NREL's S827 Airfoil (s827-nr) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: NREL's S827 Airfoil (s827-nr) Reynolds number: 500,000 Max Cl/Cd: 81.34 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s827-nr-500000-n5.txt Download as CSV file: xf-s827-nr-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NREL's S827 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
------ -------- --------- --------- -------- -------- --------
-14.000 -0.2628 0.08960 0.08618 -0.1335 0.8082 0.0037
-13.750 -0.2850 0.08275 0.07926 -0.1360 0.8057 0.0037
-13.500 -0.3045 0.07737 0.07379 -0.1374 0.8034 0.0036
-13.250 -0.3298 0.07181 0.06813 -0.1379 0.8008 0.0036
-13.000 -0.3478 0.06762 0.06384 -0.1379 0.7980 0.0036
-12.750 -0.3676 0.06342 0.05951 -0.1372 0.7951 0.0035
-12.500 -0.3833 0.05986 0.05581 -0.1361 0.7925 0.0035
-12.000 -0.4169 0.05215 0.04778 -0.1325 0.7878 0.0034
-11.750 -0.4285 0.04841 0.04385 -0.1303 0.7855 0.0033
-11.500 -0.4376 0.04386 0.03903 -0.1278 0.7833 0.0032
-11.250 -0.4235 0.03424 0.02843 -0.1248 0.7823 0.0029
-11.000 -0.3952 0.03248 0.02633 -0.1246 0.7808 0.0029
-10.750 -0.3636 0.03149 0.02505 -0.1244 0.7794 0.0029
-10.500 -0.3374 0.03099 0.02435 -0.1239 0.7779 0.0030
-10.250 -0.3143 0.03060 0.02384 -0.1235 0.7764 0.0029
-10.000 -0.2920 0.03028 0.02342 -0.1228 0.7749 0.0030
-9.750 -0.2719 0.02993 0.02299 -0.1221 0.7734 0.0031
-9.500 -0.2533 0.02952 0.02253 -0.1214 0.7718 0.0030
-9.250 -0.2365 0.02908 0.02203 -0.1204 0.7702 0.0032
-9.000 -0.2207 0.02858 0.02149 -0.1194 0.7686 0.0034
-8.750 -0.2062 0.02801 0.02087 -0.1183 0.7671 0.0037
-8.500 -0.1916 0.02743 0.02023 -0.1174 0.7656 0.0039
-8.250 -0.1781 0.02681 0.01956 -0.1164 0.7643 0.0039
-8.000 -0.1649 0.02617 0.01887 -0.1154 0.7629 0.0040
-7.750 -0.1553 0.02538 0.01805 -0.1139 0.7617 0.0047
-7.500 -0.1424 0.02472 0.01736 -0.1129 0.7604 0.0045
-7.250 -0.1327 0.02393 0.01656 -0.1115 0.7589 0.0057
-7.000 -0.1240 0.02309 0.01571 -0.1100 0.7573 0.0070
-6.750 -0.1157 0.02222 0.01482 -0.1084 0.7558 0.0086
-6.500 -0.1089 0.02129 0.01390 -0.1067 0.7544 0.0138
-6.250 -0.1018 0.02036 0.01298 -0.1050 0.7531 0.0179
-6.000 -0.0968 0.01934 0.01199 -0.1030 0.7518 0.0264
-5.750 -0.0931 0.01827 0.01094 -0.1009 0.7506 0.0377
-5.500 -0.0920 0.01709 0.00980 -0.0984 0.7493 0.0545
-5.250 -0.0913 0.01593 0.00866 -0.0959 0.7482 0.0752
-5.000 -0.0955 0.01467 0.00749 -0.0925 0.7469 0.1032
-4.750 -0.1064 0.01370 0.00658 -0.0874 0.7455 0.1305
