NREL's S804 Airfoil (s804-nr) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: NREL's S804 Airfoil (s804-nr) Reynolds number: 100,000 Max Cl/Cd: 45.18 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s804-nr-100000-n5.txt Download as CSV file: xf-s804-nr-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NREL's S804 Airfoil
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.4794 0.06794 0.06228 -0.0746 1.0000 0.0365
-11.000 -0.5113 0.06249 0.05672 -0.0770 1.0000 0.0365
-10.750 -0.5374 0.05860 0.05276 -0.0774 1.0000 0.0364
-10.500 -0.5639 0.05572 0.04984 -0.0763 1.0000 0.0363
-10.250 -0.5802 0.05053 0.04428 -0.0824 0.9872 0.0366
-10.000 -0.5582 0.04754 0.04122 -0.0872 0.9734 0.0373
-9.750 -0.5388 0.04456 0.03806 -0.0911 0.9565 0.0379
-9.500 -0.5219 0.04163 0.03489 -0.0939 0.9381 0.0386
-9.250 -0.4999 0.03875 0.03169 -0.0967 0.9229 0.0395
-9.000 -0.4724 0.03599 0.02855 -0.0996 0.9097 0.0405
-8.750 -0.4399 0.03387 0.02619 -0.1026 0.8964 0.0421
-8.500 -0.4066 0.03238 0.02462 -0.1049 0.8804 0.0438
-8.250 -0.3728 0.03066 0.02261 -0.1072 0.8638 0.0458
-8.000 -0.3362 0.02912 0.02091 -0.1095 0.8475 0.0474
-7.750 -0.2996 0.02789 0.01958 -0.1118 0.8305 0.0493
-7.500 -0.2659 0.02678 0.01821 -0.1134 0.8124 0.0522
-7.250 -0.2361 0.02588 0.01729 -0.1144 0.7934 0.0545
-7.000 -0.2080 0.02506 0.01632 -0.1148 0.7750 0.0573
-6.750 -0.1811 0.02428 0.01545 -0.1150 0.7578 0.0600
-6.250 -0.1300 0.02296 0.01395 -0.1152 0.7248 0.0680
-6.000 -0.1047 0.02236 0.01323 -0.1152 0.7097 0.0732
-5.750 -0.0790 0.02173 0.01255 -0.1154 0.6958 0.0803
-5.500 -0.0534 0.02111 0.01188 -0.1156 0.6819 0.0904
-5.250 -0.0277 0.02045 0.01124 -0.1159 0.6686 0.1050
-5.000 -0.0006 0.01981 0.01061 -0.1165 0.6568 0.1297
-4.750 0.0261 0.01913 0.01005 -0.1172 0.6441 0.1672
-4.500 0.0539 0.01847 0.00953 -0.1181 0.6330 0.2197
-4.250 0.0817 0.01787 0.00921 -0.1189 0.6216 0.2916
-4.000 0.1092 0.01773 0.00936 -0.1190 0.6114 0.3722
-3.750 0.1370 0.01791 0.00954 -0.1187 0.6012 0.4219
-3.500 0.1658 0.01809 0.00955 -0.1187 0.5917 0.4526
-3.250 0.1935 0.01830 0.00964 -0.1184 0.5819 0.4736
-3.000 0.2216 0.01852 0.00967 -0.1181 0.5733 0.4920
-2.750 0.2476 0.01876 0.00988 -0.1173 0.5641 0.5053
-2.500 0.2753 0.01895 0.00990 -0.1170 0.5566 0.5185
-2.250 0.3027 0.01912 0.00997 -0.1167 0.5486 0.5309
-2.000 0.3293 0.01928 0.01005 -0.1161 0.5413 0.5406
-1.750 0.3572 0.01944 0.01004 -0.1159 0.5351 0.5509
-1.500 0.3843 0.01954 0.01009 -0.1157 0.5276 0.5597
-1.250 0.4109 0.01968 0.01015 -0.1151 0.5209 0.5673
-1.000 0.4406 0.01977 0.01002 -0.1156 0.5151 0.5766
-0.750 0.4664 0.01988 0.01015 -0.1150 0.5084 0.5820
-0.500 0.4934 0.01999 0.01019 -0.1147 0.5024 0.5882
-0.250 0.5226 0.02009 0.01012 -0.1151 0.4976 0.5953
0.000 0.5505 0.02020 0.01017 -0.1151 0.4925 0.6008
