NREL's S823 Airfoil (s823-nr) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: NREL's S823 Airfoil (s823-nr) Reynolds number: 500,000 Max Cl/Cd: 77.45 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s823-nr-500000-n5.txt Download as CSV file: xf-s823-nr-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NREL's S823 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
------ -------- --------- --------- -------- -------- --------
-17.750 -0.7626 0.12992 0.12590 -0.0407 1.0000 0.0986
-17.500 -0.8073 0.11959 0.11539 -0.0450 1.0000 0.0985
-17.250 -0.8266 0.11345 0.10914 -0.0475 1.0000 0.0993
-17.000 -0.8424 0.10797 0.10357 -0.0497 1.0000 0.1004
-16.750 -0.8520 0.10347 0.09897 -0.0514 1.0000 0.1016
-16.500 -0.8614 0.09908 0.09450 -0.0531 1.0000 0.1023
-16.250 -0.8671 0.09525 0.09059 -0.0545 1.0000 0.1031
-16.000 -0.8743 0.09125 0.08650 -0.0560 1.0000 0.1037
-15.750 -0.8797 0.08765 0.08288 -0.0573 1.0000 0.1052
-15.500 -0.8853 0.08406 0.07925 -0.0585 1.0000 0.1060
-15.250 -0.8931 0.08023 0.07540 -0.0599 1.0000 0.1075
-15.000 -0.8989 0.07670 0.07184 -0.0610 1.0000 0.1084
-14.750 -0.9036 0.07340 0.06850 -0.0620 1.0000 0.1094
-14.500 -0.9075 0.07028 0.06533 -0.0629 1.0000 0.1103
-14.250 -0.9120 0.06714 0.06214 -0.0637 1.0000 0.1113
-14.000 -0.9145 0.06429 0.05925 -0.0644 1.0000 0.1123
-13.750 -0.9175 0.06148 0.05638 -0.0649 1.0000 0.1130
-13.500 -0.9195 0.05887 0.05372 -0.0653 1.0000 0.1138
-13.250 -0.9223 0.05624 0.05102 -0.0656 1.0000 0.1145
-13.000 -0.9249 0.05374 0.04847 -0.0658 1.0000 0.1150
-12.750 -0.9269 0.05140 0.04608 -0.0658 1.0000 0.1154
-12.500 -0.9227 0.04890 0.04354 -0.0673 0.9993 0.1164
-12.250 -0.9100 0.04619 0.04080 -0.0707 0.9973 0.1175
-12.000 -0.8974 0.04346 0.03804 -0.0743 0.9948 0.1186
-11.750 -0.8839 0.04073 0.03526 -0.0781 0.9923 0.1197
-11.500 -0.8728 0.03825 0.03274 -0.0807 0.9885 0.1205
-11.250 -0.8578 0.03591 0.03036 -0.0839 0.9844 0.1214
-10.750 -0.8299 0.03179 0.02615 -0.0886 0.9727 0.1224
-10.500 -0.8182 0.02990 0.02421 -0.0901 0.9636 0.1229
-10.250 -0.8056 0.02807 0.02233 -0.0917 0.9529 0.1235
-10.000 -0.7912 0.02634 0.02055 -0.0932 0.9419 0.1240
-9.750 -0.7691 0.02472 0.01887 -0.0960 0.9334 0.1246
-9.500 -0.7385 0.02321 0.01729 -0.1000 0.9265 0.1254
-9.250 -0.7031 0.02186 0.01588 -0.1046 0.9190 0.1261
-9.000 -0.6609 0.02065 0.01460 -0.1101 0.9115 0.1268
-8.750 -0.6221 0.01955 0.01341 -0.1149 0.9007 0.1275
-8.500 -0.5876 0.01859 0.01235 -0.1186 0.8874 0.1281
-8.250 -0.5629 0.01747 0.01113 -0.1212 0.8707 0.1294
-8.000 -0.5413 0.01664 0.01019 -0.1225 0.8553 0.1308
-7.500 -0.4976 0.01565 0.00906 -0.1228 0.8284 0.1334
-7.250 -0.4749 0.01525 0.00861 -0.1228 0.8169 0.1349
-7.000 -0.4512 0.01492 0.00822 -0.1228 0.8059 0.1364