-4.500 -0.1142 0.01286 0.00588 -0.0825 0.7441 0.1829
-4.250 -0.1374 0.01083 0.00439 -0.0754 0.7424 0.3699
-4.000 -0.1270 0.01005 0.00405 -0.0734 0.7413 0.5045
-3.750 -0.1002 0.01008 0.00405 -0.0737 0.7404 0.5222
-3.500 -0.0729 0.01016 0.00409 -0.0741 0.7394 0.5344
-3.250 -0.0450 0.01022 0.00405 -0.0746 0.7386 0.5410
-3.000 -0.0171 0.01027 0.00410 -0.0751 0.7378 0.5464
-2.750 0.0109 0.01042 0.00419 -0.0756 0.7371 0.5539
-2.500 0.0392 0.01044 0.00412 -0.0762 0.7365 0.5555
-2.250 0.0677 0.01041 0.00404 -0.0769 0.7358 0.5560
-2.000 0.0963 0.01038 0.00398 -0.0776 0.7352 0.5565
-1.750 0.1250 0.01036 0.00393 -0.0783 0.7346 0.5571
-1.500 0.1539 0.01035 0.00390 -0.0791 0.7341 0.5577
-1.250 0.1824 0.01036 0.00389 -0.0798 0.7335 0.5584
-1.000 0.2098 0.01036 0.00389 -0.0803 0.7328 0.5590
-0.750 0.2372 0.01037 0.00391 -0.0808 0.7322 0.5597
-0.500 0.2646 0.01039 0.00394 -0.0812 0.7315 0.5604
-0.250 0.2919 0.01042 0.00397 -0.0817 0.7307 0.5611
0.000 0.3192 0.01044 0.00401 -0.0821 0.7298 0.5619
0.250 0.3465 0.01046 0.00405 -0.0826 0.7289 0.5627
0.500 0.3739 0.01050 0.00410 -0.0831 0.7281 0.5636
0.750 0.4014 0.01054 0.00415 -0.0836 0.7274 0.5646
1.000 0.4289 0.01058 0.00422 -0.0841 0.7267 0.5657
1.250 0.4565 0.01063 0.00429 -0.0846 0.7260 0.5667
1.500 0.4842 0.01068 0.00436 -0.0851 0.7253 0.5677
1.750 0.5119 0.01074 0.00443 -0.0857 0.7246 0.5686
2.000 0.5397 0.01079 0.00452 -0.0863 0.7239 0.5694
2.250 0.5678 0.01083 0.00459 -0.0869 0.7231 0.5702
2.500 0.5959 0.01087 0.00468 -0.0875 0.7223 0.5712
2.750 0.6241 0.01092 0.00479 -0.0881 0.7217 0.5722
3.000 0.6525 0.01098 0.00491 -0.0888 0.7211 0.5731
3.250 0.6813 0.01104 0.00502 -0.0896 0.7204 0.5742
3.500 0.7103 0.01111 0.00515 -0.0904 0.7195 0.5752
3.750 0.7317 0.01121 0.00536 -0.0896 0.7178 0.5763
4.000 0.7542 0.01131 0.00555 -0.0891 0.7161 0.5775
4.250 0.7775 0.01140 0.00572 -0.0887 0.7142 0.5787
4.500 0.8058 0.01113 0.00548 -0.0891 0.7085 0.5799
4.750 0.8212 0.01083 0.00521 -0.0866 0.6977 0.5811
5.000 0.8341 0.01059 0.00499 -0.0837 0.6861 0.5825
5.250 0.8508 0.01046 0.00487 -0.0817 0.6775 0.5837
5.500 0.8530 0.01056 0.00507 -0.0769 0.6697 0.5849
5.750 0.8643 0.01065 0.00524 -0.0739 0.6603 0.5863
6.000 0.8711 0.01085 0.00551 -0.0702 0.6452 0.5876
6.250 0.8716 0.01113 0.00570 -0.0653 0.6071 0.5890
6.750 0.8321 0.01351 0.00752 -0.0492 0.5019 0.5915
7.000 0.8082 0.01532 0.00906 -0.0414 0.4485 0.5927
7.250 0.7949 0.01697 0.01049 -0.0358 0.4025 0.5940
