NREL's S827 Airfoil (s827-nr) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: NREL's S827 Airfoil (s827-nr) Reynolds number: 100,000 Max Cl/Cd: 21.31 at α=10° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s827-nr-100000-n5.txt Download as CSV file: xf-s827-nr-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.000 -0.2249 0.11053 0.10518 -0.1280 0.9220 0.0163
-13.750 -0.2308 0.10383 0.09847 -0.1319 0.9186 0.0162
-13.500 -0.2416 0.09725 0.09183 -0.1354 0.9152 0.0156
-13.250 -0.2584 0.09138 0.08591 -0.1375 0.9101 0.0155
-13.000 -0.2799 0.08509 0.07952 -0.1395 0.9061 0.0147
-12.500 -0.3290 0.07328 0.06716 -0.1396 0.8976 0.0134
-12.250 -0.3401 0.07006 0.06381 -0.1391 0.8934 0.0133
-12.000 -0.3537 0.06641 0.05992 -0.1384 0.8900 0.0133
-11.750 -0.3625 0.06361 0.05697 -0.1373 0.8863 0.0132
-11.500 -0.3728 0.06091 0.05406 -0.1355 0.8818 0.0132
-11.250 -0.3849 0.05805 0.05100 -0.1336 0.8780 0.0138
-11.000 -0.3855 0.05519 0.04779 -0.1319 0.8753 0.0135
-10.750 -0.3903 0.05329 0.04580 -0.1299 0.8711 0.0140
-10.500 -0.3897 0.05205 0.04444 -0.1283 0.8671 0.0145
-10.250 -0.3845 0.04997 0.04212 -0.1267 0.8641 0.0148
-10.000 -0.3743 0.04786 0.03975 -0.1255 0.8619 0.0153
-9.750 -0.3592 0.04586 0.03745 -0.1246 0.8602 0.0166
-9.500 -0.3342 0.04366 0.03492 -0.1240 0.8579 0.0168
-9.250 -0.2828 0.04121 0.03201 -0.1255 0.8573 0.0177
-9.000 -0.2239 0.03996 0.03039 -0.1271 0.8571 0.0186
-8.750 -0.1741 0.03970 0.03008 -0.1279 0.8563 0.0209
-8.500 -0.1478 0.03965 0.02995 -0.1272 0.8542 0.0246
-8.250 -0.1016 0.04097 0.03131 -0.1266 0.8532 0.0292
-8.000 -0.0700 0.04203 0.03232 -0.1254 0.8516 0.0362
-7.750 -0.0522 0.04229 0.03260 -0.1236 0.8498 0.0469
-7.500 -0.0406 0.04194 0.03226 -0.1220 0.8480 0.0600
-7.250 -0.0363 0.04106 0.03154 -0.1200 0.8463 0.0824
-7.000 -0.0449 0.04063 0.03125 -0.1159 0.8419 0.1028
-6.750 -0.0568 0.03965 0.03044 -0.1119 0.8383 0.1328
-6.500 -0.0744 0.03815 0.02914 -0.1077 0.8354 0.1725
-6.250 -0.0973 0.03619 0.02736 -0.1030 0.8330 0.2167
-6.000 -0.1286 0.03607 0.02732 -0.0951 0.8280 0.2282
-5.750 -0.1585 0.03560 0.02688 -0.0875 0.8232 0.2401
-5.500 -0.1884 0.03414 0.02546 -0.0806 0.8198 0.2657
-5.250 -0.2197 0.03477 0.02601 -0.0715 0.8152 0.2510
-5.000 -0.2532 0.03633 0.02743 -0.0609 0.8096 0.2169
-4.750 -0.2852 0.03546 0.02648 -0.0526 0.8060 0.2186
-4.500 -0.3160 0.03498 0.02589 -0.0445 0.8027 0.2138
-4.250 -0.3482 0.03603 0.02678 -0.0348 0.7977 0.1842
-4.000 -0.3761 0.03434 0.02514 -0.0282 0.7940 0.2255
-3.750 -0.3923 0.03329 0.02526 -0.0223 0.7918 0.5215
-3.500 -0.3705 0.03476 0.02657 -0.0209 0.7907 0.5642
-3.250 -0.3581 0.03630 0.02801 -0.0177 0.7885 0.5828
-3.000 -0.3486 0.03897 0.03074 -0.0127 0.7850 0.5946
-2.750 -0.3210 0.04256 0.03433 -0.0092 0.7834 0.6090
-2.500 -0.3044 0.04325 0.03491 -0.0073 0.7812 0.6155
-2.250 -0.2855 0.04298 0.03449 -0.0068 0.7794 0.6166
-2.000 -0.2665 0.04245 0.03380 -0.0067 0.7780 0.6176
-1.750 -0.2448 0.04195 0.03315 -0.0071 0.7768 0.6186
-1.500 -0.2345 0.04159 0.03265 -0.0057 0.7740 0.6199
-1.250 -0.2311 0.04130 0.03226 -0.0034 0.7702 0.6212
-1.000 -0.2140 0.04090 0.03173 -0.0033 0.7677 0.6224
-0.750 -0.1913 0.04049 0.03117 -0.0039 0.7656 0.6237
-0.500 -0.1661 0.04010 0.03064 -0.0051 0.7641 0.6250
-0.250 -0.1389 0.03975 0.03012 -0.0065 0.7628 0.6264
0.000 -0.1186 0.03967 0.02994 -0.0066 0.7604 0.6275
0.250 -0.1122 0.03996 0.03022 -0.0042 0.7556 0.6282
