NREL's S803 Airfoil (s803-nr) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: NREL's S803 Airfoil (s803-nr) Reynolds number: 1,000,000 Max Cl/Cd: 140.3 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s803-nr-1000000.txt Download as CSV file: xf-s803-nr-1000000.csv |
XFOIL Version 6.96
Calculated polar for: NREL's S803 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 -0.3485 0.08589 0.08429 -0.0529 0.9956 0.0139
-9.000 -0.3383 0.08028 0.07868 -0.0591 0.9943 0.0142
-8.750 -0.4374 0.02733 0.02436 -0.1139 0.9735 0.0121
-8.500 -0.4203 0.02385 0.02042 -0.1155 0.9662 0.0123
-8.250 -0.3946 0.01944 0.01557 -0.1187 0.9627 0.0128
-8.000 -0.3615 0.01826 0.01428 -0.1209 0.9608 0.0132
-7.750 -0.3396 0.01740 0.01335 -0.1203 0.9524 0.0136
-7.500 -0.3076 0.01652 0.01237 -0.1218 0.9489 0.0141
-7.250 -0.2779 0.01567 0.01140 -0.1226 0.9423 0.0147
-7.000 -0.2416 0.01475 0.01033 -0.1248 0.9376 0.0153
-6.750 -0.1989 0.01391 0.00934 -0.1284 0.9342 0.0158
-6.500 -0.1584 0.01345 0.00876 -0.1313 0.9258 0.0160
-6.250 -0.1194 0.01131 0.00642 -0.1346 0.9157 0.0167
-6.000 -0.0833 0.01062 0.00565 -0.1367 0.9010 0.0174
-5.750 -0.0519 0.01023 0.00517 -0.1377 0.8834 0.0181
-5.500 -0.0233 0.00992 0.00475 -0.1379 0.8656 0.0189
-5.250 0.0039 0.00959 0.00430 -0.1379 0.8484 0.0194
-5.000 0.0306 0.00931 0.00391 -0.1378 0.8320 0.0198
-4.750 0.0573 0.00907 0.00357 -0.1376 0.8166 0.0203
-4.500 0.0842 0.00888 0.00328 -0.1374 0.8022 0.0206
-4.250 0.1114 0.00846 0.00275 -0.1375 0.7890 0.0216
-4.000 0.1387 0.00824 0.00246 -0.1374 0.7768 0.0230
-3.750 0.1661 0.00811 0.00226 -0.1374 0.7653 0.0245
-3.500 0.1936 0.00800 0.00207 -0.1373 0.7541 0.0257
-3.250 0.2215 0.00786 0.00188 -0.1373 0.7434 0.0286
-3.000 0.2495 0.00766 0.00172 -0.1374 0.7335 0.0459
-2.750 0.2776 0.00733 0.00157 -0.1378 0.7238 0.1105
-2.500 0.3062 0.00705 0.00148 -0.1382 0.7152 0.1758
-2.250 0.3346 0.00678 0.00141 -0.1386 0.7069 0.2591
-2.000 0.3636 0.00647 0.00134 -0.1392 0.6990 0.3488
-1.750 0.3924 0.00613 0.00129 -0.1397 0.6914 0.4652
-1.500 0.4214 0.00591 0.00133 -0.1401 0.6842 0.5701
-1.250 0.4494 0.00594 0.00137 -0.1401 0.6773 0.6058
-1.000 0.4778 0.00598 0.00142 -0.1402 0.6712 0.6305
-0.750 0.5058 0.00604 0.00147 -0.1401 0.6649 0.6472
-0.500 0.5338 0.00611 0.00151 -0.1401 0.6591 0.6581
-0.250 0.5621 0.00615 0.00154 -0.1401 0.6533 0.6651
0.000 0.5900 0.00623 0.00159 -0.1401 0.6475 0.6729
0.250 0.6182 0.00629 0.00162 -0.1401 0.6417 0.6790
0.500 0.6461 0.00634 0.00166 -0.1400 0.6351 0.6845
0.750 0.6738 0.00643 0.00171 -0.1400 0.6285 0.6905
1.000 0.7017 0.00647 0.00175 -0.1399 0.6214 0.6959
1.250 0.7291 0.00656 0.00182 -0.1398 0.6145 0.7013
1.500 0.7572 0.00662 0.00187 -0.1398 0.6075 0.7073
2.000 0.8121 0.00674 0.00199 -0.1396 0.5927 0.7182
2.250 0.8395 0.00684 0.00205 -0.1394 0.5855 0.7224
2.500 0.8673 0.00687 0.00212 -0.1394 0.5782 0.7259
2.750 0.8942 0.00696 0.00219 -0.1392 0.5698 0.7291
3.000 0.9220 0.00701 0.00226 -0.1392 0.5620 0.7324
3.250 0.9489 0.00712 0.00234 -0.1390 0.5534 0.7357
3.500 0.9764 0.00719 0.00242 -0.1390 0.5438 0.7389
3.750 1.0033 0.00727 0.00251 -0.1388 0.5341 0.7425
4.000 1.0297 0.00739 0.00261 -0.1385 0.5209 0.7461
