NREL's S803 Airfoil (s803-nr) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: NREL's S803 Airfoil (s803-nr) Reynolds number: 100,000 Max Cl/Cd: 62.96 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s803-nr-100000-n5.txt Download as CSV file: xf-s803-nr-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.3768 0.09269 0.08778 -0.0475 1.0000 0.0326
-8.750 -0.3795 0.09002 0.08518 -0.0466 1.0000 0.0323
-8.500 -0.3862 0.08716 0.08240 -0.0460 1.0000 0.0320
-8.250 -0.3957 0.08449 0.07983 -0.0449 1.0000 0.0317
-8.000 -0.4111 0.08184 0.07729 -0.0435 1.0000 0.0314
-7.750 -0.4134 0.07697 0.07247 -0.0478 0.9951 0.0310
-7.250 -0.3898 0.05687 0.05201 -0.0761 0.9718 0.0308
-7.000 -0.3744 0.04891 0.04356 -0.0849 0.9609 0.0312
-6.750 -0.3546 0.04286 0.03694 -0.0902 0.9506 0.0315
-6.500 -0.3289 0.03801 0.03152 -0.0941 0.9425 0.0315
-6.250 -0.2972 0.03382 0.02667 -0.0977 0.9365 0.0319
-6.000 -0.2660 0.03070 0.02297 -0.1000 0.9298 0.0323
-5.750 -0.2333 0.02837 0.02026 -0.1022 0.9236 0.0337
-5.500 -0.1968 0.02682 0.01855 -0.1047 0.9198 0.0359
-5.250 -0.1680 0.02526 0.01672 -0.1053 0.9112 0.0372
-5.000 -0.1319 0.02363 0.01483 -0.1070 0.9068 0.0384
-4.750 -0.1005 0.02236 0.01335 -0.1078 0.8997 0.0398
-4.250 -0.0292 0.02024 0.01114 -0.1113 0.8893 0.0464
-4.000 0.0017 0.01947 0.01024 -0.1120 0.8807 0.0500
-3.500 0.0713 0.01781 0.00854 -0.1152 0.8672 0.0668
-3.250 0.1086 0.01695 0.00781 -0.1173 0.8616 0.1044
-3.000 0.1410 0.01614 0.00739 -0.1189 0.8535 0.1906
-2.750 0.1764 0.01484 0.00713 -0.1215 0.8471 0.4197
-2.500 0.2021 0.01468 0.00750 -0.1204 0.8387 0.5759
-2.250 0.2342 0.01478 0.00751 -0.1206 0.8315 0.6396
-2.000 0.2627 0.01494 0.00755 -0.1203 0.8231 0.6760
-1.750 0.2920 0.01504 0.00755 -0.1199 0.8161 0.7010
-1.500 0.3193 0.01516 0.00756 -0.1194 0.8078 0.7226
-1.250 0.3479 0.01522 0.00752 -0.1190 0.8008 0.7399
-1.000 0.3736 0.01532 0.00753 -0.1182 0.7928 0.7552
-0.750 0.4015 0.01537 0.00750 -0.1179 0.7861 0.7698
-0.500 0.4270 0.01545 0.00751 -0.1171 0.7789 0.7831
-0.250 0.4523 0.01549 0.00750 -0.1162 0.7719 0.7950
0.000 0.4790 0.01553 0.00748 -0.1158 0.7656 0.8057
0.250 0.5059 0.01561 0.00751 -0.1156 0.7585 0.8154
0.500 0.5347 0.01562 0.00745 -0.1156 0.7533 0.8228
0.750 0.5605 0.01573 0.00754 -0.1154 0.7459 0.8305
1.000 0.5884 0.01577 0.00754 -0.1153 0.7402 0.8368
1.250 0.6170 0.01588 0.00762 -0.1156 0.7344 0.8437
1.500 0.6425 0.01597 0.00771 -0.1152 0.7278 0.8497
1.750 0.6728 0.01603 0.00773 -0.1157 0.7229 0.8562
2.000 0.6973 0.01618 0.00792 -0.1152 0.7160 0.8627
2.250 0.7250 0.01626 0.00802 -0.1152 0.7100 0.8697
2.500 0.7521 0.01637 0.00815 -0.1152 0.7040 0.8767
2.750 0.7772 0.01649 0.00831 -0.1147 0.6968 0.8845
3.000 0.8058 0.01653 0.00838 -0.1148 0.6910 0.8927
3.250 0.8287 0.01668 0.00861 -0.1139 0.6825 0.9031
3.500 0.8568 0.01668 0.00863 -0.1138 0.6757 0.9135
3.750 0.8800 0.01676 0.00882 -0.1129 0.6659 0.9289
4.000 0.9092 0.01678 0.00892 -0.1132 0.6564 0.9543
