NREL's S827 Airfoil (s827-nr) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: NREL's S827 Airfoil (s827-nr) Reynolds number: 1,000,000 Max Cl/Cd: 121.42 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s827-nr-1000000.txt Download as CSV file: xf-s827-nr-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.2575 0.02569 0.01977 -0.1228 0.7730 0.0041
-9.000 -0.2352 0.02547 0.01950 -0.1220 0.7716 0.0040
-8.750 -0.2165 0.02522 0.01921 -0.1207 0.7701 0.0040
-8.500 -0.2016 0.02477 0.01871 -0.1194 0.7686 0.0040
-8.250 -0.1863 0.02426 0.01817 -0.1184 0.7672 0.0040
-8.000 -0.1731 0.02368 0.01755 -0.1172 0.7657 0.0040
-7.750 -0.1697 0.02273 0.01655 -0.1147 0.7642 0.0041
-7.500 -0.1534 0.02224 0.01603 -0.1141 0.7628 0.0040
-7.250 -0.1564 0.02097 0.01470 -0.1110 0.7613 0.0044
-7.000 -0.1511 0.01999 0.01370 -0.1090 0.7602 0.0049
-6.750 -0.1432 0.01910 0.01280 -0.1073 0.7591 0.0050
-6.500 -0.1361 0.01817 0.01183 -0.1055 0.7579 0.0061
-6.250 -0.1287 0.01726 0.01089 -0.1037 0.7567 0.0064
-6.000 -0.1279 0.01605 0.00966 -0.1011 0.7553 0.0101
-5.750 -0.1284 0.01480 0.00845 -0.0983 0.7541 0.0204
-5.500 -0.1241 0.01380 0.00746 -0.0960 0.7529 0.0302
-5.250 -0.1190 0.01291 0.00659 -0.0937 0.7517 0.0411
-5.000 -0.1205 0.01209 0.00578 -0.0900 0.7505 0.0567
-4.750 -0.1193 0.01164 0.00534 -0.0863 0.7491 0.0745
-4.500 -0.1102 0.01116 0.00495 -0.0839 0.7476 0.1144
-4.250 -0.1199 0.00963 0.00401 -0.0788 0.7467 0.2905
-4.000 -0.1202 0.00795 0.00309 -0.0753 0.7458 0.5073
-3.750 -0.0918 0.00802 0.00316 -0.0759 0.7452 0.5297
-3.500 -0.0631 0.00808 0.00321 -0.0766 0.7446 0.5368
-3.250 -0.0342 0.00817 0.00325 -0.0773 0.7439 0.5434
-3.000 -0.0054 0.00825 0.00334 -0.0780 0.7432 0.5487
-2.750 0.0236 0.00832 0.00338 -0.0787 0.7426 0.5520
-2.500 0.0528 0.00850 0.00350 -0.0795 0.7419 0.5558
-2.250 0.0814 0.00845 0.00348 -0.0802 0.7413 0.5601
-2.000 0.1104 0.00845 0.00346 -0.0810 0.7407 0.5608
-1.750 0.1395 0.00844 0.00343 -0.0818 0.7401 0.5614
-1.500 0.1686 0.00844 0.00341 -0.0826 0.7395 0.5620
-1.250 0.1978 0.00843 0.00340 -0.0834 0.7389 0.5627
-1.000 0.2270 0.00843 0.00338 -0.0842 0.7382 0.5633
-0.750 0.2563 0.00844 0.00337 -0.0851 0.7375 0.5640
-0.500 0.2856 0.00845 0.00338 -0.0859 0.7369 0.5648
-0.250 0.3149 0.00847 0.00339 -0.0868 0.7364 0.5655
0.000 0.3442 0.00850 0.00342 -0.0877 0.7358 0.5662
0.250 0.3736 0.00855 0.00346 -0.0886 0.7352 0.5670
0.500 0.4029 0.00861 0.00352 -0.0895 0.7346 0.5677
0.750 0.4321 0.00871 0.00363 -0.0903 0.7339 0.5684
1.000 0.4607 0.00877 0.00371 -0.0911 0.7334 0.5690
1.250 0.4891 0.00881 0.00377 -0.0917 0.7330 0.5696
1.500 0.5173 0.00884 0.00382 -0.0924 0.7325 0.5703
1.750 0.5451 0.00883 0.00386 -0.0929 0.7318 0.5716
2.000 0.5730 0.00885 0.00394 -0.0935 0.7312 0.5727
2.250 0.6009 0.00889 0.00403 -0.0941 0.7306 0.5738
2.500 0.6287 0.00894 0.00413 -0.0947 0.7299 0.5748
2.750 0.6564 0.00898 0.00422 -0.0952 0.7289 0.5760
3.000 0.6843 0.00901 0.00429 -0.0958 0.7277 0.5770
3.250 0.7125 0.00904 0.00438 -0.0964 0.7266 0.5782
3.500 0.7413 0.00903 0.00440 -0.0971 0.7250 0.5793
3.750 0.7758 0.00887 0.00418 -0.0988 0.7196 0.5804
4.000 0.7964 0.00849 0.00386 -0.0975 0.7119 0.5814
4.250 0.8244 0.00830 0.00364 -0.0978 0.7046 0.5824
