NREL's S820 Airfoil (s820-nr) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: NREL's S820 Airfoil (s820-nr) Reynolds number: 500,000 Max Cl/Cd: 95.06 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s820-nr-500000-n5.txt Download as CSV file: xf-s820-nr-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NREL's S820 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.3433 0.06247 0.05918 -0.1082 0.8126 0.0079
-8.500 -0.4350 0.03577 0.03099 -0.0912 0.7813 0.0045
-8.250 -0.4306 0.03334 0.02835 -0.0890 0.7784 0.0044
-8.000 -0.4221 0.03086 0.02562 -0.0870 0.7758 0.0043
-7.750 -0.4099 0.02848 0.02297 -0.0852 0.7734 0.0042
-7.500 -0.3944 0.02614 0.02034 -0.0837 0.7712 0.0041
-7.250 -0.3754 0.02367 0.01758 -0.0825 0.7690 0.0039
-7.000 -0.3529 0.02148 0.01511 -0.0817 0.7667 0.0038
-6.750 -0.3282 0.01976 0.01317 -0.0812 0.7646 0.0037
-6.500 -0.3032 0.01834 0.01157 -0.0808 0.7626 0.0036
-6.250 -0.2796 0.01712 0.01019 -0.0801 0.7606 0.0036
-6.000 -0.2580 0.01624 0.00920 -0.0793 0.7586 0.0037
-5.750 -0.2378 0.01549 0.00836 -0.0782 0.7568 0.0037
-5.500 -0.2187 0.01477 0.00755 -0.0771 0.7547 0.0038
-5.250 -0.1987 0.01419 0.00693 -0.0761 0.7524 0.0038
-5.000 -0.1785 0.01364 0.00632 -0.0751 0.7500 0.0040
-4.750 -0.1571 0.01317 0.00579 -0.0743 0.7478 0.0041
-4.500 -0.1348 0.01274 0.00530 -0.0737 0.7459 0.0044
-4.250 -0.1114 0.01239 0.00487 -0.0732 0.7440 0.0047
-4.000 -0.0877 0.01203 0.00445 -0.0728 0.7423 0.0053
-3.750 -0.0626 0.01177 0.00416 -0.0726 0.7406 0.0063
-3.500 -0.0373 0.01152 0.00389 -0.0725 0.7386 0.0080
-3.250 -0.0121 0.01126 0.00364 -0.0723 0.7364 0.0155
-3.000 0.0053 0.01021 0.00319 -0.0714 0.7341 0.1740
-2.750 0.0123 0.00812 0.00267 -0.0692 0.7318 0.5949
-2.500 0.0393 0.00826 0.00289 -0.0690 0.7300 0.6412
-2.250 0.0681 0.00832 0.00285 -0.0694 0.7284 0.6499
-2.000 0.0972 0.00832 0.00277 -0.0699 0.7269 0.6521
-1.750 0.1259 0.00831 0.00274 -0.0703 0.7251 0.6540
-1.500 0.1546 0.00830 0.00270 -0.0707 0.7231 0.6559
-1.250 0.1834 0.00830 0.00267 -0.0711 0.7209 0.6579
-1.000 0.2122 0.00830 0.00263 -0.0716 0.7189 0.6599
-0.750 0.2410 0.00831 0.00260 -0.0720 0.7170 0.6621
-0.500 0.2700 0.00832 0.00256 -0.0725 0.7153 0.6645
-0.250 0.2991 0.00834 0.00254 -0.0730 0.7137 0.6666
0.000 0.3279 0.00836 0.00256 -0.0735 0.7120 0.6684
0.250 0.3562 0.00837 0.00259 -0.0738 0.7098 0.6703
0.500 0.3846 0.00838 0.00262 -0.0742 0.7076 0.6723
0.750 0.4132 0.00841 0.00265 -0.0747 0.7055 0.6745
1.000 0.4419 0.00843 0.00267 -0.0751 0.7035 0.6768
1.250 0.4706 0.00846 0.00269 -0.0756 0.7015 0.6792
1.500 0.4995 0.00849 0.00272 -0.0760 0.6997 0.6815
1.750 0.5281 0.00852 0.00278 -0.0765 0.6979 0.6836
2.000 0.5559 0.00855 0.00286 -0.0767 0.6951 0.6857
2.250 0.5837 0.00856 0.00292 -0.0770 0.6915 0.6880
2.500 0.6115 0.00855 0.00291 -0.0772 0.6865 0.6904
2.750 0.6382 0.00853 0.00291 -0.0772 0.6784 0.6929
3.000 0.6650 0.00851 0.00286 -0.0771 0.6692 0.6953
3.250 0.6913 0.00850 0.00291 -0.0770 0.6602 0.6974
3.500 0.7178 0.00852 0.00296 -0.0770 0.6521 0.6997
3.750 0.7441 0.00855 0.00303 -0.0769 0.6437 0.7023
4.000 0.7702 0.00860 0.00311 -0.0768 0.6342 0.7051
