NREL's S822 Airfoil (s822-nr) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: NREL's S822 Airfoil (s822-nr) Reynolds number: 500,000 Max Cl/Cd: 85.13 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s822-nr-500000-n5.txt Download as CSV file: xf-s822-nr-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NREL's S822 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
------ -------- --------- --------- -------- -------- --------
-18.500 -0.7919 0.10916 0.10558 -0.0616 1.0000 0.0053
-18.250 -0.8105 0.10223 0.09854 -0.0648 1.0000 0.0053
-18.000 -0.8284 0.09554 0.09174 -0.0680 1.0000 0.0055
-17.750 -0.8470 0.08893 0.08501 -0.0711 1.0000 0.0054
-17.500 -0.8651 0.08254 0.07851 -0.0741 1.0000 0.0055
-17.250 -0.8818 0.07654 0.07239 -0.0769 1.0000 0.0053
-17.000 -0.8962 0.07104 0.06677 -0.0794 1.0000 0.0055
-16.750 -0.9097 0.06583 0.06144 -0.0817 1.0000 0.0054
-16.500 -0.9207 0.06116 0.05666 -0.0836 1.0000 0.0056
-16.250 -0.9307 0.05680 0.05219 -0.0853 1.0000 0.0056
-16.000 -0.9377 0.05303 0.04831 -0.0865 1.0000 0.0058
-15.750 -0.9449 0.04946 0.04463 -0.0875 1.0000 0.0058
-15.500 -0.9518 0.04612 0.04119 -0.0881 1.0000 0.0060
-15.250 -0.9566 0.04326 0.03822 -0.0883 1.0000 0.0060
-15.000 -0.9601 0.04077 0.03563 -0.0880 1.0000 0.0063
-14.750 -0.9637 0.03849 0.03326 -0.0874 1.0000 0.0063
-14.500 -0.9599 0.03599 0.03068 -0.0884 0.9982 0.0067
-14.250 -0.9496 0.03364 0.02824 -0.0901 0.9893 0.0071
-13.750 -0.9190 0.02981 0.02423 -0.0939 0.9735 0.0082
-13.500 -0.8980 0.02819 0.02249 -0.0963 0.9656 0.0087
-13.250 -0.8760 0.02654 0.02075 -0.0989 0.9569 0.0093
-13.000 -0.8515 0.02508 0.01922 -0.1015 0.9478 0.0106
-12.750 -0.8255 0.02385 0.01788 -0.1040 0.9386 0.0117
-12.500 -0.8034 0.02276 0.01667 -0.1054 0.9279 0.0121
-12.250 -0.7884 0.02175 0.01559 -0.1053 0.9168 0.0140
-12.000 -0.7739 0.02098 0.01472 -0.1046 0.9079 0.0153
-11.750 -0.7616 0.02022 0.01388 -0.1034 0.8996 0.0167
-11.500 -0.7500 0.01949 0.01309 -0.1020 0.8924 0.0184
-11.250 -0.7370 0.01888 0.01240 -0.1005 0.8858 0.0198
-11.000 -0.7232 0.01831 0.01174 -0.0991 0.8806 0.0214
-10.750 -0.7113 0.01767 0.01109 -0.0974 0.8752 0.0241
-10.500 -0.6973 0.01716 0.01051 -0.0959 0.8702 0.0267
-10.250 -0.6839 0.01663 0.00994 -0.0942 0.8659 0.0297
-10.000 -0.6703 0.01612 0.00942 -0.0924 0.8612 0.0331
-9.750 -0.6559 0.01569 0.00893 -0.0906 0.8567 0.0366
-9.500 -0.6426 0.01525 0.00846 -0.0886 0.8528 0.0410
-9.000 -0.6124 0.01452 0.00771 -0.0850 0.8451 0.0516
-8.750 -0.5938 0.01418 0.00734 -0.0838 0.8417 0.0579
-8.500 -0.5749 0.01381 0.00697 -0.0826 0.8386 0.0664
-8.250 -0.5554 0.01345 0.00663 -0.0815 0.8357 0.0752
-8.000 -0.5348 0.01314 0.00632 -0.0806 0.8326 0.0835
-7.500 -0.4923 0.01250 0.00571 -0.0790 0.8267 0.1057
