0.00943 0.00272 -0.0743 0.6834 0.0166
-2.500 0.1018 0.00927 0.00258 -0.0744 0.6827 0.0232
-2.250 0.1282 0.00911 0.00247 -0.0746 0.6819 0.0352
-2.000 0.1546 0.00894 0.00237 -0.0747 0.6811 0.0546
-1.750 0.1812 0.00878 0.00228 -0.0749 0.6803 0.0788
-1.500 0.2067 0.00851 0.00217 -0.0750 0.6795 0.1411
-1.250 0.2159 0.00643 0.00166 -0.0731 0.6787 0.6544
-1.000 0.2444 0.00644 0.00171 -0.0735 0.6780 0.6811
-0.750 0.2732 0.00647 0.00175 -0.0740 0.6773 0.6917
-0.500 0.3024 0.00651 0.00174 -0.0746 0.6766 0.6964
-0.250 0.3313 0.00653 0.00177 -0.0752 0.6759 0.7015
0.000 0.3602 0.00656 0.00179 -0.0757 0.6751 0.7055
0.250 0.3893 0.00661 0.00181 -0.0763 0.6743 0.7092
0.500 0.4184 0.00663 0.00182 -0.0769 0.6736 0.7102
0.750 0.4475 0.00666 0.00183 -0.0776 0.6729 0.7109
1.000 0.4767 0.00670 0.00185 -0.0782 0.6722 0.7116
1.250 0.5058 0.00675 0.00188 -0.0788 0.6713 0.7124
1.500 0.5348 0.00678 0.00192 -0.0795 0.6706 0.7134
1.750 0.5635 0.00679 0.00197 -0.0800 0.6699 0.7144
2.000 0.5923 0.00681 0.00202 -0.0806 0.6692 0.7154
2.250 0.6211 0.00684 0.00207 -0.0812 0.6686 0.7163
2.500 0.6499 0.00687 0.00214 -0.0818 0.6678 0.7172
2.750 0.6785 0.00690 0.00221 -0.0824 0.6669 0.7182
3.000 0.7072 0.00694 0.00228 -0.0829 0.6660 0.7193
3.250 0.7358 0.00697 0.00234 -0.0835 0.6648 0.7203
3.500 0.7639 0.00696 0.00236 -0.0839 0.6620 0.7214
3.750 0.7914 0.00694 0.00233 -0.0841 0.6563 0.7225
4.000 0.8176 0.00685 0.00230 -0.0841 0.6472 0.7237
4.250 0.8431 0.00681 0.00226 -0.0839 0.6327 0.7248
4.500 0.8658 0.00687 0.00225 -0.0832 0.6031 0.7260
5.000 0.8668 0.00860 0.00320 -0.0732 0.4337 0.7289
5.250 0.8615 0.00938 0.00373 -0.0672 0.3731 0.7306
5.500 0.8571 0.01015 0.00430 -0.0614 0.3239 0.7324
5.750 0.8522 0.01108 0.00501 -0.0559 0.2731 0.7343
6.000 0.8489 0.01208 0.00580 -0.0510 0.2243 0.7365
6.250 0.8489 0.01308 0.00663 -0.0470 0.1825 0.7385
6.500 0.8538 0.01399 0.00741 -0.0439 0.1507 0.7403
7.000 0.8690 0.01577 0.00899 -0.0390 0.0989 0.7436
7.250 0.8813 0.01650 0.00968 -0.0373 0.0843 0.7454
7.500 0.8948 0.01720 0.01036 -0.0359 0.0730 0.7472
7.750 0.9088 0.01789 0.01104 -0.0346 0.0638 0.7491
8.000 0.9225 0.01861 0.01174 -0.0332 0.0545 0.7510
8.250 0.9370 0.01931 0.01242 -0.0320 0.0472 0.7530
8.500 0.9520 0.01999 0.01310 -0.0309 0.0418 0.7548
8.750 0.9671 0.02068 0.01379 -0.0299 0.0377 0.7565
9.000 0.9816 0.02139 0.01452 -0.0287 0.0327 0.7586
9.250 0.9973 0.02205 0.01522 -0.0278 0.0307 0.7607
9.500 1.0104 0.02287 0.01601 -0.0266 0.0244 0.7630
9.750 1.0256 0.02358 0.01675 -0.0257 0.0218 0.7653
10.000 1.0395 0.02439 0.01754 -0.0246 0.0184 0.7677
10.250 1.0557 0.02508 0.01828 -0.0239 0.0183 0.7700
10.500 1.0708 0.02583 0.01907 -0.0230 0.0164 0.7724
10.750 1.0847 0.02666 0.01992 -0.0221 0.0144 0.7752
11.000 1.0996 0.02745 0.02075 -0.0212 0.0133 0.7781
11.250 1.1142 0.02827 0.02161 -0.0204 0.0116 0.7811
11.500 1.1283 0.02914 0.02251 -0.0196 0.0103 0.7839
12.000 1.1549 0.03103 0.02444 -0.0179 0.0065 0.7897
12.250 1.1691 0.03193 0.02542 -0.0172 0.0064 0.7932
12.500 1.1804 0.03305 0.02655 -0.0162 0.0039 0.7967
12.750 1.1934 0.03409 0.02764 -0.0154 0.0030 0.8001
13.000 1.2019 0.03548 0.02906 -0.0143 0.0011 0.8037
13.250 1.2149 0.03652 0.03018 -0.0136 0.0011 0.8079
13.500 1.2263 0.03774 0.03146 -0.0128 0.0007 0.8122
13.750 1.2384 0.03891 0.03272 -0.0121 0.0007 0.8165
14.000 1.2495 0.04018 0.03408 -0.0114 0.0005 0.8215
14.250 1.2604 0.04149 0.03548 -0.0107 0.0004 0.8271
14.500 1.2706 0.04287 0.03696 -0.0100 0.0004 0.8330
14.750 1.2777 0.04457 0.03878 -0.0091 0.0002 0.8401
15.000 1.2868 0.04610 0.04044 -0.0084 0.0002 0.8475
15.250 1.2965 0.04757 0.04202 -0.0078 0.0002 0.8575
15.500 1.3047 0.04920 0.04378 -0.0072 0.0002 0.8687
15.750 1.3118 0.05089 0.04562 -0.0065 0.0002 0.8840
16.000 1.3168 0.05260 0.04752 -0.0054 0.0002 0.9128
16.500 1.3316 0.05671 0.05196 -0.0054 0.0002 1.0000
16.750 1.3354 0.05909 0.05445 -0.0051 0.0002 1.0000
17.000 1.3413 0.06126 0.05670 -0.0050 0.0002 1.0000
17.250 1.3420 0.06408 0.05966 -0.0048 0.0002 1.0000
17.500 1.3456 0.06665 0.06231 -0.0049 0.0002 1.0000
17.750 1.3459 0.06968 0.06546 -0.0050 0.0002 1.0000
18.000 1.3432 0.07320 0.06913 -0.0052 0.0002 1.0000
18.250 1.3412 0.07669 0.07274 -0.0057 0.0002 1.0000
18.500 1.3372 0.08056 0.07674 -0.0064 0.0001 1.0000
18.750 1.3308 0.08491 0.08124 -0.0073 0.0001 1.0000
19.000 1.3238 0.08952 0.08599 -0.0086 0.0001 1.0000
19.250 1.3127 0.09491 0.09154 -0.0102 0.0001 1.0000
|
Polar data table (+)
Polar graphs
<< Back to NREL's S817 Airfoil (s817-nr)