NREL's S821 Airfoil (s821-nr) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: NREL's S821 Airfoil (s821-nr) Reynolds number: 500,000 Max Cl/Cd: 72.85 at α=7.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s821-nr-500000.txt Download as CSV file: xf-s821-nr-500000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 -0.3059 0.13949 0.13599 -0.0228 1.0000 0.1707
-10.750 -0.9694 0.04068 0.03575 -0.0679 0.9913 0.2053
-10.500 -0.9766 0.03632 0.03121 -0.0734 0.9842 0.2063
-10.250 -0.9681 0.03319 0.02795 -0.0780 0.9789 0.2075
-10.000 -0.9390 0.03194 0.02669 -0.0812 0.9767 0.2086
-9.750 -0.9049 0.03113 0.02589 -0.0846 0.9753 0.2094
-9.500 -0.8960 0.02993 0.02468 -0.0842 0.9664 0.2101
-9.250 -0.8681 0.02891 0.02365 -0.0869 0.9629 0.2109
-9.000 -0.8366 0.02790 0.02263 -0.0904 0.9605 0.2118
-8.750 -0.8274 0.02657 0.02126 -0.0905 0.9515 0.2125
-8.500 -0.7976 0.02533 0.01998 -0.0938 0.9473 0.2134
-8.250 -0.7619 0.02415 0.01876 -0.0980 0.9449 0.2144
-8.000 -0.7237 0.02308 0.01764 -0.1025 0.9432 0.2156
-7.750 -0.7107 0.02217 0.01667 -0.1019 0.9328 0.2164
-7.500 -0.6757 0.02138 0.01582 -0.1047 0.9298 0.2174
-7.250 -0.6379 0.02065 0.01504 -0.1078 0.9278 0.2182
-7.000 -0.5987 0.02000 0.01434 -0.1109 0.9263 0.2188
-6.750 -0.5830 0.01946 0.01375 -0.1095 0.9154 0.2192
-6.500 -0.5502 0.01843 0.01274 -0.1113 0.9122 0.2207
-6.250 -0.5141 0.01776 0.01210 -0.1132 0.9098 0.2219
-6.000 -0.4927 0.01727 0.01162 -0.1125 0.8999 0.2228
-5.750 -0.4579 0.01677 0.01113 -0.1141 0.8945 0.2237
-5.500 -0.4152 0.01628 0.01064 -0.1172 0.8911 0.2248
-5.250 -0.3838 0.01588 0.01024 -0.1182 0.8809 0.2258
-5.000 -0.3362 0.01546 0.00981 -0.1222 0.8749 0.2271
-4.750 -0.2897 0.01510 0.00941 -0.1261 0.8664 0.2285
-4.500 -0.2456 0.01475 0.00900 -0.1295 0.8547 0.2298
-4.250 -0.2079 0.01447 0.00864 -0.1316 0.8402 0.2309
-4.000 -0.1721 0.01425 0.00831 -0.1334 0.8245 0.2318
-3.500 -0.1128 0.01371 0.00762 -0.1344 0.7917 0.2340
-3.250 -0.0852 0.01347 0.00736 -0.1345 0.7766 0.2355
-3.000 -0.0570 0.01334 0.00717 -0.1346 0.7616 0.2367
-2.750 -0.0302 0.01321 0.00701 -0.1345 0.7465 0.2379
-2.500 -0.0028 0.01312 0.00687 -0.1344 0.7326 0.2392
-2.250 0.0247 0.01304 0.00674 -0.1344 0.7188 0.2405
-2.000 0.0521 0.01295 0.00662 -0.1343 0.7063 0.2420
-1.500 0.1076 0.01283 0.00638 -0.1341 0.6816 0.2449
-1.250 0.1355 0.01281 0.00626 -0.1340 0.6693 0.2460
-1.000 0.1630 0.01267 0.00610 -0.1339 0.6575 0.2473
-0.750 0.1904 0.01251 0.00592 -0.1338 0.6460 0.2495
-0.500 0.2185 0.01239 0.00584 -0.1338 0.6355 0.2513
-0.250 0.2464 0.01237 0.00578 -0.1337 0.6247 0.2531
0.000 0.2748 0.01232 0.00573 -0.1337 0.6147 0.2549
0.250 0.3027 0.01231 0.00568 -0.1335 0.6040 0.2568
0.500 0.3311 0.01230 0.00564 -0.1334 0.5941 0.2587
0.750 0.3594 0.01230 0.00561 -0.1333 0.5842 0.2605
1.000 0.3877 0.01230 0.00555 -0.1332 0.5750 0.2627
1.250 0.4164 0.01217 0.00549 -0.1333 0.5658 0.2658
1.500 0.4444 0.01219 0.00550 -0.1331 0.5563 0.2683
1.750 0.4731 0.01220 0.00552 -0.1330 0.5479 0.2708
2.000 0.5014 0.01222 0.00553 -0.1328 0.5391 0.2734
2.250 0.5292 0.01232 0.00556 -0.1326 0.5298 0.2759
2.500 0.5573 0.01229 0.00555 -0.1323 0.5205 0.2784
2.750 0.5847 0.01229 0.00555 -0.1321 0.5106 0.2821