4.250 1.0560 0.00753 0.00273 -0.1382 0.5042 0.7498
4.500 1.0817 0.00771 0.00285 -0.1378 0.4826 0.7536
4.750 1.1057 0.00798 0.00302 -0.1371 0.4503 0.7577
5.000 1.1259 0.00856 0.00333 -0.1358 0.3905 0.7623
5.250 1.1457 0.00922 0.00372 -0.1344 0.3332 0.7673
5.500 1.1654 0.00987 0.00413 -0.1331 0.2815 0.7720
5.750 1.1855 0.01048 0.00453 -0.1319 0.2371 0.7774
6.000 1.2060 0.01105 0.00491 -0.1307 0.1995 0.7832
6.250 1.2265 0.01157 0.00531 -0.1295 0.1688 0.7892
6.500 1.2478 0.01203 0.00568 -0.1284 0.1451 0.7964
7.000 1.2899 0.01293 0.00644 -0.1262 0.1090 0.8130
7.250 1.3106 0.01335 0.00684 -0.1250 0.0949 0.8227
7.500 1.3311 0.01377 0.00724 -0.1238 0.0834 0.8341
7.750 1.3510 0.01419 0.00765 -0.1225 0.0738 0.8479
8.000 1.3712 0.01454 0.00804 -0.1212 0.0672 0.8656
8.250 1.3888 0.01492 0.00847 -0.1194 0.0601 0.8931
8.500 1.4030 0.01512 0.00880 -0.1168 0.0558 1.0000
8.750 1.4196 0.01565 0.00930 -0.1150 0.0501 1.0000
9.000 1.4383 0.01603 0.00970 -0.1135 0.0475 1.0000
9.250 1.4541 0.01655 0.01021 -0.1115 0.0437 1.0000
9.500 1.4692 0.01712 0.01080 -0.1094 0.0404 1.0000
9.750 1.4866 0.01755 0.01127 -0.1078 0.0385 1.0000
10.000 1.5018 0.01812 0.01183 -0.1059 0.0358 1.0000
10.250 1.5138 0.01887 0.01258 -0.1035 0.0327 1.0000
10.500 1.5309 0.01934 0.01310 -0.1020 0.0316 1.0000
10.750 1.5457 0.01993 0.01373 -0.1002 0.0300 1.0000
11.000 1.5588 0.02065 0.01447 -0.0982 0.0284 1.0000
11.250 1.5687 0.02159 0.01543 -0.0958 0.0265 1.0000
11.500 1.5814 0.02237 0.01627 -0.0939 0.0256 1.0000
11.750 1.5951 0.02310 0.01706 -0.0922 0.0247 1.0000
12.000 1.6078 0.02392 0.01792 -0.0905 0.0236 1.0000
12.250 1.6187 0.02489 0.01893 -0.0887 0.0224 1.0000
12.500 1.6264 0.02614 0.02021 -0.0866 0.0209 1.0000
12.750 1.6359 0.02730 0.02144 -0.0849 0.0200 1.0000
13.000 1.6479 0.02830 0.02250 -0.0835 0.0193 1.0000
13.250 1.6583 0.02946 0.02372 -0.0821 0.0184 1.0000
13.500 1.6670 0.03080 0.02510 -0.0806 0.0174 1.0000
13.750 1.6725 0.03248 0.02682 -0.0790 0.0163 1.0000
14.000 1.6801 0.03403 0.02844 -0.0777 0.0155 1.0000
14.250 1.6897 0.03544 0.02993 -0.0767 0.0147 1.0000
14.500 1.6971 0.03709 0.03163 -0.0756 0.0138 1.0000
14.750 1.7014 0.03911 0.03369 -0.0745 0.0128 1.0000
15.000 1.7058 0.04119 0.03585 -0.0735 0.0119 1.0000
15.250 1.7120 0.04313 0.03787 -0.0728 0.0111 1.0000
15.500 1.7155 0.04542 0.04020 -0.0720 0.0102 1.0000
15.750 1.7149 0.04826 0.04311 -0.0714 0.0093 1.0000
16.000 1.7186 0.05068 0.04563 -0.0709 0.0087 1.0000
16.250 1.7200 0.05343 0.04845 -0.0706 0.0081 1.0000
16.500 1.7187 0.05662 0.05171 -0.0704 0.0075 1.0000
16.750 1.7124 0.06057 0.05577 -0.0704 0.0070 1.0000
17.000 1.7128 0.06374 0.05905 -0.0706 0.0068 1.0000
17.250 1.7110 0.06730 0.06272 -0.0709 0.0065 1.0000
17.500 1.7080 0.07112 0.06666 -0.0715 0.0062 1.0000
17.750 1.7036 0.07529 0.07093 -0.0723 0.0060 1.0000
18.000 1.6976 0.07980 0.07555 -0.0733 0.0058 1.0000
18.250 1.6898 0.08471 0.08058 -0.0747 0.0056 1.0000
18.500 1.6796 0.09020 0.08618 -0.0764 0.0054 1.0000
18.750 1.6661 0.09644 0.09257 -0.0787 0.0053 1.0000
19.000 1.6492 0.10349 0.09977 -0.0816 0.0051 1.0000
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