NREL's S821 Airfoil (s821-nr) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: NREL's S821 Airfoil (s821-nr) Reynolds number: 500,000 Max Cl/Cd: 66.01 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s821-nr-500000-n5.txt Download as CSV file: xf-s821-nr-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NREL's S821 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
------ -------- --------- --------- -------- -------- --------
-13.750 -0.7845 0.09156 0.08716 -0.0461 0.9997 0.1737
-13.500 -0.7643 0.09079 0.08641 -0.0469 0.9992 0.1741
-13.000 -0.9512 0.05924 0.05420 -0.0635 0.9954 0.1835
-12.750 -0.9305 0.05788 0.05285 -0.0656 0.9939 0.1843
-12.500 -0.9091 0.05618 0.05115 -0.0685 0.9923 0.1851
-12.250 -0.8873 0.05421 0.04917 -0.0720 0.9908 0.1860
-12.000 -0.8768 0.05166 0.04659 -0.0746 0.9886 0.1870
-11.750 -0.8697 0.04920 0.04409 -0.0765 0.9859 0.1880
-11.500 -0.8631 0.04646 0.04130 -0.0790 0.9832 0.1890
-11.250 -0.8524 0.04404 0.03883 -0.0817 0.9809 0.1900
-11.000 -0.8407 0.04151 0.03623 -0.0849 0.9787 0.1909
-10.750 -0.8246 0.03934 0.03400 -0.0881 0.9770 0.1918
-10.500 -0.8074 0.03710 0.03169 -0.0918 0.9755 0.1927
-10.250 -0.8072 0.03526 0.02980 -0.0915 0.9703 0.1933
-10.000 -0.7974 0.03334 0.02782 -0.0930 0.9658 0.1939
-9.750 -0.7792 0.03165 0.02607 -0.0955 0.9629 0.1944
-9.500 -0.7551 0.03031 0.02470 -0.0982 0.9608 0.1952
-9.250 -0.7281 0.02910 0.02351 -0.1011 0.9593 0.1963
-9.000 -0.7360 0.02769 0.02210 -0.0984 0.9488 0.1971
-8.750 -0.7146 0.02637 0.02077 -0.1005 0.9452 0.1979
-8.500 -0.7124 0.02504 0.01942 -0.0993 0.9363 0.1986
-8.250 -0.7028 0.02370 0.01806 -0.0994 0.9283 0.1993
-8.000 -0.7084 0.02234 0.01666 -0.0969 0.9143 0.2000
-7.750 -0.6853 0.02108 0.01538 -0.0987 0.9085 0.2007
-7.500 -0.6726 0.01993 0.01418 -0.0988 0.8956 0.2014
-7.250 -0.6376 0.01891 0.01311 -0.1022 0.8904 0.2023
-7.000 -0.6060 0.01800 0.01216 -0.1049 0.8808 0.2031
-6.750 -0.5617 0.01723 0.01134 -0.1095 0.8745 0.2040
-6.500 -0.5120 0.01661 0.01066 -0.1147 0.8671 0.2048
-6.250 -0.4612 0.01610 0.01008 -0.1200 0.8567 0.2057
-6.000 -0.4172 0.01566 0.00955 -0.1239 0.8425 0.2064
-5.750 -0.3812 0.01523 0.00904 -0.1263 0.8252 0.2075
-5.500 -0.3509 0.01487 0.00861 -0.1276 0.8066 0.2087
-5.250 -0.3238 0.01459 0.00825 -0.1282 0.7885 0.2096
-5.000 -0.2975 0.01434 0.00794 -0.1284 0.7715 0.2105
-4.750 -0.2713 0.01413 0.00766 -0.1286 0.7558 0.2114