0.250 0.5771 0.02033 0.01029 -0.1148 0.4872 0.6055
0.500 0.6049 0.02046 0.01035 -0.1148 0.4825 0.6110
0.750 0.6343 0.02059 0.01033 -0.1153 0.4783 0.6172
1.000 0.6618 0.02074 0.01045 -0.1152 0.4740 0.6218
1.250 0.6878 0.02090 0.01063 -0.1149 0.4690 0.6262
1.500 0.7151 0.02107 0.01077 -0.1149 0.4645 0.6318
1.750 0.7439 0.02124 0.01084 -0.1152 0.4607 0.6381
2.000 0.7721 0.02144 0.01095 -0.1153 0.4577 0.6428
2.250 0.7978 0.02167 0.01125 -0.1150 0.4539 0.6475
2.500 0.8245 0.02193 0.01153 -0.1149 0.4501 0.6535
2.750 0.8526 0.02219 0.01176 -0.1152 0.4466 0.6604
3.000 0.8787 0.02241 0.01200 -0.1148 0.4434 0.6655
3.250 0.9061 0.02265 0.01220 -0.1148 0.4405 0.6715
3.500 0.9344 0.02293 0.01244 -0.1151 0.4377 0.6782
3.750 0.9586 0.02327 0.01288 -0.1146 0.4341 0.6843
4.000 0.9834 0.02360 0.01330 -0.1142 0.4308 0.6912
4.250 1.0100 0.02396 0.01368 -0.1142 0.4279 0.6995
4.500 1.0355 0.02428 0.01404 -0.1139 0.4253 0.7063
4.750 1.0622 0.02461 0.01437 -0.1138 0.4230 0.7143
5.000 1.0900 0.02494 0.01469 -0.1140 0.4208 0.7225
5.250 1.1143 0.02535 0.01517 -0.1135 0.4183 0.7310
5.500 1.1363 0.02585 0.01582 -0.1129 0.4151 0.7411
5.750 1.1578 0.02631 0.01642 -0.1120 0.4121 0.7508
6.000 1.1811 0.02678 0.01698 -0.1115 0.4095 0.7620
6.250 1.2045 0.02722 0.01749 -0.1109 0.4072 0.7736
6.500 1.2287 0.02761 0.01795 -0.1104 0.4051 0.7858
6.750 1.2539 0.02797 0.01834 -0.1101 0.4030 0.8001
7.000 1.2794 0.02832 0.01871 -0.1098 0.4010 0.8161
7.250 1.2917 0.02903 0.01968 -0.1076 0.3981 0.8344
7.500 1.3050 0.02968 0.02055 -0.1055 0.3954 0.8587
7.750 1.3202 0.03026 0.02130 -0.1038 0.3926 0.8951
8.000 1.3378 0.03068 0.02185 -0.1024 0.3899 1.0000
8.250 1.3639 0.03127 0.02246 -0.1027 0.3874 1.0000
8.500 1.3923 0.03176 0.02292 -0.1033 0.3852 1.0000
8.750 1.4236 0.03218 0.02329 -0.1041 0.3832 1.0000
9.000 1.4288 0.03353 0.02489 -0.1018 0.3796 1.0000
9.250 1.4362 0.03478 0.02631 -0.0997 0.3761 1.0000
9.500 1.4490 0.03573 0.02736 -0.0982 0.3728 1.0000
9.750 1.4684 0.03635 0.02803 -0.0974 0.3698 1.0000
10.000 1.4973 0.03660 0.02826 -0.0977 0.3672 1.0000
10.250 1.5242 0.03698 0.02864 -0.0978 0.3645 1.0000
10.500 1.4927 0.03949 0.03145 -0.0913 0.3601 1.0000
10.750 1.4793 0.04156 0.03368 -0.0875 0.3559 1.0000
11.000 1.4910 0.04243 0.03461 -0.0862 0.3524 1.0000
11.250 1.5286 0.04191 0.03406 -0.0869 0.3495 1.0000
11.500 1.5279 0.04354 0.03580 -0.0847 0.3459 1.0000
11.750 1.2773 0.06992 0.06274 -0.0805 0.3273 1.0000
12.000 1.3351 0.06551 0.05833 -0.0791 0.3282 1.0000
12.250 1.4086 0.05969 0.05249 -0.0779 0.3289 1.0000
12.500 1.3094 0.07487 0.06785 -0.0803 0.3148 1.0000
12.750 1.3525 0.07208 0.06509 -0.0791 0.3141 1.0000
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Polar data table (+)
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