NREL's S802 Airfoil (s802-nr) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: NREL's S802 Airfoil (s802-nr) Reynolds number: 1,000,000 Max Cl/Cd: 132.52 at α=2.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s802-nr-1000000-n5.txt Download as CSV file: xf-s802-nr-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NREL's S802 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.500 -0.7156 0.03819 0.03590 -0.1071 0.9893 0.0070
-12.250 -0.7018 0.03545 0.03307 -0.1114 0.9863 0.0072
-12.000 -0.7102 0.03151 0.02892 -0.1143 0.9775 0.0072
-11.250 -0.6676 0.02574 0.02269 -0.1176 0.9512 0.0076
-11.000 -0.6404 0.02392 0.02067 -0.1202 0.9445 0.0078
-10.750 -0.6066 0.02200 0.01852 -0.1241 0.9380 0.0080
-10.500 -0.5657 0.02029 0.01657 -0.1290 0.9328 0.0083
-10.250 -0.5263 0.01879 0.01482 -0.1333 0.9223 0.0085
-10.000 -0.4912 0.01783 0.01365 -0.1360 0.9068 0.0088
-9.750 -0.4639 0.01708 0.01268 -0.1368 0.8884 0.0089
-9.500 -0.4422 0.01610 0.01148 -0.1366 0.8707 0.0091
-9.250 -0.4198 0.01545 0.01068 -0.1363 0.8554 0.0093
-9.000 -0.3964 0.01501 0.01012 -0.1360 0.8419 0.0095
-8.500 -0.3474 0.01441 0.00934 -0.1354 0.8184 0.0100
-8.250 -0.3229 0.01399 0.00882 -0.1351 0.8089 0.0103
-8.000 -0.2983 0.01355 0.00826 -0.1349 0.8000 0.0105
-7.750 -0.2732 0.01307 0.00768 -0.1347 0.7922 0.0108
-7.500 -0.2480 0.01264 0.00714 -0.1345 0.7846 0.0110
-7.250 -0.2221 0.01222 0.00663 -0.1344 0.7779 0.0113
-7.000 -0.1961 0.01186 0.00618 -0.1343 0.7712 0.0116
-6.750 -0.1696 0.01157 0.00582 -0.1343 0.7653 0.0118
-6.500 -0.1429 0.01129 0.00547 -0.1343 0.7590 0.0121
-6.000 -0.0902 0.01040 0.00445 -0.1343 0.7480 0.0129
-5.750 -0.0630 0.01013 0.00413 -0.1344 0.7428 0.0133
-5.250 -0.0081 0.00965 0.00355 -0.1345 0.7341 0.0140
-5.000 0.0196 0.00941 0.00328 -0.1347 0.7298 0.0144
-4.750 0.0473 0.00921 0.00303 -0.1348 0.7257 0.0148
-4.500 0.0751 0.00904 0.00281 -0.1349 0.7218 0.0153
-4.250 0.1033 0.00888 0.00263 -0.1350 0.7181 0.0157
-4.000 0.1314 0.00866 0.00237 -0.1352 0.7141 0.0166
-3.750 0.1595 0.00850 0.00218 -0.1354 0.7105 0.0174
-3.500 0.1875 0.00837 0.00202 -0.1355 0.7073 0.0182
-3.250 0.2161 0.00825 0.00189 -0.1357 0.7045 0.0192
-3.000 0.2446 0.00814 0.00177 -0.1359 0.7014 0.0202
-2.750 0.2730 0.00803 0.00165 -0.1361 0.6983 0.0236
-2.500 0.3014 0.00785 0.00155 -0.1364 0.6952 0.0437
-2.250 0.3297 0.00769 0.00147 -0.1366 0.6922 0.0711
-2.000 0.3586 0.00748 0.00140 -0.1370 0.6897 0.1121
-1.750 0.3874 0.00733 0.00134 -0.1374 0.6871 0.1479
-1.500 0.4162 0.00713 0.00130 -0.1378 0.6844 0.2006
-1.250 0.4450 0.00694 0.00127 -0.1383 0.6816 0.2602
-1.000 0.4739 0.00672 0.00125 -0.1388 0.6789 0.3388
-0.750 0.5034 0.00633 0.00124 -0.1396 0.6765 0.4744
-0.500 0.5330 0.00598 0.00127 -0.1403 0.6739 0.6061
-0.250 0.5616 0.00592 0.00133 -0.1405 0.6704 0.6598
0.000 0.5897 0.00594 0.00138 -0.1405 0.6660 0.6829
0.250 0.6176 0.00600 0.00142 -0.1405 0.6613 0.6975
0.500 0.6460 0.00603 0.00145 -0.1406 0.6561 0.7084
0.750 0.6737 0.00608 0.00150 -0.1406 0.6499 0.7170
1.000 0.7016 0.00613 0.00153 -0.1406 0.6436 0.7246
1.250 0.7292 0.00618 0.00158 -0.1405 0.6362 0.7313
1.500 0.7568 0.00625 0.00163 -0.1405 0.6290 0.7379
1.750 0.7842 0.00631 0.00169 -0.1404 0.6207 0.7431
2.000 0.8115 0.00638 0.00175 -0.1403 0.6113 0.7487
2.250 0.8383 0.00648 0.00181 -0.1401 0.5990 0.7546
2.500 0.8647 0.00657 0.00189 -0.1398 0.5847 0.7596
2.750 0.8905 0.00672 0.00198 -0.1394 0.5632 0.7634