-4.250 -0.2190 0.01377 0.00718 -0.1287 0.7260 0.2132
-4.000 -0.1927 0.01363 0.00697 -0.1287 0.7123 0.2142
-3.750 -0.1662 0.01348 0.00677 -0.1287 0.6984 0.2151
-3.500 -0.1391 0.01335 0.00658 -0.1287 0.6864 0.2161
-3.250 -0.1120 0.01323 0.00640 -0.1287 0.6744 0.2170
-3.000 -0.0845 0.01312 0.00624 -0.1288 0.6634 0.2179
-2.750 -0.0572 0.01304 0.00610 -0.1287 0.6513 0.2188
-2.500 -0.0296 0.01291 0.00594 -0.1288 0.6401 0.2200
-2.250 -0.0018 0.01277 0.00578 -0.1289 0.6288 0.2215
-2.000 0.0263 0.01266 0.00565 -0.1291 0.6193 0.2228
-1.750 0.0549 0.01256 0.00554 -0.1292 0.6094 0.2241
-1.250 0.1116 0.01241 0.00535 -0.1294 0.5901 0.2267
-1.000 0.1395 0.01237 0.00526 -0.1293 0.5796 0.2281
-0.750 0.1682 0.01232 0.00519 -0.1294 0.5706 0.2295
-0.500 0.1968 0.01227 0.00513 -0.1294 0.5616 0.2308
-0.250 0.2247 0.01227 0.00507 -0.1293 0.5531 0.2320
0.000 0.2542 0.01220 0.00501 -0.1295 0.5452 0.2335
0.250 0.2829 0.01215 0.00496 -0.1296 0.5360 0.2355
0.500 0.3115 0.01213 0.00493 -0.1296 0.5277 0.2376
0.750 0.3407 0.01209 0.00491 -0.1297 0.5195 0.2398
1.000 0.3690 0.01210 0.00490 -0.1296 0.5117 0.2419
1.250 0.3977 0.01211 0.00490 -0.1296 0.5046 0.2438
1.500 0.4265 0.01211 0.00490 -0.1296 0.4966 0.2456
1.750 0.4545 0.01214 0.00491 -0.1294 0.4886 0.2475
2.000 0.4836 0.01213 0.00493 -0.1294 0.4820 0.2500
2.250 0.5124 0.01214 0.00496 -0.1294 0.4741 0.2526
2.500 0.5394 0.01221 0.00500 -0.1290 0.4646 0.2551
2.750 0.5677 0.01224 0.00504 -0.1288 0.4552 0.2577
3.000 0.5944 0.01233 0.00509 -0.1283 0.4451 0.2601
3.250 0.6220 0.01239 0.00515 -0.1280 0.4358 0.2625
3.500 0.6493 0.01245 0.00522 -0.1277 0.4258 0.2657
3.750 0.6760 0.01253 0.00530 -0.1272 0.4172 0.2691
4.000 0.7027 0.01261 0.00538 -0.1267 0.4077 0.2726
4.250 0.7274 0.01274 0.00548 -0.1258 0.3978 0.2756
4.500 0.7537 0.01282 0.00557 -0.1252 0.3876 0.2784
4.750 0.7783 0.01296 0.00569 -0.1244 0.3778 0.2819
5.000 0.8046 0.01305 0.00581 -0.1238 0.3682 0.2855
5.250 0.8282 0.01323 0.00596 -0.1227 0.3578 0.2890
5.500 0.8537 0.01336 0.00610 -0.1220 0.3471 0.2922
5.750 0.8771 0.01357 0.00627 -0.1209 0.3353 0.2952
6.000 0.9013 0.01377 0.00647 -0.1200 0.3214 0.2991
6.250 0.9248 0.01401 0.00669 -0.1190 0.3062 0.3031
6.500 0.9464 0.01434 0.00696 -0.1177 0.2879 0.3071
6.750 0.9662 0.01475 0.00727 -0.1161 0.2664 0.3106
7.000 0.9849 0.01523 0.00765 -0.1144 0.2431 0.3145
7.250 1.0033 0.01574 0.00808 -0.1127 0.2205 0.3188
7.500 1.0212 0.01628 0.00853 -0.1110 0.2005 0.3228