-6.750 -0.4271 0.01462 0.00786 -0.1228 0.7950 0.1379
-6.500 -0.4023 0.01435 0.00754 -0.1228 0.7851 0.1393
-6.250 -0.3770 0.01412 0.00724 -0.1228 0.7752 0.1407
-6.000 -0.3516 0.01386 0.00695 -0.1228 0.7661 0.1425
-5.750 -0.3262 0.01359 0.00664 -0.1228 0.7571 0.1452
-5.500 -0.3001 0.01333 0.00638 -0.1229 0.7477 0.1477
-5.250 -0.2738 0.01313 0.00613 -0.1230 0.7391 0.1504
-5.000 -0.2468 0.01294 0.00592 -0.1231 0.7307 0.1530
-4.750 -0.2197 0.01280 0.00573 -0.1231 0.7228 0.1551
-4.500 -0.1926 0.01257 0.00551 -0.1233 0.7143 0.1586
-4.250 -0.1655 0.01240 0.00531 -0.1234 0.7061 0.1621
-4.000 -0.1378 0.01223 0.00514 -0.1235 0.6980 0.1657
-3.750 -0.1101 0.01213 0.00500 -0.1236 0.6906 0.1689
-3.500 -0.0821 0.01194 0.00483 -0.1238 0.6831 0.1731
-3.250 -0.0544 0.01181 0.00469 -0.1239 0.6751 0.1774
-3.000 -0.0261 0.01169 0.00456 -0.1241 0.6678 0.1815
-2.750 0.0021 0.01160 0.00445 -0.1242 0.6602 0.1848
-2.500 0.0303 0.01147 0.00433 -0.1244 0.6533 0.1891
-2.250 0.0588 0.01137 0.00423 -0.1245 0.6457 0.1935
-2.000 0.0869 0.01131 0.00415 -0.1246 0.6387 0.1973
-1.750 0.1157 0.01122 0.00407 -0.1247 0.6315 0.2012
-1.500 0.1440 0.01114 0.00399 -0.1248 0.6244 0.2059
-1.250 0.1728 0.01107 0.00393 -0.1250 0.6176 0.2105
-1.000 0.2013 0.01103 0.00388 -0.1250 0.6105 0.2144
-0.750 0.2298 0.01096 0.00383 -0.1251 0.6040 0.2194
-0.500 0.2587 0.01091 0.00380 -0.1253 0.5971 0.2244
-0.250 0.2870 0.01090 0.00377 -0.1253 0.5905 0.2289
0.000 0.3159 0.01084 0.00375 -0.1254 0.5840 0.2337
0.250 0.3445 0.01081 0.00374 -0.1254 0.5772 0.2391
0.500 0.3729 0.01082 0.00373 -0.1254 0.5710 0.2441
0.750 0.4018 0.01078 0.00374 -0.1255 0.5645 0.2497
1.000 0.4301 0.01078 0.00375 -0.1255 0.5580 0.2562
1.250 0.4588 0.01078 0.00377 -0.1255 0.5521 0.2629
1.500 0.4875 0.01075 0.00380 -0.1256 0.5455 0.2711
1.750 0.5155 0.01080 0.00384 -0.1254 0.5396 0.2780
2.000 0.5444 0.01078 0.00389 -0.1255 0.5334 0.2857
2.250 0.5726 0.01081 0.00394 -0.1254 0.5270 0.2925
2.500 0.6006 0.01085 0.00400 -0.1252 0.5207 0.2984
2.750 0.6288 0.01087 0.00406 -0.1251 0.5132 0.3044
3.250 0.6838 0.01098 0.00421 -0.1246 0.4966 0.3167
3.500 0.7105 0.01107 0.00429 -0.1242 0.4885 0.3236
3.750 0.7382 0.01112 0.00439 -0.1239 0.4798 0.3296
4.000 0.7646 0.01122 0.00449 -0.1235 0.4710 0.3360
4.250 0.7914 0.01131 0.00459 -0.1230 0.4610 0.3423
4.500 0.8177 0.01141 0.00472 -0.1226 0.4514 0.3496
4.750 0.8433 0.01154 0.00485 -0.1219 0.4409 0.3568
5.000 0.8694 0.01165 0.00499 -0.1214 0.4297 0.3632
5.250 0.8943 0.01180 0.00515 -0.1206 0.4176 0.3709
5.500 0.9182 0.01199 0.00532 -0.1197 0.4036 0.3778
5.750 0.9414 0.01219 0.00552 -0.1186 0.3873 0.3849
6.000 0.9635 0.01244 0.00572 -0.1174 0.3697 0.3919