3.000 0.9143 0.00698 0.00209 -0.1386 0.5289 0.7663
3.250 0.9337 0.00754 0.00235 -0.1371 0.4650 0.7689
3.500 0.9539 0.00809 0.00265 -0.1357 0.4106 0.7711
3.750 0.9750 0.00857 0.00293 -0.1346 0.3655 0.7734
4.000 0.9952 0.00910 0.00324 -0.1333 0.3170 0.7757
4.250 1.0153 0.00963 0.00355 -0.1320 0.2718 0.7780
4.500 1.0371 0.01004 0.00383 -0.1310 0.2403 0.7804
4.750 1.0586 0.01046 0.00411 -0.1299 0.2109 0.7829
5.000 1.0796 0.01090 0.00441 -0.1288 0.1823 0.7851
5.250 1.1013 0.01127 0.00470 -0.1278 0.1607 0.7873
5.500 1.1223 0.01166 0.00501 -0.1266 0.1402 0.7895
5.750 1.1434 0.01204 0.00531 -0.1255 0.1221 0.7920
6.000 1.1645 0.01241 0.00562 -0.1244 0.1073 0.7949
6.250 1.1855 0.01277 0.00593 -0.1233 0.0952 0.7978
6.500 1.2064 0.01313 0.00625 -0.1221 0.0855 0.8004
6.750 1.2266 0.01348 0.00657 -0.1209 0.0770 0.8030
7.000 1.2461 0.01378 0.00688 -0.1194 0.0704 0.8060
7.250 1.2637 0.01416 0.00724 -0.1176 0.0628 0.8093
7.500 1.2824 0.01450 0.00758 -0.1161 0.0580 0.8128
7.750 1.3000 0.01490 0.00797 -0.1144 0.0527 0.8162
8.000 1.3187 0.01524 0.00834 -0.1128 0.0496 0.8202
8.250 1.3358 0.01566 0.00877 -0.1111 0.0454 0.8248
8.500 1.3532 0.01609 0.00921 -0.1094 0.0419 0.8294
8.750 1.3709 0.01648 0.00965 -0.1078 0.0396 0.8340
9.000 1.3872 0.01696 0.01014 -0.1061 0.0369 0.8395
9.250 1.4032 0.01747 0.01068 -0.1043 0.0340 0.8453
9.500 1.4198 0.01792 0.01119 -0.1026 0.0326 0.8518
9.750 1.4358 0.01843 0.01174 -0.1009 0.0308 0.8594
10.000 1.4500 0.01902 0.01237 -0.0990 0.0286 0.8685
10.250 1.4643 0.01961 0.01302 -0.0972 0.0266 0.8802
10.500 1.4780 0.02016 0.01365 -0.0952 0.0249 0.8995
10.750 1.4886 0.02067 0.01429 -0.0927 0.0234 1.0000
11.000 1.5021 0.02146 0.01510 -0.0910 0.0217 1.0000
11.250 1.5164 0.02221 0.01589 -0.0895 0.0208 1.0000
11.500 1.5306 0.02298 0.01671 -0.0880 0.0199 1.0000
11.750 1.5439 0.02383 0.01759 -0.0865 0.0188 1.0000
12.000 1.5564 0.02477 0.01855 -0.0850 0.0177 1.0000
12.250 1.5680 0.02579 0.01960 -0.0834 0.0165 1.0000
12.500 1.5809 0.02674 0.02062 -0.0821 0.0157 1.0000
12.750 1.5929 0.02778 0.02171 -0.0807 0.0148 1.0000
13.000 1.6039 0.02893 0.02289 -0.0793 0.0138 1.0000
13.250 1.6141 0.03017 0.02416 -0.0779 0.0129 1.0000
13.500 1.6249 0.03139 0.02544 -0.0766 0.0122 1.0000
13.750 1.6350 0.03269 0.02680 -0.0754 0.0114 1.0000
14.000 1.6439 0.03413 0.02828 -0.0742 0.0105 1.0000
14.250 1.6521 0.03566 0.02986 -0.0729 0.0097 1.0000
14.500 1.6607 0.03718 0.03146 -0.0718 0.0091 1.0000
14.750 1.6684 0.03884 0.03318 -0.0708 0.0084 1.0000
15.000 1.6745 0.04068 0.03507 -0.0697 0.0077 1.0000
15.250 1.6808 0.04255 0.03701 -0.0688 0.0071 1.0000
15.500 1.6867 0.04450 0.03904 -0.0679 0.0065 1.0000
15.750 1.6913 0.04665 0.04125 -0.0671 0.0060 1.0000
16.000 1.6943 0.04902 0.04369 -0.0663 0.0054 1.0000
16.250 1.6981 0.05136 0.04611 -0.0657 0.0051 1.0000
16.500 1.7014 0.05382 0.04866 -0.0652 0.0048 1.0000
16.750 1.7036 0.05648 0.05142 -0.0648 0.0045 1.0000
17.000 1.7044 0.05939 0.05442 -0.0645 0.0042 1.0000
17.250 1.7041 0.06249 0.05762 -0.0644 0.0040 1.0000
17.500 1.7028 0.06584 0.06106 -0.0645 0.0038 1.0000
18.000 1.6985 0.07308 0.06852 -0.0651 0.0035 1.0000
18.250 1.6955 0.07696 0.07251 -0.0658 0.0035 1.0000
18.500 1.6912 0.08115 0.07682 -0.0666 0.0034 1.0000
18.750 1.6857 0.08565 0.08145 -0.0678 0.0033 1.0000
19.000 1.6789 0.09053 0.08645 -0.0693 0.0032 1.0000
19.250 1.6704 0.09582 0.09187 -0.0711 0.0031 1.0000
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