4.250 0.9419 0.01681 0.00895 -0.1141 0.6459 1.0000
4.500 0.9690 0.01698 0.00918 -0.1142 0.6331 1.0000
4.750 0.9964 0.01713 0.00940 -0.1142 0.6200 1.0000
5.000 1.0234 0.01728 0.00958 -0.1141 0.6062 1.0000
5.250 1.0496 0.01743 0.00977 -0.1138 0.5912 1.0000
5.500 1.0749 0.01758 0.00997 -0.1133 0.5747 1.0000
5.750 1.0995 0.01774 0.01019 -0.1127 0.5564 1.0000
6.000 1.1224 0.01795 0.01045 -0.1118 0.5356 1.0000
6.250 1.1437 0.01818 0.01071 -0.1105 0.5101 1.0000
6.500 1.1635 0.01848 0.01100 -0.1090 0.4773 1.0000
6.750 1.1809 0.01889 0.01130 -0.1071 0.4305 1.0000
7.000 1.1934 0.01962 0.01169 -0.1045 0.3736 1.0000
7.250 1.2024 0.02068 0.01241 -0.1016 0.3191 1.0000
7.500 1.2102 0.02187 0.01332 -0.0986 0.2725 1.0000
7.750 1.2175 0.02303 0.01428 -0.0957 0.2351 1.0000
8.000 1.2248 0.02421 0.01532 -0.0929 0.2043 1.0000
8.250 1.2325 0.02542 0.01640 -0.0902 0.1792 1.0000
8.500 1.2411 0.02662 0.01753 -0.0878 0.1587 1.0000
8.750 1.2493 0.02788 0.01873 -0.0854 0.1420 1.0000
9.000 1.2578 0.02916 0.01999 -0.0832 0.1283 1.0000
9.250 1.2665 0.03047 0.02133 -0.0811 0.1172 1.0000
9.500 1.2743 0.03190 0.02275 -0.0791 0.1082 1.0000
9.750 1.2824 0.03335 0.02423 -0.0772 0.1000 1.0000
10.000 1.2909 0.03484 0.02579 -0.0754 0.0931 1.0000
10.250 1.2986 0.03644 0.02743 -0.0738 0.0873 1.0000
10.500 1.3063 0.03812 0.02916 -0.0722 0.0824 1.0000
10.750 1.3155 0.03973 0.03091 -0.0708 0.0772 1.0000
11.000 1.3217 0.04162 0.03280 -0.0694 0.0733 1.0000
11.250 1.3315 0.04337 0.03468 -0.0682 0.0698 1.0000
11.500 1.3410 0.04514 0.03659 -0.0671 0.0661 1.0000
11.750 1.3486 0.04707 0.03858 -0.0660 0.0630 1.0000
12.000 1.3564 0.04914 0.04068 -0.0650 0.0602 1.0000
12.250 1.3669 0.05105 0.04282 -0.0640 0.0574 1.0000
12.500 1.3756 0.05311 0.04506 -0.0632 0.0548 1.0000
12.750 1.3822 0.05529 0.04733 -0.0624 0.0525 1.0000
13.000 1.3890 0.05764 0.04968 -0.0617 0.0504 1.0000
13.250 1.3958 0.06010 0.05243 -0.0610 0.0484 1.0000
13.500 1.4012 0.06274 0.05531 -0.0604 0.0464 1.0000
13.750 1.4042 0.06551 0.05828 -0.0599 0.0445 1.0000
14.000 1.4059 0.06835 0.06124 -0.0597 0.0429 1.0000
14.250 1.4082 0.07123 0.06417 -0.0596 0.0414 1.0000
14.500 1.4082 0.07471 0.06786 -0.0595 0.0402 1.0000
14.750 1.4031 0.07883 0.07235 -0.0597 0.0389 1.0000
15.000 1.3963 0.08322 0.07703 -0.0604 0.0377 1.0000
15.250 1.3887 0.08777 0.08183 -0.0614 0.0365 1.0000
15.500 1.3810 0.09240 0.08667 -0.0627 0.0355 1.0000
15.750 1.3741 0.09700 0.09142 -0.0642 0.0346 1.0000
16.000 1.3687 0.10150 0.09603 -0.0659 0.0337 1.0000
16.250 1.3648 0.10587 0.10046 -0.0675 0.0329 1.0000
16.500 1.3481 0.11284 0.10771 -0.0708 0.0325 1.0000
16.750 1.3280 0.12086 0.11602 -0.0753 0.0322 1.0000
17.000 1.3058 0.12987 0.12531 -0.0808 0.0321 1.0000
17.250 1.2811 0.14012 0.13581 -0.0875 0.0321 1.0000
17.500 1.2530 0.15213 0.14803 -0.0959 0.0323 1.0000
17.750 1.2194 0.16697 0.16300 -0.1063 0.0327 1.0000
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