NREL's S803 Airfoil (s803-nr) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: NREL's S803 Airfoil (s803-nr) Reynolds number: 500,000 Max Cl/Cd: 108.06 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s803-nr-500000-n5.txt Download as CSV file: xf-s803-nr-500000-n5.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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.3955 0.10503 0.10266 -0.0396 1.0000 0.0094
-10.500 -0.3947 0.10210 0.09975 -0.0401 1.0000 0.0096
-9.250 -0.5071 0.03157 0.02825 -0.1052 0.9631 0.0102
-9.000 -0.4924 0.02803 0.02432 -0.1072 0.9543 0.0106
-8.750 -0.4684 0.02528 0.02122 -0.1096 0.9487 0.0110
-8.500 -0.4464 0.02300 0.01858 -0.1105 0.9407 0.0116
-8.250 -0.4160 0.02127 0.01651 -0.1125 0.9359 0.0120
-8.000 -0.3862 0.01958 0.01451 -0.1142 0.9298 0.0124
-7.750 -0.3535 0.01800 0.01277 -0.1164 0.9241 0.0128
-7.500 -0.3150 0.01698 0.01162 -0.1194 0.9201 0.0131
-7.250 -0.2770 0.01606 0.01058 -0.1222 0.9130 0.0136
-7.000 -0.2349 0.01513 0.00949 -0.1258 0.9060 0.0141
-6.750 -0.1961 0.01439 0.00861 -0.1285 0.8951 0.0148
-6.500 -0.1593 0.01378 0.00783 -0.1308 0.8821 0.0154
-6.250 -0.1262 0.01325 0.00715 -0.1321 0.8679 0.0159
-6.000 -0.0964 0.01262 0.00639 -0.1329 0.8531 0.0162
-5.750 -0.0683 0.01199 0.00565 -0.1333 0.8382 0.0168
-5.500 -0.0406 0.01159 0.00515 -0.1335 0.8237 0.0173
-5.250 -0.0133 0.01126 0.00472 -0.1335 0.8096 0.0179
-5.000 0.0138 0.01098 0.00434 -0.1336 0.7965 0.0185
-4.750 0.0410 0.01074 0.00401 -0.1336 0.7844 0.0195
-4.500 0.0684 0.01052 0.00370 -0.1336 0.7731 0.0203
-4.250 0.0959 0.01026 0.00336 -0.1336 0.7628 0.0211
-4.000 0.1234 0.01004 0.00305 -0.1336 0.7526 0.0223
-3.750 0.1510 0.00986 0.00282 -0.1337 0.7424 0.0238
-3.500 0.1787 0.00973 0.00261 -0.1337 0.7331 0.0257
-3.250 0.2065 0.00957 0.00242 -0.1337 0.7240 0.0310
-3.000 0.2346 0.00934 0.00226 -0.1339 0.7160 0.0539
-2.750 0.2626 0.00913 0.00212 -0.1342 0.7083 0.0864
-2.500 0.2910 0.00892 0.00202 -0.1345 0.7009 0.1256
-2.250 0.3193 0.00870 0.00192 -0.1348 0.6935 0.1812
-2.000 0.3480 0.00843 0.00184 -0.1353 0.6865 0.2507
-1.750 0.3770 0.00806 0.00177 -0.1360 0.6796 0.3569
-1.500 0.4063 0.00765 0.00174 -0.1367 0.6739 0.4923
-1.250 0.4346 0.00753 0.00186 -0.1369 0.6678 0.5874
-1.000 0.4625 0.00759 0.00191 -0.1368 0.6620 0.6171
-0.750 0.4907 0.00763 0.00194 -0.1368 0.6564 0.6315
-0.500 0.5188 0.00770 0.00197 -0.1368 0.6507 0.6445
0.000 0.5749 0.00782 0.00205 -0.1368 0.6409 0.6627
0.250 0.6028 0.00788 0.00211 -0.1367 0.6356 0.6710
0.500 0.6306 0.00797 0.00215 -0.1366 0.6309 0.6788
0.750 0.6585 0.00802 0.00222 -0.1366 0.6259 0.6866
1.000 0.6863 0.00809 0.00229 -0.1365 0.6201 0.6948
1.250 0.7136 0.00819 0.00236 -0.1364 0.6141 0.7016
1.500 0.7413 0.00825 0.00242 -0.1363 0.6067 0.7072
1.750 0.7683 0.00834 0.00249 -0.1361 0.5990 0.7108
2.000 0.7956 0.00840 0.00256 -0.1360 0.5904 0.7141
2.250 0.8225 0.00850 0.00263 -0.1358 0.5818 0.7176
2.500 0.8494 0.00859 0.00271 -0.1356 0.5716 0.7208
2.750 0.8764 0.00868 0.00280 -0.1354 0.5618 0.7240
3.000 0.9028 0.00879 0.00290 -0.1351 0.5518 0.7271
3.250 0.9291 0.00890 0.00300 -0.1348 0.5398 0.7305
3.500 0.9554 0.00902 0.00312 -0.1345 0.5266 0.7339
3.750 0.9815 0.00916 0.00323 -0.1341 0.5121 0.7375
4.000 1.0065 0.00933 0.00337 -0.1336 0.4934 0.7410
