NREL's S807 Airfoil (s807-nr) Xfoil prediction polar at RE=50,000 Ncrit=9
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Airfoil: NREL's S807 Airfoil (s807-nr) Reynolds number: 50,000 Max Cl/Cd: 20.34 at α=1.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s807-nr-50000.txt Download as CSV file: xf-s807-nr-50000.csv |
XFOIL Version 6.96
Calculated polar for: NREL's S807 Airfoil
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.500 -0.7168 0.09513 0.08739 -0.0500 1.0000 0.1238
-13.250 -0.7503 0.08725 0.07942 -0.0529 1.0000 0.1226
-13.000 -0.7833 0.08036 0.07239 -0.0551 1.0000 0.1214
-12.750 -0.8135 0.07450 0.06636 -0.0564 1.0000 0.1207
-12.500 -0.8377 0.06963 0.06129 -0.0569 1.0000 0.1205
-12.250 -0.8558 0.06552 0.05697 -0.0567 1.0000 0.1208
-12.000 -0.8695 0.06193 0.05314 -0.0559 1.0000 0.1217
-11.750 -0.8802 0.05873 0.04967 -0.0546 1.0000 0.1230
-11.500 -0.8437 0.05656 0.04753 -0.0534 1.0000 0.1298
-11.250 -0.8345 0.05432 0.04513 -0.0519 1.0000 0.1361
-11.000 -0.7985 0.05317 0.04407 -0.0499 1.0000 0.1489
-10.750 -0.7729 0.05205 0.04306 -0.0474 1.0000 0.1647
-10.500 -0.7643 0.05034 0.04149 -0.0451 1.0000 0.1835
-10.250 -0.7561 0.04914 0.04085 -0.0419 1.0000 0.2128
-9.000 -0.4111 0.09227 0.08388 -0.0090 1.0000 0.4652
-8.750 -0.3283 0.09489 0.08624 -0.0051 1.0000 0.5564
-8.500 -0.3196 0.09304 0.08433 -0.0040 1.0000 0.5785
-8.250 -0.3141 0.09132 0.08255 -0.0028 1.0000 0.5978
-8.000 -0.3060 0.08943 0.08059 -0.0017 1.0000 0.6157
-7.750 -0.2979 0.08763 0.07874 -0.0005 1.0000 0.6334
-7.500 -0.2853 0.08550 0.07654 0.0002 1.0000 0.6504
-7.250 -0.2719 0.08339 0.07437 0.0008 1.0000 0.6673
-7.000 -0.2553 0.08105 0.07196 0.0011 1.0000 0.6836
-6.750 -0.2387 0.07881 0.06966 0.0014 1.0000 0.6995
-6.500 -0.2222 0.07662 0.06742 0.0017 1.0000 0.7150
-6.250 -0.2067 0.07462 0.06538 0.0021 1.0000 0.7304
-6.000 -0.1916 0.07274 0.06347 0.0026 1.0000 0.7461
-5.750 -0.1764 0.07096 0.06165 0.0031 1.0000 0.7623
-5.500 -0.1607 0.06921 0.05988 0.0035 1.0000 0.7787
-5.250 -0.1444 0.06755 0.05820 0.0039 1.0000 0.7963
-5.000 -0.1284 0.06602 0.05665 0.0044 1.0000 0.8146
-4.750 -0.1205 0.06534 0.05599 0.0062 1.0000 0.8346
-4.250 -0.0657 0.06065 0.05130 0.0032 1.0000 0.8720
-4.000 -0.0459 0.05960 0.05025 0.0031 1.0000 0.8988
-3.750 -0.0060 0.05665 0.04731 -0.0010 1.0000 0.9212
-3.500 0.0357 0.05427 0.04492 -0.0058 1.0000 0.9518
-3.000 0.1377 0.04896 0.03962 -0.0208 1.0000 1.0000
-2.750 0.1464 0.04839 0.03918 -0.0196 1.0000 1.0000
-2.500 0.1535 0.04798 0.03893 -0.0183 1.0000 1.0000
-2.250 0.1569 0.04791 0.03908 -0.0167 1.0000 1.0000