-7.250 -0.4702 0.01221 0.00542 -0.0783 0.8241 0.1175
-7.000 -0.4478 0.01192 0.00516 -0.0776 0.8216 0.1310
-6.750 -0.4254 0.01162 0.00492 -0.0770 0.8187 0.1474
-6.500 -0.4024 0.01134 0.00468 -0.0764 0.8159 0.1636
-6.250 -0.3792 0.01107 0.00445 -0.0759 0.8131 0.1802
-6.000 -0.3554 0.01081 0.00423 -0.0755 0.8105 0.1973
-5.750 -0.3311 0.01057 0.00402 -0.0751 0.8081 0.2164
-5.500 -0.3068 0.01034 0.00384 -0.0747 0.8055 0.2349
-5.250 -0.2824 0.01011 0.00367 -0.0744 0.8027 0.2542
-5.000 -0.2577 0.00989 0.00351 -0.0741 0.7999 0.2734
-4.750 -0.2325 0.00969 0.00336 -0.0738 0.7972 0.2941
-4.500 -0.2070 0.00949 0.00320 -0.0736 0.7946 0.3150
-4.250 -0.1813 0.00931 0.00306 -0.0735 0.7922 0.3364
-4.000 -0.1559 0.00913 0.00295 -0.0732 0.7892 0.3580
-3.750 -0.1304 0.00895 0.00284 -0.0730 0.7863 0.3807
-3.500 -0.1043 0.00879 0.00274 -0.0729 0.7835 0.4026
-3.250 -0.0780 0.00863 0.00263 -0.0728 0.7808 0.4251
-3.000 -0.0512 0.00850 0.00253 -0.0728 0.7783 0.4478
-2.750 -0.0253 0.00835 0.00247 -0.0727 0.7751 0.4705
-2.250 0.0277 0.00809 0.00236 -0.0725 0.7688 0.5155
-2.000 0.0548 0.00799 0.00231 -0.0725 0.7661 0.5386
-1.750 0.0824 0.00791 0.00227 -0.0726 0.7635 0.5609
-1.500 0.1092 0.00784 0.00228 -0.0725 0.7599 0.5801
-1.250 0.1365 0.00780 0.00228 -0.0726 0.7563 0.5975
-1.000 0.1642 0.00776 0.00227 -0.0726 0.7531 0.6128
-0.750 0.1923 0.00773 0.00226 -0.0728 0.7503 0.6262
-0.500 0.2201 0.00771 0.00227 -0.0729 0.7470 0.6385
-0.250 0.2474 0.00769 0.00230 -0.0729 0.7430 0.6495
0.000 0.2753 0.00768 0.00231 -0.0730 0.7394 0.6600
0.250 0.3034 0.00767 0.00231 -0.0732 0.7361 0.6699
0.500 0.3313 0.00767 0.00234 -0.0733 0.7327 0.6789
0.750 0.3587 0.00767 0.00238 -0.0733 0.7279 0.6879
1.000 0.3861 0.00765 0.00239 -0.0732 0.7223 0.6962
1.250 0.4130 0.00765 0.00240 -0.0731 0.7150 0.7046
1.500 0.4397 0.00765 0.00241 -0.0729 0.7070 0.7127
1.750 0.4664 0.00766 0.00245 -0.0727 0.6992 0.7205
2.000 0.4930 0.00768 0.00248 -0.0725 0.6914 0.7284
2.250 0.5194 0.00771 0.00254 -0.0723 0.6830 0.7359
2.500 0.5455 0.00775 0.00259 -0.0720 0.6746 0.7435
2.750 0.5714 0.00780 0.00266 -0.0716 0.6650 0.7508
3.000 0.5971 0.00787 0.00275 -0.0712 0.6555 0.7582
3.250 0.6223 0.00795 0.00282 -0.0708 0.6452 0.7654
3.500 0.6468 0.00804 0.00293 -0.0701 0.6330 0.7723
3.750 0.6711 0.00815 0.00303 -0.0695 0.6197 0.7794
4.000 0.6940 0.00827 0.00316 -0.0686 0.6045 0.7858
4.250 0.7161 0.00843 0.00328 -0.0675 0.5857 0.7930
4.500 0.7347 0.00863 0.00344 -0.0657 0.5587 0.7993
4.750 0.7488 0.00896 0.00363 -0.0631 0.5187 0.8070
5.000 0.7557 0.00943 0.00391 -0.0590 0.4708 0.8138
5.250 0.7600 0.00992 0.00422 -0.0546 0.4288 0.8216
5.500 0.7669 0.01042 0.00459 -0.0507 0.3926 0.8280
5.750 0.7750 0.01098 0.00501 -0.0473 0.3556 0.8350