0.500 -0.0908 0.04009 0.03029 -0.0041 0.7530 0.6290
0.750 -0.0650 0.04016 0.03031 -0.0047 0.7509 0.6299
1.000 -0.0370 0.04023 0.03034 -0.0055 0.7492 0.6310
1.250 -0.0071 0.04029 0.03036 -0.0067 0.7479 0.6321
1.500 -0.0058 0.04074 0.03081 -0.0038 0.7414 0.6335
1.750 0.0177 0.04086 0.03091 -0.0041 0.7384 0.6348
2.000 0.0454 0.04092 0.03093 -0.0051 0.7363 0.6362
2.250 0.0761 0.04094 0.03092 -0.0066 0.7347 0.6377
2.500 0.0862 0.04131 0.03127 -0.0051 0.7289 0.6393
2.750 0.1083 0.04146 0.03139 -0.0055 0.7250 0.6409
3.000 0.1360 0.04158 0.03152 -0.0064 0.7225 0.6422
3.250 0.1662 0.04169 0.03169 -0.0074 0.7207 0.6432
3.750 0.1980 0.04246 0.03256 -0.0057 0.7101 0.6456
4.000 0.2274 0.04256 0.03272 -0.0066 0.7077 0.6472
4.250 0.2595 0.04263 0.03286 -0.0079 0.7059 0.6490
4.500 0.2641 0.04325 0.03354 -0.0057 0.6971 0.6509
4.750 0.2937 0.04332 0.03366 -0.0068 0.6942 0.6530
5.000 0.3270 0.04329 0.03368 -0.0085 0.6922 0.6553
5.250 0.3337 0.04390 0.03438 -0.0065 0.6830 0.6567
5.500 0.3628 0.04393 0.03453 -0.0073 0.6799 0.6581
5.750 0.3961 0.04383 0.03456 -0.0085 0.6778 0.6597
6.000 0.4025 0.04445 0.03528 -0.0065 0.6677 0.6613
6.250 0.4352 0.04427 0.03526 -0.0076 0.6649 0.6634
6.500 0.4462 0.04475 0.03584 -0.0063 0.6552 0.6654
6.750 0.4785 0.04449 0.03571 -0.0074 0.6516 0.6679
7.000 0.4926 0.04485 0.03618 -0.0065 0.6418 0.6705
7.250 0.5250 0.04438 0.03591 -0.0072 0.6376 0.6724
7.500 0.5385 0.04462 0.03631 -0.0059 0.6267 0.6744
7.750 0.5755 0.04370 0.03560 -0.0069 0.6226 0.6770
9.250 0.6945 0.04172 0.03470 -0.0013 0.5317 0.6929
9.500 0.7226 0.04073 0.03386 -0.0008 0.5020 0.6964
9.750 0.7791 0.03711 0.02994 -0.0016 0.4208 0.7004
10.000 0.7932 0.03723 0.02945 0.0006 0.3240 0.7031
10.250 0.7947 0.03873 0.03054 0.0029 0.2541 0.7060
10.500 0.7971 0.04039 0.03181 0.0049 0.1916 0.7093
10.750 0.8033 0.04195 0.03311 0.0062 0.1428 0.7131
11.000 0.8106 0.04345 0.03441 0.0075 0.1082 0.7160
11.250 0.8191 0.04490 0.03578 0.0087 0.0849 0.7192
11.500 0.8277 0.04643 0.03726 0.0098 0.0686 0.7228
11.750 0.8361 0.04806 0.03886 0.0107 0.0579 0.7268
12.000 0.8463 0.04954 0.04046 0.0116 0.0490 0.7303
12.250 0.8543 0.05121 0.04222 0.0127 0.0428 0.7337
12.500 0.8629 0.05289 0.04398 0.0135 0.0373 0.7378
12.750 0.8719 0.05468 0.04587 0.0142 0.0329 0.7423
13.000 0.8817 0.05635 0.04770 0.0151 0.0295 0.7461
13.250 0.8880 0.05839 0.04981 0.0159 0.0263 0.7504
13.500 0.9009 0.06002 0.05167 0.0164 0.0233 0.7558
13.750 0.9126 0.06180 0.05363 0.0171 0.0214 0.7605
14.000 0.9209 0.06380 0.05575 0.0176 0.0198 0.7656
14.250 0.9295 0.06612 0.05822 0.0180 0.0177 0.7714
14.500 0.9381 0.06830 0.06072 0.0186 0.0163 0.7765
14.750 0.9447 0.07083 0.06350 0.0191 0.0152 0.7824
15.000 0.9489 0.07362 0.06654 0.0196 0.0145 0.7882
15.250 0.9499 0.07662 0.06975 0.0199 0.0140 0.7939
15.750 0.9459 0.08356 0.07710 0.0201 0.0131 0.8061
16.000 0.9367 0.08801 0.08187 0.0199 0.0127 0.8123
16.250 0.9266 0.09270 0.08688 0.0195 0.0127 0.8185
16.500 0.9106 0.09824 0.09280 0.0184 0.0121 0.8250
16.750 0.8970 0.10379 0.09862 0.0169 0.0123 0.8321
17.000 0.8772 0.11046 0.10563 0.0144 0.0118 0.8395
17.250 0.8600 0.11714 0.11256 0.0116 0.0120 0.8478
17.500 0.8397 0.12488 0.12054 0.0078 0.0120 0.8569
17.750 0.8213 0.13261 0.12849 0.0037 0.0123 0.8678
18.000 0.8043 0.14043 0.13648 -0.0006 0.0126 0.8829
18.250 0.7849 0.14935 0.14556 -0.0055 0.0128 0.9037
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