7.500 0.7826 0.01872 0.01199 -0.0306 0.3506 0.5953
7.750 0.7744 0.02040 0.01340 -0.0262 0.2955 0.5967
8.000 0.7735 0.02181 0.01458 -0.0229 0.2482 0.5980
8.250 0.7775 0.02303 0.01561 -0.0205 0.2072 0.5993
8.500 0.7842 0.02413 0.01658 -0.0184 0.1697 0.6008
8.750 0.7920 0.02522 0.01752 -0.0165 0.1365 0.6024
9.000 0.8021 0.02620 0.01839 -0.0150 0.1092 0.6042
9.250 0.8136 0.02715 0.01925 -0.0137 0.0855 0.6060
9.500 0.8256 0.02809 0.02011 -0.0125 0.0671 0.6080
9.750 0.8386 0.02899 0.02097 -0.0114 0.0521 0.6103
10.000 0.8528 0.02984 0.02179 -0.0105 0.0420 0.6123
10.250 0.8668 0.03070 0.02266 -0.0096 0.0336 0.6143
10.500 0.8806 0.03160 0.02357 -0.0087 0.0274 0.6166
10.750 0.8957 0.03243 0.02445 -0.0080 0.0230 0.6190
11.000 0.9094 0.03338 0.02540 -0.0072 0.0185 0.6214
11.250 0.9244 0.03424 0.02631 -0.0065 0.0156 0.6238
11.500 0.9374 0.03526 0.02734 -0.0057 0.0130 0.6262
11.750 0.9521 0.03617 0.02831 -0.0051 0.0106 0.6285
12.000 0.9653 0.03720 0.02938 -0.0043 0.0086 0.6311
12.250 0.9793 0.03821 0.03048 -0.0037 0.0074 0.6340
12.500 0.9920 0.03932 0.03165 -0.0030 0.0065 0.6369
12.750 1.0047 0.04045 0.03284 -0.0023 0.0051 0.6398
13.000 1.0177 0.04157 0.03404 -0.0017 0.0048 0.6426
13.250 1.0289 0.04286 0.03541 -0.0010 0.0040 0.6456
13.500 1.0387 0.04431 0.03696 -0.0001 0.0034 0.6488
13.750 1.0523 0.04542 0.03814 0.0002 0.0029 0.6524
14.000 1.0635 0.04679 0.03959 0.0008 0.0026 0.6557
14.250 1.0718 0.04842 0.04132 0.0015 0.0023 0.6592
14.500 1.0810 0.05001 0.04303 0.0021 0.0021 0.6633
14.750 1.0894 0.05172 0.04486 0.0027 0.0021 0.6673
15.250 1.1054 0.05528 0.04868 0.0037 0.0018 0.6750
15.500 1.1124 0.05722 0.05074 0.0041 0.0018 0.6793
15.750 1.1186 0.05928 0.05293 0.0045 0.0017 0.6835
16.000 1.1253 0.06130 0.05507 0.0047 0.0015 0.6875
16.250 1.1300 0.06361 0.05752 0.0050 0.0015 0.6919
16.500 1.1338 0.06607 0.06010 0.0051 0.0014 0.6963
16.750 1.1376 0.06859 0.06276 0.0051 0.0013 0.7007
17.000 1.1373 0.07169 0.06601 0.0052 0.0013 0.7050
17.250 1.1389 0.07459 0.06906 0.0049 0.0012 0.7099
17.750 1.1342 0.08172 0.07653 0.0040 0.0013 0.7187
18.000 1.1323 0.08537 0.08033 0.0033 0.0012 0.7238
18.250 1.1199 0.09067 0.08581 0.0020 0.0011 0.7277
18.500 1.1145 0.09508 0.09038 0.0007 0.0011 0.7322
18.750 1.1059 0.10012 0.09560 -0.0011 0.0011 0.7368
19.000 1.1002 0.10489 0.10053 -0.0029 0.0010 0.7418
19.250 1.0876 0.11091 0.10674 -0.0055 0.0011 0.7458
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