4.500 0.8460 0.00820 0.00361 -0.0968 0.6994 0.5833
4.750 0.8715 0.00814 0.00357 -0.0968 0.6952 0.5841
5.000 0.8959 0.00807 0.00355 -0.0965 0.6899 0.5856
5.250 0.9148 0.00799 0.00356 -0.0950 0.6834 0.5871
5.500 0.9337 0.00794 0.00354 -0.0935 0.6753 0.5885
5.750 0.9481 0.00790 0.00356 -0.0910 0.6653 0.5898
6.000 0.9592 0.00790 0.00362 -0.0879 0.6543 0.5912
6.250 0.9639 0.00804 0.00374 -0.0835 0.6326 0.5925
6.500 0.9422 0.00878 0.00424 -0.0739 0.5785 0.5937
6.750 0.9118 0.01010 0.00528 -0.0635 0.5236 0.5949
7.000 0.8924 0.01146 0.00643 -0.0556 0.4770 0.5962
7.250 0.8718 0.01310 0.00782 -0.0481 0.4254 0.5974
7.500 0.8492 0.01504 0.00945 -0.0408 0.3638 0.5983
7.750 0.8458 0.01632 0.01058 -0.0367 0.3233 0.6001
8.000 0.8395 0.01781 0.01185 -0.0324 0.2725 0.6018
8.250 0.8344 0.01932 0.01309 -0.0283 0.2176 0.6034
8.500 0.8368 0.02055 0.01412 -0.0255 0.1757 0.6050
8.750 0.8408 0.02174 0.01511 -0.0229 0.1358 0.6067
9.000 0.8485 0.02278 0.01601 -0.0210 0.1045 0.6085
9.250 0.8592 0.02371 0.01683 -0.0194 0.0817 0.6102
9.500 0.8700 0.02466 0.01768 -0.0179 0.0616 0.6119
9.750 0.8819 0.02556 0.01849 -0.0166 0.0455 0.6137
10.000 0.8946 0.02642 0.01931 -0.0154 0.0323 0.6162
10.250 0.9089 0.02722 0.02011 -0.0145 0.0259 0.6185
10.500 0.9231 0.02804 0.02091 -0.0135 0.0204 0.6209
10.750 0.9390 0.02877 0.02169 -0.0128 0.0178 0.6234
11.000 0.9535 0.02961 0.02250 -0.0120 0.0141 0.6258
11.250 0.9689 0.03041 0.02333 -0.0113 0.0118 0.6283
11.500 0.9826 0.03130 0.02425 -0.0104 0.0094 0.6313
11.750 0.9978 0.03212 0.02514 -0.0097 0.0080 0.6346
12.000 1.0101 0.03317 0.02620 -0.0087 0.0058 0.6378
12.250 1.0246 0.03408 0.02715 -0.0081 0.0048 0.6407
12.500 1.0367 0.03517 0.02829 -0.0071 0.0041 0.6440
12.750 1.0492 0.03625 0.02945 -0.0063 0.0031 0.6475
13.000 1.0632 0.03725 0.03052 -0.0057 0.0032 0.6512
13.250 1.0749 0.03844 0.03177 -0.0048 0.0028 0.6547
13.500 1.0832 0.03992 0.03334 -0.0037 0.0024 0.6582
13.750 1.0927 0.04131 0.03483 -0.0028 0.0021 0.6622
14.000 1.1041 0.04259 0.03619 -0.0021 0.0021 0.6663
14.250 1.1142 0.04401 0.03770 -0.0014 0.0019 0.6702
14.500 1.1266 0.04522 0.03901 -0.0009 0.0017 0.6748
14.750 1.1326 0.04707 0.04098 0.0001 0.0018 0.6792
15.000 1.1425 0.04856 0.04255 0.0006 0.0017 0.6838
15.250 1.1520 0.05011 0.04418 0.0011 0.0016 0.6885
15.500 1.1603 0.05180 0.04597 0.0016 0.0015 0.6937
15.750 1.1674 0.05366 0.04791 0.0021 0.0013 0.6988
16.000 1.1508 0.05805 0.05254 0.0039 0.0011 0.7022
16.250 1.1548 0.06036 0.05498 0.0043 0.0011 0.7077
16.500 1.1575 0.06290 0.05766 0.0046 0.0010 0.7131
16.750 1.1619 0.06530 0.06018 0.0047 0.0010 0.7187
17.000 1.1573 0.06883 0.06389 0.0050 0.0010 0.7243
17.250 1.1595 0.07167 0.06685 0.0048 0.0010 0.7299
17.500 1.1539 0.07551 0.07086 0.0047 0.0010 0.7354
17.750 1.1488 0.07945 0.07495 0.0042 0.0010 0.7411
18.000 1.1471 0.08307 0.07871 0.0035 0.0010 0.7470
18.250 1.1404 0.08754 0.08337 0.0025 0.0010 0.7530
18.500 1.1309 0.09255 0.08855 0.0012 0.0009 0.7584
18.750 1.1224 0.09751 0.09367 -0.0004 0.0010 0.7645
19.000 1.1117 0.10308 0.09941 -0.0025 0.0009 0.7704
19.250 1.0982 0.10927 0.10579 -0.0050 0.0009 0.7758
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