NREL's S827 Airfoil (s827-nr) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: NREL's S827 Airfoil (s827-nr) Reynolds number: 200,000 Max Cl/Cd: 34.99 at α=8.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s827-nr-200000-n5.txt Download as CSV file: xf-s827-nr-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.750 -0.2389 0.09366 0.08936 -0.1346 0.8633 0.0083
-13.500 -0.2540 0.08774 0.08335 -0.1370 0.8602 0.0081
-13.250 -0.2745 0.08188 0.07741 -0.1387 0.8563 0.0080
-13.000 -0.2924 0.07713 0.07255 -0.1395 0.8526 0.0078
-12.750 -0.3114 0.07261 0.06790 -0.1396 0.8493 0.0077
-12.250 -0.3458 0.06470 0.05969 -0.1384 0.8428 0.0074
-12.000 -0.3633 0.06075 0.05556 -0.1369 0.8392 0.0073
-11.750 -0.3777 0.05690 0.05149 -0.1350 0.8360 0.0071
-11.500 -0.3955 0.04996 0.04406 -0.1317 0.8335 0.0066
-11.250 -0.4000 0.04666 0.04047 -0.1297 0.8306 0.0066
-11.000 -0.3920 0.04254 0.03586 -0.1279 0.8280 0.0063
-10.750 -0.3796 0.03985 0.03285 -0.1268 0.8255 0.0064
-10.500 -0.3568 0.03766 0.03030 -0.1264 0.8235 0.0065
-10.250 -0.3270 0.03607 0.02842 -0.1265 0.8219 0.0065
-10.000 -0.2950 0.03500 0.02711 -0.1266 0.8204 0.0067
-9.750 -0.2664 0.03431 0.02626 -0.1266 0.8190 0.0072
-9.500 -0.2330 0.03392 0.02570 -0.1266 0.8178 0.0073
-9.250 -0.2061 0.03368 0.02536 -0.1260 0.8159 0.0080
-9.000 -0.1832 0.03345 0.02502 -0.1253 0.8140 0.0088
-8.750 -0.1644 0.03307 0.02465 -0.1248 0.8121 0.0108
-8.500 -0.1454 0.03274 0.02427 -0.1240 0.8103 0.0123
-8.250 -0.1287 0.03233 0.02381 -0.1228 0.8086 0.0130
-8.000 -0.1157 0.03176 0.02320 -0.1214 0.8069 0.0140
-7.750 -0.1040 0.03110 0.02253 -0.1201 0.8054 0.0162
-7.500 -0.0906 0.03052 0.02187 -0.1190 0.8041 0.0183
-7.250 -0.0824 0.02982 0.02122 -0.1172 0.8022 0.0243
-7.000 -0.0765 0.02902 0.02046 -0.1153 0.8001 0.0317
-6.750 -0.0725 0.02815 0.01965 -0.1132 0.7979 0.0455
-6.500 -0.0706 0.02721 0.01879 -0.1108 0.7958 0.0629
-6.250 -0.0718 0.02609 0.01777 -0.1082 0.7940 0.0868
-6.000 -0.0784 0.02467 0.01644 -0.1051 0.7922 0.1165
-5.750 -0.0901 0.02296 0.01480 -0.1015 0.7905 0.1491
-5.500 -0.1097 0.02118 0.01312 -0.0967 0.7883 0.1862
-5.250 -0.1373 0.01962 0.01166 -0.0901 0.7852 0.2212
-5.000 -0.1691 0.01872 0.01080 -0.0817 0.7822 0.2526
-4.750 -0.2007 0.01732 0.00967 -0.0731 0.7795 0.3443
-4.500 -0.2017 0.01702 0.00991 -0.0688 0.7778 0.5162
-4.250 -0.1804 0.01723 0.00995 -0.0681 0.7768 0.5409
-4.000 -0.1552 0.01770 0.01032 -0.0678 0.7761 0.5563
-3.750 -0.1319 0.01844 0.01109 -0.0669 0.7747 0.5652
-3.500 -0.1195 0.01897 0.01159 -0.0643 0.7725 0.5723
-3.250 -0.0994 0.01986 0.01252 -0.0628 0.7707 0.5805
-3.000 -0.0860 0.01994 0.01245 -0.0609 0.7688 0.5848
-2.750 -0.0661 0.01997 0.01241 -0.0601 0.7673 0.5853
-2.500 -0.0437 0.01994 0.01229 -0.0597 0.7660 0.5857
-2.250 -0.0193 0.01988 0.01216 -0.0598 0.7649 0.5862
-2.000 0.0060 0.01983 0.01202 -0.0599 0.7640 0.5867
-1.750 0.0314 0.01981 0.01193 -0.0602 0.7632 0.5873
-1.500 0.0577 0.01979 0.01186 -0.0605 0.7625 0.5879
-1.250 0.0628 0.02024 0.01231 -0.0571 0.7600 0.5887
-0.250 0.0342 0.02373 0.01577 -0.0356 0.7408 0.5924
0.000 0.0552 0.02395 0.01595 -0.0352 0.7387 0.5934
0.250 0.0799 0.02407 0.01603 -0.0354 0.7374 0.5946
0.500 0.1069 0.02411 0.01602 -0.0359 0.7364 0.5958
0.750 0.1353 0.02409 0.01595 -0.0367 0.7356 0.5971