3.000 0.6128 0.01230 0.00560 -0.1318 0.5016 0.2853
3.250 0.6399 0.01236 0.00565 -0.1314 0.4919 0.2886
3.500 0.6670 0.01247 0.00572 -0.1310 0.4831 0.2917
3.750 0.6946 0.01251 0.00577 -0.1306 0.4744 0.2945
4.000 0.7214 0.01256 0.00583 -0.1302 0.4652 0.2992
4.250 0.7489 0.01260 0.00592 -0.1298 0.4566 0.3033
4.500 0.7751 0.01270 0.00601 -0.1291 0.4474 0.3071
4.750 0.8012 0.01284 0.00612 -0.1284 0.4392 0.3104
5.000 0.8281 0.01286 0.00619 -0.1280 0.4306 0.3146
5.250 0.8524 0.01299 0.00631 -0.1270 0.4217 0.3189
5.500 0.8783 0.01306 0.00644 -0.1263 0.4135 0.3231
5.750 0.9020 0.01320 0.00655 -0.1252 0.4041 0.3270
6.000 0.9257 0.01336 0.00670 -0.1240 0.3953 0.3301
6.250 0.9504 0.01343 0.00682 -0.1232 0.3852 0.3356
6.500 0.9734 0.01361 0.00702 -0.1220 0.3752 0.3402
6.750 0.9967 0.01380 0.00720 -0.1208 0.3636 0.3447
7.000 1.0193 0.01404 0.00742 -0.1195 0.3516 0.3487
7.250 1.0404 0.01431 0.00766 -0.1181 0.3374 0.3538
7.500 1.0621 0.01458 0.00793 -0.1168 0.3211 0.3587
7.750 1.0819 0.01494 0.00825 -0.1151 0.3022 0.3634
8.000 1.0992 0.01542 0.00861 -0.1132 0.2791 0.3675
8.250 1.1148 0.01599 0.00905 -0.1110 0.2523 0.3715
8.500 1.1282 0.01668 0.00963 -0.1087 0.2270 0.3767
8.750 1.1429 0.01734 0.01021 -0.1065 0.2055 0.3817
9.000 1.1568 0.01804 0.01082 -0.1043 0.1871 0.3865
9.250 1.1706 0.01875 0.01144 -0.1020 0.1716 0.3906
9.500 1.1854 0.01942 0.01209 -0.1001 0.1578 0.3963
9.750 1.1991 0.02015 0.01280 -0.0980 0.1459 0.4018
10.000 1.2125 0.02092 0.01353 -0.0959 0.1355 0.4071
10.250 1.2245 0.02177 0.01433 -0.0937 0.1261 0.4117
10.500 1.2379 0.02257 0.01512 -0.0919 0.1176 0.4175
10.750 1.2510 0.02340 0.01600 -0.0900 0.1103 0.4234
11.000 1.2623 0.02437 0.01695 -0.0880 0.1038 0.4292
11.250 1.2732 0.02539 0.01796 -0.0861 0.0977 0.4342
11.500 1.2849 0.02640 0.01900 -0.0844 0.0923 0.4399
11.750 1.2938 0.02764 0.02026 -0.0826 0.0874 0.4460
12.000 1.3056 0.02873 0.02140 -0.0811 0.0828 0.4523
12.250 1.3133 0.03014 0.02281 -0.0794 0.0789 0.4577
12.500 1.3238 0.03144 0.02415 -0.0781 0.0749 0.4639
12.750 1.3312 0.03301 0.02578 -0.0767 0.0714 0.4701
13.000 1.3405 0.03450 0.02731 -0.0756 0.0679 0.4768
13.250 1.3458 0.03637 0.02919 -0.0743 0.0649 0.4824
13.500 1.3549 0.03802 0.03093 -0.0735 0.0618 0.4895
13.750 1.3589 0.04018 0.03312 -0.0726 0.0590 0.4960
14.000 1.3674 0.04200 0.03501 -0.0718 0.0562 0.5030
14.250 1.3710 0.04434 0.03738 -0.0712 0.0538 0.5088
14.500 1.3769 0.04657 0.03971 -0.0708 0.0514 0.5164
14.750 1.3809 0.04904 0.04223 -0.0704 0.0491 0.5239
15.000 1.3834 0.05174 0.04497 -0.0701 0.0471 0.5307
15.250 1.3878 0.05435 0.04768 -0.0701 0.0450 0.5385
15.500 1.3881 0.05748 0.05087 -0.0702 0.0433 0.5459
15.750 1.3909 0.06039 0.05385 -0.0703 0.0415 0.5534
16.000 1.3933 0.06346 0.05701 -0.0707 0.0398 0.5615
16.250 1.3912 0.06717 0.06079 -0.0713 0.0385 0.5695
16.500 1.3926 0.07050 0.06420 -0.0718 0.0371 0.5780
16.750 1.3941 0.07392 0.06774 -0.0725 0.0357 0.5871
17.000 1.3920 0.07789 0.07178 -0.0735 0.0346 0.5960
17.250 1.3886 0.08213 0.07610 -0.0747 0.0336 0.6042
17.500 1.3903 0.08572 0.07981 -0.0757 0.0325 0.6149
17.750 1.3896 0.08971 0.08389 -0.0769 0.0315 0.6251
18.000 1.3865 0.09411 0.08839 -0.0785 0.0307 0.6359
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