4.250 1.0309 0.00954 0.00352 -0.1329 0.4670 0.7450
4.500 1.0532 0.00990 0.00374 -0.1319 0.4273 0.7492
4.750 1.0720 0.01055 0.00410 -0.1304 0.3693 0.7535
5.000 1.0908 0.01123 0.00454 -0.1289 0.3162 0.7575
5.250 1.1104 0.01186 0.00497 -0.1276 0.2716 0.7622
5.500 1.1309 0.01242 0.00538 -0.1264 0.2359 0.7674
5.750 1.1510 0.01299 0.00580 -0.1252 0.2024 0.7727
6.000 1.1711 0.01353 0.00623 -0.1239 0.1740 0.7788
6.250 1.1914 0.01405 0.00666 -0.1227 0.1508 0.7850
6.500 1.2115 0.01453 0.00709 -0.1215 0.1307 0.7915
6.750 1.2317 0.01501 0.00752 -0.1203 0.1148 0.7989
7.000 1.2514 0.01548 0.00796 -0.1190 0.1012 0.8067
7.250 1.2710 0.01593 0.00841 -0.1176 0.0900 0.8157
7.500 1.2900 0.01637 0.00887 -0.1162 0.0814 0.8265
7.750 1.3079 0.01683 0.00934 -0.1145 0.0736 0.8390
8.000 1.3248 0.01722 0.00979 -0.1127 0.0676 0.8545
8.250 1.3390 0.01768 0.01029 -0.1103 0.0614 0.8757
8.500 1.3505 0.01793 0.01069 -0.1072 0.0575 0.9438
8.750 1.3664 0.01846 0.01123 -0.1054 0.0531 1.0000
9.000 1.3823 0.01905 0.01183 -0.1036 0.0494 1.0000
9.250 1.3986 0.01961 0.01243 -0.1019 0.0463 1.0000
9.500 1.4131 0.02028 0.01310 -0.1000 0.0430 1.0000
9.750 1.4271 0.02099 0.01386 -0.0981 0.0404 1.0000
10.000 1.4420 0.02165 0.01458 -0.0964 0.0385 1.0000
10.250 1.4555 0.02240 0.01537 -0.0945 0.0363 1.0000
10.500 1.4674 0.02328 0.01627 -0.0925 0.0341 1.0000
10.750 1.4787 0.02422 0.01726 -0.0906 0.0324 1.0000
11.000 1.4915 0.02508 0.01820 -0.0889 0.0311 1.0000
11.250 1.5034 0.02603 0.01922 -0.0872 0.0295 1.0000
11.500 1.5140 0.02711 0.02033 -0.0855 0.0276 1.0000
11.750 1.5227 0.02838 0.02163 -0.0837 0.0258 1.0000
12.000 1.5342 0.02947 0.02280 -0.0823 0.0246 1.0000
12.250 1.5446 0.03068 0.02408 -0.0809 0.0232 1.0000
12.500 1.5536 0.03205 0.02551 -0.0794 0.0220 1.0000
12.750 1.5612 0.03360 0.02711 -0.0781 0.0208 1.0000
13.000 1.5688 0.03519 0.02879 -0.0768 0.0200 1.0000
13.250 1.5773 0.03675 0.03044 -0.0757 0.0192 1.0000
13.500 1.5849 0.03843 0.03222 -0.0746 0.0183 1.0000
13.750 1.5916 0.04026 0.03412 -0.0737 0.0174 1.0000
14.000 1.5972 0.04225 0.03617 -0.0728 0.0165 1.0000
14.250 1.6017 0.04441 0.03841 -0.0719 0.0157 1.0000
14.500 1.6075 0.04648 0.04059 -0.0713 0.0149 1.0000
14.750 1.6126 0.04870 0.04291 -0.0707 0.0141 1.0000
15.000 1.6165 0.05110 0.04540 -0.0703 0.0132 1.0000
15.250 1.6186 0.05378 0.04815 -0.0699 0.0124 1.0000
15.500 1.6211 0.05649 0.05097 -0.0697 0.0118 1.0000
15.750 1.6233 0.05930 0.05390 -0.0696 0.0111 1.0000
16.000 1.6243 0.06235 0.05705 -0.0697 0.0105 1.0000
16.250 1.6240 0.06565 0.06045 -0.0699 0.0099 1.0000
16.500 1.6219 0.06930 0.06419 -0.0703 0.0094 1.0000
16.750 1.6205 0.07294 0.06796 -0.0709 0.0090 1.0000
17.000 1.6182 0.07684 0.07199 -0.0716 0.0085 1.0000
17.250 1.6143 0.08104 0.07632 -0.0726 0.0081 1.0000
17.500 1.6092 0.08556 0.08096 -0.0738 0.0077 1.0000
17.750 1.6025 0.09048 0.08602 -0.0754 0.0074 1.0000
18.000 1.5939 0.09587 0.09153 -0.0773 0.0072 1.0000
18.250 1.5846 0.10152 0.09732 -0.0795 0.0070 1.0000
18.500 1.5754 0.10729 0.10324 -0.0819 0.0068 1.0000
18.750 1.5651 0.11344 0.10955 -0.0848 0.0066 1.0000
19.000 1.5537 0.11994 0.11620 -0.0880 0.0064 1.0000
19.250 1.5410 0.12684 0.12326 -0.0916 0.0063 1.0000
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