4.250 0.7955 0.00866 0.00318 -0.0766 0.6218 0.7080
4.500 0.8196 0.00876 0.00327 -0.0760 0.6051 0.7107
4.750 0.8425 0.00889 0.00339 -0.0753 0.5865 0.7130
5.000 0.8631 0.00908 0.00354 -0.0741 0.5594 0.7156
5.250 0.8745 0.00953 0.00379 -0.0712 0.5069 0.7186
5.500 0.8781 0.01024 0.00422 -0.0669 0.4496 0.7218
5.750 0.8793 0.01091 0.00467 -0.0621 0.4018 0.7250
6.000 0.8800 0.01161 0.00521 -0.0575 0.3586 0.7280
6.250 0.8828 0.01240 0.00583 -0.0534 0.3158 0.7315
6.500 0.8895 0.01313 0.00642 -0.0502 0.2824 0.7354
6.750 0.8983 0.01383 0.00702 -0.0475 0.2527 0.7391
7.000 0.9069 0.01458 0.00767 -0.0449 0.2237 0.7424
7.500 0.9284 0.01601 0.00897 -0.0405 0.1765 0.7499
7.750 0.9395 0.01678 0.00966 -0.0386 0.1554 0.7539
8.000 0.9522 0.01749 0.01034 -0.0369 0.1389 0.7576
8.250 0.9653 0.01820 0.01104 -0.0353 0.1245 0.7619
8.500 0.9783 0.01895 0.01176 -0.0338 0.1100 0.7667
8.750 0.9916 0.01970 0.01250 -0.0323 0.0976 0.7714
9.000 1.0048 0.02045 0.01325 -0.0309 0.0872 0.7763
9.250 1.0194 0.02117 0.01399 -0.0297 0.0785 0.7817
9.500 1.0329 0.02195 0.01478 -0.0284 0.0694 0.7869
9.750 1.0462 0.02276 0.01561 -0.0271 0.0613 0.7930
10.250 1.0738 0.02434 0.01728 -0.0247 0.0490 0.8068
10.500 1.0861 0.02526 0.01821 -0.0235 0.0414 0.8146
10.750 1.0998 0.02606 0.01909 -0.0224 0.0369 0.8233
11.000 1.1115 0.02701 0.02008 -0.0211 0.0319 0.8329
11.250 1.1229 0.02799 0.02110 -0.0198 0.0256 0.8451
11.500 1.1342 0.02895 0.02215 -0.0185 0.0222 0.8610
11.750 1.1427 0.03003 0.02331 -0.0168 0.0171 0.8847
12.000 1.1561 0.03119 0.02458 -0.0164 0.0122 0.9477
12.500 1.1785 0.03358 0.02704 -0.0148 0.0078 1.0000
12.750 1.1892 0.03488 0.02838 -0.0139 0.0065 1.0000
13.000 1.1998 0.03620 0.02975 -0.0131 0.0052 1.0000
13.250 1.2103 0.03756 0.03118 -0.0124 0.0046 1.0000
13.500 1.2195 0.03906 0.03274 -0.0116 0.0040 1.0000
13.750 1.2294 0.04053 0.03429 -0.0109 0.0034 1.0000
14.000 1.2385 0.04210 0.03596 -0.0103 0.0030 1.0000
14.250 1.2459 0.04386 0.03779 -0.0096 0.0025 1.0000
14.500 1.2536 0.04563 0.03966 -0.0091 0.0020 1.0000
14.750 1.2609 0.04750 0.04162 -0.0086 0.0019 1.0000
15.000 1.2670 0.04950 0.04371 -0.0081 0.0017 1.0000
15.250 1.2697 0.05193 0.04624 -0.0077 0.0013 1.0000
15.500 1.2752 0.05410 0.04851 -0.0074 0.0011 1.0000
15.750 1.2791 0.05651 0.05104 -0.0072 0.0011 1.0000
16.000 1.2797 0.05938 0.05403 -0.0071 0.0009 1.0000
16.250 1.2826 0.06203 0.05679 -0.0072 0.0009 1.0000
16.500 1.2821 0.06514 0.06002 -0.0073 0.0008 1.0000
16.750 1.2779 0.06888 0.06392 -0.0077 0.0006 1.0000
17.000 1.2787 0.07208 0.06724 -0.0082 0.0007 1.0000
17.250 1.2753 0.07594 0.07123 -0.0091 0.0007 1.0000
17.500 1.2709 0.08006 0.07550 -0.0101 0.0007 1.0000
17.750 1.2593 0.08545 0.08105 -0.0117 0.0006 1.0000
18.000 1.2493 0.09082 0.08659 -0.0136 0.0006 1.0000
18.250 1.2407 0.09618 0.09211 -0.0158 0.0005 1.0000
18.500 1.2337 0.10134 0.09740 -0.0181 0.0006 1.0000
18.750 1.2185 0.10826 0.10449 -0.0213 0.0006 1.0000
19.000 1.2064 0.11478 0.11117 -0.0246 0.0005 1.0000
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Polar data table (+)
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