7.750 1.0386 0.01682 0.00899 -0.1091 0.1833 0.3266
8.000 1.0558 0.01737 0.00947 -0.1073 0.1677 0.3298
8.250 1.0731 0.01794 0.00998 -0.1056 0.1529 0.3338
8.500 1.0893 0.01854 0.01054 -0.1037 0.1393 0.3381
8.750 1.1057 0.01914 0.01109 -0.1019 0.1276 0.3427
9.000 1.1223 0.01974 0.01166 -0.1001 0.1174 0.3470
9.250 1.1387 0.02034 0.01224 -0.0983 0.1094 0.3511
9.500 1.1549 0.02096 0.01287 -0.0966 0.1023 0.3561
9.750 1.1701 0.02164 0.01356 -0.0949 0.0958 0.3612
10.000 1.1855 0.02232 0.01425 -0.0931 0.0900 0.3661
10.500 1.2138 0.02389 0.01583 -0.0896 0.0798 0.3754
10.750 1.2283 0.02468 0.01666 -0.0880 0.0754 0.3809
11.000 1.2409 0.02561 0.01760 -0.0863 0.0715 0.3862
11.250 1.2534 0.02657 0.01858 -0.0846 0.0675 0.3905
11.500 1.2655 0.02761 0.01965 -0.0831 0.0639 0.3954
11.750 1.2771 0.02872 0.02080 -0.0816 0.0604 0.4009
12.000 1.2880 0.02991 0.02203 -0.0801 0.0573 0.4064
12.250 1.2981 0.03121 0.02335 -0.0787 0.0543 0.4114
12.500 1.3082 0.03256 0.02474 -0.0774 0.0516 0.4160
12.750 1.3175 0.03404 0.02627 -0.0763 0.0490 0.4214
13.000 1.3263 0.03561 0.02789 -0.0752 0.0467 0.4272
13.250 1.3348 0.03726 0.02959 -0.0742 0.0443 0.4327
13.500 1.3421 0.03908 0.03144 -0.0732 0.0423 0.4376
13.750 1.3497 0.04094 0.03338 -0.0725 0.0402 0.4434
14.000 1.3556 0.04303 0.03552 -0.0718 0.0383 0.4490
14.250 1.3629 0.04505 0.03760 -0.0712 0.0367 0.4546
14.500 1.3682 0.04733 0.03992 -0.0708 0.0351 0.4597
14.750 1.3728 0.04977 0.04244 -0.0705 0.0336 0.4659
15.000 1.3785 0.05216 0.04491 -0.0703 0.0322 0.4726
15.250 1.3824 0.05480 0.04761 -0.0702 0.0309 0.4786
15.500 1.3849 0.05767 0.05053 -0.0702 0.0298 0.4835
15.750 1.3892 0.06043 0.05338 -0.0704 0.0287 0.4898
16.000 1.3925 0.06336 0.05640 -0.0707 0.0277 0.4968
16.250 1.3940 0.06659 0.05971 -0.0711 0.0267 0.5032
16.500 1.3956 0.06987 0.06306 -0.0716 0.0260 0.5094
16.750 1.3982 0.07310 0.06639 -0.0722 0.0251 0.5164
17.000 1.3992 0.07662 0.06999 -0.0730 0.0244 0.5232
17.250 1.4000 0.08020 0.07365 -0.0739 0.0236 0.5298
17.500 1.3998 0.08402 0.07756 -0.0750 0.0230 0.5366
17.750 1.3993 0.08793 0.08157 -0.0761 0.0225 0.5444
18.000 1.4004 0.09165 0.08538 -0.0773 0.0219 0.5521
18.250 1.3998 0.09570 0.08953 -0.0787 0.0214 0.5593
18.500 1.3993 0.09976 0.09369 -0.0801 0.0208 0.5672
18.750 1.3979 0.10396 0.09798 -0.0817 0.0203 0.5749
19.000 1.3954 0.10842 0.10254 -0.0835 0.0199 0.5826
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