1.000 0.1642 0.02406 0.01588 -0.0375 0.7349 0.5983
1.250 0.1930 0.02407 0.01589 -0.0383 0.7343 0.5991
1.500 0.2209 0.02411 0.01595 -0.0389 0.7335 0.5999
2.000 0.2235 0.02619 0.01810 -0.0321 0.7217 0.6017
2.250 0.2526 0.02621 0.01814 -0.0329 0.7209 0.6027
2.500 0.2824 0.02618 0.01815 -0.0338 0.7202 0.6038
2.750 0.3129 0.02614 0.01813 -0.0348 0.7196 0.6049
3.250 0.3249 0.02783 0.01988 -0.0296 0.7077 0.6074
3.500 0.3555 0.02776 0.01986 -0.0306 0.7068 0.6087
3.750 0.3865 0.02768 0.01982 -0.0317 0.7060 0.6102
4.250 0.4075 0.02900 0.02121 -0.0279 0.6943 0.6130
4.500 0.4380 0.02888 0.02119 -0.0288 0.6931 0.6143
4.750 0.4698 0.02871 0.02112 -0.0299 0.6922 0.6157
5.250 0.4965 0.02971 0.02229 -0.0268 0.6801 0.6186
5.500 0.5293 0.02941 0.02209 -0.0279 0.6788 0.6202
5.750 0.5606 0.02912 0.02190 -0.0288 0.6769 0.6219
6.250 0.6017 0.02913 0.02210 -0.0275 0.6647 0.6255
8.250 0.8196 0.02357 0.01708 -0.0256 0.5113 0.6418
8.500 0.8307 0.02374 0.01663 -0.0228 0.4151 0.6437
8.750 0.8195 0.02554 0.01806 -0.0182 0.3507 0.6455
9.000 0.8123 0.02733 0.01956 -0.0144 0.2946 0.6475
9.250 0.8079 0.02910 0.02106 -0.0112 0.2401 0.6495
9.500 0.8086 0.03069 0.02240 -0.0088 0.1935 0.6518
9.750 0.8122 0.03218 0.02367 -0.0068 0.1518 0.6543
10.000 0.8193 0.03350 0.02485 -0.0052 0.1191 0.6566
10.250 0.8273 0.03478 0.02604 -0.0038 0.0920 0.6587
10.500 0.8367 0.03602 0.02724 -0.0025 0.0718 0.6610
10.750 0.8472 0.03722 0.02841 -0.0015 0.0574 0.6638
11.000 0.8579 0.03845 0.02962 -0.0005 0.0457 0.6667
11.250 0.8696 0.03965 0.03085 0.0004 0.0376 0.6697
11.500 0.8810 0.04086 0.03216 0.0013 0.0318 0.6725
11.750 0.8909 0.04222 0.03356 0.0023 0.0272 0.6753
12.000 0.9019 0.04352 0.03498 0.0032 0.0235 0.6787
12.250 0.9127 0.04489 0.03641 0.0039 0.0200 0.6825
12.500 0.9208 0.04651 0.03812 0.0049 0.0177 0.6859
12.750 0.9313 0.04793 0.03972 0.0057 0.0154 0.6892
13.000 0.9405 0.04948 0.04134 0.0064 0.0137 0.6929
13.250 0.9473 0.05134 0.04333 0.0073 0.0122 0.6968
13.500 0.9584 0.05281 0.04492 0.0078 0.0103 0.7007
13.750 0.9660 0.05462 0.04687 0.0084 0.0097 0.7043
14.000 0.9722 0.05663 0.04897 0.0090 0.0087 0.7083
14.250 0.9799 0.05856 0.05108 0.0096 0.0076 0.7128
14.500 0.9864 0.06062 0.05331 0.0101 0.0072 0.7167
14.750 0.9920 0.06281 0.05566 0.0106 0.0068 0.7210
15.000 0.9968 0.06515 0.05814 0.0109 0.0064 0.7258
15.250 0.9992 0.06780 0.06095 0.0112 0.0061 0.7302
15.500 1.0010 0.07058 0.06390 0.0115 0.0059 0.7346
15.750 1.0024 0.07359 0.06712 0.0117 0.0057 0.7395
16.000 1.0033 0.07675 0.07054 0.0118 0.0055 0.7444
16.250 1.0029 0.08010 0.07413 0.0117 0.0054 0.7493
16.500 0.9996 0.08398 0.07827 0.0114 0.0051 0.7545
16.750 0.9952 0.08805 0.08259 0.0109 0.0051 0.7596
17.000 0.9873 0.09276 0.08757 0.0099 0.0049 0.7646
17.250 0.9793 0.09764 0.09268 0.0086 0.0049 0.7702
17.500 0.9679 0.10322 0.09852 0.0069 0.0048 0.7750
17.750 0.9557 0.10910 0.10466 0.0046 0.0048 0.7804
18.000 0.9425 0.11544 0.11123 0.0017 0.0048 0.7859
18.250 0.9272 0.12248 0.11851 -0.0018 0.0047 0.7910
18.500 0.9135 0.12955 0.12578 -0.0057 0.0046 0.7969
18.750 0.8895 0.13938 0.13587 -0.0112 0.0049 0.8006
19.000 0.8687 0.14923 0.14593 -0.0171 0.0049 0.8047
19.250 0.8409 0.16187 0.15875 -0.0245 0.0052 0.8066
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