6.250 0.9840 0.01272 0.00597 -0.1159 0.3494 0.3992
6.500 1.0017 0.01307 0.00624 -0.1139 0.3275 0.4064
6.750 1.0181 0.01346 0.00656 -0.1117 0.3046 0.4126
7.000 1.0337 0.01393 0.00694 -0.1095 0.2796 0.4200
7.250 1.0486 0.01447 0.00738 -0.1072 0.2539 0.4270
7.500 1.0620 0.01509 0.00789 -0.1047 0.2284 0.4341
7.750 1.0760 0.01571 0.00841 -0.1024 0.2048 0.4411
8.000 1.0896 0.01633 0.00897 -0.1001 0.1844 0.4482
8.250 1.1035 0.01696 0.00954 -0.0979 0.1673 0.4560
8.500 1.1164 0.01763 0.01015 -0.0956 0.1504 0.4633
8.750 1.1286 0.01835 0.01081 -0.0933 0.1337 0.4708
9.000 1.1405 0.01910 0.01152 -0.0910 0.1193 0.4783
9.250 1.1520 0.01989 0.01228 -0.0888 0.1067 0.4868
9.500 1.1638 0.02069 0.01306 -0.0867 0.0957 0.4946
9.750 1.1763 0.02149 0.01386 -0.0848 0.0870 0.5030
10.000 1.1873 0.02240 0.01477 -0.0828 0.0789 0.5112
10.250 1.1980 0.02336 0.01574 -0.0809 0.0710 0.5202
10.500 1.2095 0.02432 0.01672 -0.0791 0.0651 0.5287
10.750 1.2191 0.02544 0.01785 -0.0773 0.0589 0.5376
11.000 1.2300 0.02652 0.01897 -0.0757 0.0536 0.5468
11.250 1.2392 0.02776 0.02023 -0.0741 0.0488 0.5567
11.500 1.2490 0.02901 0.02152 -0.0727 0.0444 0.5660
11.750 1.2576 0.03039 0.02293 -0.0712 0.0406 0.5763
12.000 1.2669 0.03177 0.02437 -0.0700 0.0373 0.5865
12.250 1.2749 0.03331 0.02595 -0.0687 0.0343 0.5972
12.500 1.2838 0.03483 0.02753 -0.0677 0.0316 0.6087
12.750 1.2905 0.03657 0.02932 -0.0666 0.0290 0.6198
13.000 1.2992 0.03819 0.03102 -0.0657 0.0271 0.6320
13.250 1.3063 0.04003 0.03291 -0.0648 0.0251 0.6449
13.500 1.3130 0.04194 0.03490 -0.0641 0.0234 0.6581
13.750 1.3200 0.04388 0.03693 -0.0634 0.0218 0.6729
14.000 1.3258 0.04600 0.03913 -0.0628 0.0204 0.6881
14.250 1.3318 0.04816 0.04139 -0.0624 0.0192 0.7049
14.500 1.3379 0.05034 0.04368 -0.0620 0.0181 0.7242
15.000 1.3467 0.05521 0.04878 -0.0614 0.0162 0.7709
15.250 1.3513 0.05760 0.05134 -0.0611 0.0155 0.8068
15.500 1.3506 0.05973 0.05374 -0.0597 0.0148 0.9255
15.750 1.3533 0.06245 0.05652 -0.0598 0.0141 1.0000
16.000 1.3559 0.06544 0.05957 -0.0600 0.0135 1.0000
16.250 1.3585 0.06854 0.06272 -0.0604 0.0129 1.0000
16.500 1.3616 0.07160 0.06585 -0.0609 0.0124 1.0000
16.750 1.3642 0.07481 0.06912 -0.0615 0.0119 1.0000
17.000 1.3657 0.07819 0.07256 -0.0621 0.0114 1.0000
17.250 1.3662 0.08179 0.07623 -0.0630 0.0110 1.0000
17.500 1.3658 0.08559 0.08009 -0.0640 0.0106 1.0000
17.750 1.3659 0.08936 0.08393 -0.0650 0.0103 1.0000
18.000 1.3664 0.09312 0.08777 -0.0661 0.0100 1.0000
18.250 1.3656 0.09713 0.09187 -0.0675 0.0097 1.0000
18.500 1.3645 0.10125 0.09606 -0.0689 0.0094 1.0000
18.750 1.3631 0.10544 0.10033 -0.0704 0.0091 1.0000
19.000 1.3608 0.10983 0.10480 -0.0722 0.0089 1.0000
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