S9033 (7.5%) (s9033-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: S9033 (7.5%) (s9033-il) Reynolds number: 100,000 Max Cl/Cd: 29.52 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s9033-il-100000.txt Download as CSV file: xf-s9033-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: S9033 (7.5%)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.7012 0.09308 0.08824 0.0112 1.0000 0.1552
-8.500 -0.7012 0.08788 0.08309 0.0101 1.0000 0.1573
-8.250 -0.8014 0.05313 0.04719 -0.0142 1.0000 0.0735
-8.000 -0.7970 0.04816 0.04170 -0.0142 1.0000 0.0739
-7.750 -0.7884 0.04328 0.03632 -0.0138 1.0000 0.0744
-7.500 -0.7748 0.03883 0.03138 -0.0132 1.0000 0.0745
-7.250 -0.7585 0.03467 0.02682 -0.0125 1.0000 0.0754
-7.000 -0.7384 0.03178 0.02369 -0.0119 1.0000 0.0775
-6.750 -0.7165 0.02946 0.02110 -0.0111 1.0000 0.0807
-6.500 -0.6940 0.02752 0.01858 -0.0101 1.0000 0.0865
-6.250 -0.6711 0.02555 0.01659 -0.0096 1.0000 0.0934
-6.000 -0.6465 0.02373 0.01437 -0.0086 1.0000 0.1013
-5.750 -0.6223 0.02235 0.01296 -0.0080 1.0000 0.1129
-5.500 -0.5980 0.02112 0.01168 -0.0073 1.0000 0.1268
-5.250 -0.5734 0.01998 0.01049 -0.0066 1.0000 0.1423
-5.000 -0.5491 0.01888 0.00950 -0.0059 1.0000 0.1596
-4.750 -0.5246 0.01799 0.00864 -0.0052 1.0000 0.1810
-4.500 -0.5003 0.01701 0.00779 -0.0045 1.0000 0.2046
-4.250 -0.4761 0.01613 0.00705 -0.0037 1.0000 0.2342
-4.000 -0.4523 0.01533 0.00641 -0.0029 1.0000 0.2716
-3.750 -0.4288 0.01456 0.00588 -0.0020 1.0000 0.3149
-3.500 -0.4055 0.01387 0.00544 -0.0010 1.0000 0.3677
-3.250 -0.3830 0.01320 0.00511 0.0002 1.0000 0.4276
-3.000 -0.3609 0.01260 0.00484 0.0016 1.0000 0.4960
-2.750 -0.3394 0.01204 0.00463 0.0033 1.0000 0.5699
-2.500 -0.3185 0.01155 0.00449 0.0054 1.0000 0.6460
-2.250 -0.2977 0.01114 0.00438 0.0078 1.0000 0.7243
-2.000 -0.2763 0.01083 0.00434 0.0105 1.0000 0.8044
-1.750 -0.2410 0.01074 0.00436 0.0108 1.0000 0.8891
-1.500 -0.1752 0.01084 0.00435 0.0044 1.0000 0.9566
-1.250 -0.0918 0.01080 0.00408 -0.0066 1.0000 0.9979
-1.000 -0.0728 0.01055 0.00377 -0.0059 1.0000 1.0000
-0.750 -0.0557 0.01040 0.00356 -0.0044 1.0000 1.0000
-0.500 -0.0374 0.01031 0.00343 -0.0030 1.0000 1.0000
-0.250 -0.0187 0.01026 0.00335 -0.0015 1.0000 1.0000
0.000 0.0000 0.01025 0.00333 0.0000 1.0000 1.0000
0.250 0.0187 0.01026 0.00335 0.0015 1.0000 1.0000
0.500 0.0374 0.01031 0.00343 0.0030 1.0000 1.0000
0.750 0.0557 0.01040 0.00356 0.0044 1.0000 1.0000
1.000 0.0727 0.01055 0.00377 0.0059 1.0000 1.0000
1.250 0.0919 0.01080 0.00408 0.0066 0.9979 1.0000
1.500 0.1752 0.01085 0.00435 -0.0044 0.9566 1.0000
1.750 0.2411 0.01074 0.00436 -0.0108 0.8890 1.0000
2.000 0.2763 0.01083 0.00434 -0.0105 0.8043 1.0000
2.250 0.2978 0.01114 0.00438 -0.0078 0.7244 1.0000
2.500 0.3186 0.01155 0.00449 -0.0054 0.6459 1.0000
2.750 0.3395 0.01204 0.00463 -0.0033 0.5698 1.0000
3.000 0.3609 0.01260 0.00484 -0.0016 0.4960 1.0000
3.250 0.3830 0.01320 0.00511 -0.0002 0.4276 1.0000
3.500 0.4056 0.01387 0.00544 0.0010 0.3676 1.0000
3.750 0.4288 0.01456 0.00588 0.0020 0.3149 1.0000
4.000 0.4523 0.01533 0.00641 0.0029 0.2716 1.0000
4.250 0.4761 0.01613 0.00705 0.0037 0.2343 1.0000
4.500 0.5003 0.01700 0.00779 0.0045 0.2046 1.0000
4.750 0.5246 0.01799 0.00864 0.0052 0.1810 1.0000
5.000 0.5491 0.01888 0.00950 0.0059 0.1596 1.0000
5.250 0.5734 0.01998 0.01049 0.0066 0.1423 1.0000
5.500 0.5980 0.02112 0.01168 0.0073 0.1267 1.0000
5.750 0.6223 0.02235 0.01296 0.0080 0.1129 1.0000
6.000 0.6465 0.02374 0.01437 0.0086 0.1013 1.0000
6.250 0.6710 0.02555 0.01659 0.0096 0.0935 1.0000
6.500 0.6939 0.02753 0.01858 0.0101 0.0865 1.0000
6.750 0.7164 0.02946 0.02110 0.0111 0.0808 1.0000
7.000 0.7384 0.03178 0.02369 0.0119 0.0775 1.0000
7.250 0.7584 0.03466 0.02681 0.0126 0.0754 1.0000
7.500 0.7747 0.03882 0.03136 0.0132 0.0745 1.0000
7.750 0.7881 0.04332 0.03636 0.0138 0.0743 1.0000
8.000 0.7969 0.04815 0.04169 0.0142 0.0739 1.0000
8.250 0.8013 0.05311 0.04717 0.0142 0.0735 1.0000
8.500 0.7019 0.08789 0.08309 -0.0100 0.1573 1.0000
8.750 0.7014 0.09310 0.08826 -0.0113 0.1552 1.0000
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Polar data table (+)
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