-2.000 0.2078 0.04662 0.03811 -0.0267 0.9765 1.0000
-1.750 0.3371 0.04050 0.03200 -0.0492 0.8774 1.0000
-1.500 0.4636 0.03589 0.02677 -0.0707 0.7908 1.0000
-1.250 0.5084 0.03494 0.02526 -0.0755 0.7344 1.0000
-1.000 0.5348 0.03464 0.02467 -0.0767 0.7012 1.0000
-0.750 0.5586 0.03444 0.02427 -0.0775 0.6772 1.0000
-0.500 0.5818 0.03430 0.02400 -0.0783 0.6578 1.0000
-0.250 0.6038 0.03421 0.02385 -0.0788 0.6411 1.0000
0.000 0.6239 0.03420 0.02383 -0.0790 0.6265 1.0000
0.250 0.6432 0.03426 0.02389 -0.0790 0.6140 1.0000
0.500 0.6634 0.03434 0.02391 -0.0791 0.6039 1.0000
0.750 0.6798 0.03455 0.02423 -0.0786 0.5937 1.0000
1.000 0.6985 0.03476 0.02440 -0.0784 0.5855 1.0000
1.250 0.7136 0.03508 0.02484 -0.0777 0.5766 1.0000
1.500 0.5382 0.04123 0.03096 -0.0440 0.5868 0.8656
1.750 0.5268 0.04163 0.03153 -0.0397 0.5803 0.8469
2.000 0.5096 0.04209 0.03205 -0.0343 0.5753 0.8330
2.250 0.5233 0.04208 0.03201 -0.0333 0.5688 0.8291
2.500 0.4806 0.04283 0.03290 -0.0240 0.5659 0.8172
2.750 0.4779 0.04316 0.03335 -0.0208 0.5597 0.8135
3.000 0.4794 0.04338 0.03361 -0.0182 0.5549 0.8114
3.250 0.4816 0.04373 0.03399 -0.0157 0.5510 0.8107
3.500 0.4585 0.04463 0.03508 -0.0102 0.5470 0.8093
3.750 0.4444 0.04548 0.03607 -0.0062 0.5425 0.8089
4.000 0.4500 0.04603 0.03666 -0.0048 0.5377 0.8096
4.250 0.4635 0.04659 0.03725 -0.0043 0.5332 0.8111
4.500 0.4260 0.04892 0.03979 0.0006 0.5298 0.8116
4.750 0.3871 0.05207 0.04308 0.0042 0.5274 0.8127
5.000 0.3313 0.05671 0.04783 0.0068 0.5275 0.8135
5.250 0.3040 0.06139 0.05256 0.0052 0.5284 0.8154
5.500 0.3003 0.06489 0.05610 0.0024 0.5292 0.8180
5.750 0.3070 0.06760 0.05887 0.0005 0.5321 0.8207
6.000 0.3244 0.06993 0.06126 -0.0016 0.5342 0.8240
7.000 0.2120 0.08727 0.07891 -0.0144 0.6817 0.8316
7.250 0.2346 0.08954 0.08122 -0.0165 0.6703 0.8363
7.500 0.2631 0.09200 0.08376 -0.0184 0.6587 0.8420
7.750 0.2726 0.09333 0.08514 -0.0190 0.6442 0.8465
8.000 0.2897 0.09544 0.08730 -0.0208 0.6307 0.8513
8.250 0.3276 0.09924 0.09118 -0.0234 0.6219 0.8580
8.500 0.3339 0.10024 0.09225 -0.0237 0.6068 0.8633
8.750 0.3421 0.10190 0.09397 -0.0243 0.5926 0.8689
9.000 0.3545 0.10404 0.09618 -0.0248 0.5807 0.8756
9.250 0.3911 0.10781 0.10007 -0.0273 0.5701 0.8853
9.500 0.3895 0.10871 0.10103 -0.0269 0.5556 0.8918
9.750 0.3982 0.11084 0.10324 -0.0278 0.5424 0.8997
10.000 0.4355 0.11525 0.10779 -0.0298 0.5339 0.9133
10.250 0.4327 0.11592 0.10855 -0.0295 0.5194 0.9230
10.500 0.4360 0.11777 0.11050 -0.0301 0.5065 0.9360
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