6.000 0.7847 0.01153 0.00543 -0.0442 0.3227 0.8413
6.250 0.7948 0.01208 0.00587 -0.0413 0.2915 0.8479
6.500 0.8058 0.01266 0.00632 -0.0387 0.2613 0.8544
6.750 0.8177 0.01318 0.00677 -0.0362 0.2352 0.8606
7.000 0.8299 0.01376 0.00726 -0.0339 0.2093 0.8676
7.250 0.8416 0.01433 0.00776 -0.0315 0.1865 0.8738
7.500 0.8535 0.01495 0.00829 -0.0293 0.1622 0.8809
8.000 0.8800 0.01607 0.00932 -0.0252 0.1289 0.8956
8.250 0.8926 0.01665 0.00987 -0.0232 0.1128 0.9034
8.750 0.9185 0.01782 0.01100 -0.0193 0.0879 0.9234
9.000 0.9317 0.01842 0.01160 -0.0174 0.0772 0.9380
9.250 0.9516 0.01902 0.01222 -0.0171 0.0683 0.9571
9.750 0.9907 0.02038 0.01355 -0.0165 0.0541 1.0000
10.000 1.0072 0.02104 0.01423 -0.0155 0.0488 1.0000
10.250 1.0218 0.02184 0.01500 -0.0144 0.0430 1.0000
10.500 1.0379 0.02255 0.01573 -0.0134 0.0392 1.0000
10.750 1.0522 0.02337 0.01654 -0.0123 0.0351 1.0000
11.000 1.0669 0.02418 0.01737 -0.0112 0.0320 1.0000
11.250 1.0815 0.02500 0.01821 -0.0102 0.0291 1.0000
11.500 1.0943 0.02596 0.01917 -0.0090 0.0263 1.0000
11.750 1.1083 0.02684 0.02011 -0.0080 0.0244 1.0000
12.000 1.1215 0.02780 0.02110 -0.0069 0.0226 1.0000
12.250 1.1339 0.02883 0.02214 -0.0059 0.0208 1.0000
12.500 1.1451 0.02997 0.02331 -0.0047 0.0193 1.0000
12.750 1.1581 0.03098 0.02439 -0.0038 0.0182 1.0000
13.000 1.1698 0.03211 0.02556 -0.0029 0.0170 1.0000
13.250 1.1808 0.03333 0.02681 -0.0019 0.0158 1.0000
13.500 1.1894 0.03476 0.02828 -0.0009 0.0146 1.0000
13.750 1.2006 0.03601 0.02961 -0.0001 0.0141 1.0000
14.000 1.2109 0.03735 0.03103 0.0007 0.0134 1.0000
14.250 1.2205 0.03878 0.03251 0.0015 0.0126 1.0000
14.500 1.2290 0.04035 0.03415 0.0022 0.0121 1.0000
14.750 1.2366 0.04205 0.03589 0.0029 0.0115 1.0000
15.000 1.2438 0.04381 0.03770 0.0035 0.0106 1.0000
15.250 1.2510 0.04562 0.03960 0.0040 0.0102 1.0000
15.500 1.2570 0.04758 0.04166 0.0045 0.0099 1.0000
15.750 1.2640 0.04950 0.04365 0.0048 0.0093 1.0000
16.000 1.2688 0.05170 0.04593 0.0051 0.0089 1.0000
16.250 1.2734 0.05397 0.04828 0.0053 0.0084 1.0000
16.500 1.2750 0.05665 0.05104 0.0053 0.0080 1.0000
16.750 1.2768 0.05937 0.05385 0.0053 0.0078 1.0000
17.000 1.2800 0.06201 0.05660 0.0050 0.0074 1.0000
17.250 1.2815 0.06493 0.05962 0.0047 0.0070 1.0000
17.500 1.2815 0.06810 0.06290 0.0041 0.0068 1.0000
17.750 1.2808 0.07145 0.06636 0.0034 0.0066 1.0000
18.000 1.2789 0.07508 0.07010 0.0025 0.0063 1.0000
18.250 1.2762 0.07895 0.07406 0.0013 0.0061 1.0000
18.500 1.2710 0.08330 0.07852 -0.0002 0.0059 1.0000
18.750 1.2642 0.08802 0.08335 -0.0020 0.0057 1.0000
19.000 1.2539 0.09345 0.08892 -0.0043 0.0055 1.0000
19.250 1.2464 0.09858 0.09417 -0.0066 0.0055 1.0000
|
Polar data table (+)
Polar graphs
<< Back to NREL's S822 Airfoil (s822-nr)