S9033 (7.5%) (s9033-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: S9033 (7.5%) (s9033-il) Reynolds number: 200,000 Max Cl/Cd: 39.61 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s9033-il-200000.txt Download as CSV file: xf-s9033-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.7674 0.08052 0.07710 -0.0007 1.0000 0.0502
-9.750 -0.7579 0.07862 0.07518 0.0009 1.0000 0.0472
-9.500 -0.8754 0.05343 0.04929 -0.0163 1.0000 0.0383
-9.250 -0.8770 0.04920 0.04470 -0.0161 1.0000 0.0380
-9.000 -0.8768 0.04432 0.03942 -0.0157 1.0000 0.0379
-8.750 -0.8756 0.03871 0.03332 -0.0151 1.0000 0.0384
-8.500 -0.8645 0.03501 0.02939 -0.0146 1.0000 0.0399
-8.250 -0.8478 0.03263 0.02675 -0.0139 1.0000 0.0412
-8.000 -0.8305 0.02980 0.02353 -0.0130 1.0000 0.0420
-7.750 -0.8109 0.02742 0.02081 -0.0121 1.0000 0.0430
-7.500 -0.7897 0.02533 0.01840 -0.0112 1.0000 0.0444
-7.250 -0.7670 0.02376 0.01655 -0.0104 1.0000 0.0465
-7.000 -0.7430 0.02264 0.01514 -0.0096 1.0000 0.0486
-6.750 -0.7210 0.02016 0.01248 -0.0088 1.0000 0.0512
-6.500 -0.6971 0.01896 0.01125 -0.0081 1.0000 0.0547
-6.250 -0.6725 0.01797 0.01010 -0.0074 1.0000 0.0594
-6.000 -0.6493 0.01665 0.00878 -0.0066 1.0000 0.0657
-5.750 -0.6244 0.01596 0.00801 -0.0059 1.0000 0.0751
-5.500 -0.5998 0.01529 0.00733 -0.0053 1.0000 0.0865
-5.250 -0.5756 0.01452 0.00661 -0.0047 1.0000 0.0985
-5.000 -0.5508 0.01393 0.00601 -0.0041 1.0000 0.1125
-4.750 -0.5260 0.01335 0.00546 -0.0035 1.0000 0.1289
-4.500 -0.5016 0.01274 0.00498 -0.0029 1.0000 0.1485
-4.250 -0.4769 0.01220 0.00454 -0.0022 1.0000 0.1733
-4.000 -0.4523 0.01167 0.00415 -0.0016 1.0000 0.2022
-3.750 -0.4277 0.01118 0.00379 -0.0010 1.0000 0.2354
-3.500 -0.4032 0.01072 0.00350 -0.0004 1.0000 0.2740
-3.250 -0.3789 0.01028 0.00326 0.0003 1.0000 0.3196
-3.000 -0.3548 0.00987 0.00305 0.0011 1.0000 0.3696
-2.750 -0.3310 0.00947 0.00287 0.0019 1.0000 0.4250
-2.500 -0.3077 0.00907 0.00274 0.0029 1.0000 0.4858
-2.250 -0.2849 0.00869 0.00265 0.0041 1.0000 0.5519
-2.000 -0.2627 0.00833 0.00259 0.0055 1.0000 0.6193
-1.750 -0.2409 0.00801 0.00253 0.0071 1.0000 0.6851
-1.500 -0.2198 0.00771 0.00251 0.0091 1.0000 0.7516
-1.250 -0.1990 0.00746 0.00254 0.0113 1.0000 0.8241
-1.000 -0.1645 0.00739 0.00265 0.0109 1.0000 0.9061
-0.750 -0.1054 0.00746 0.00272 0.0051 1.0000 0.9660
-0.500 -0.0458 0.00748 0.00269 -0.0014 1.0000 0.9949
-0.250 -0.0174 0.00743 0.00261 -0.0018 1.0000 1.0000
0.000 0.0000 0.00741 0.00259 0.0000 1.0000 1.0000
0.250 0.0174 0.00743 0.00261 0.0018 1.0000 1.0000
0.500 0.0457 0.00748 0.00269 0.0014 0.9950 1.0000
0.750 0.1054 0.00746 0.00272 -0.0051 0.9660 1.0000
1.000 0.1646 0.00739 0.00265 -0.0109 0.9058 1.0000
1.250 0.1991 0.00746 0.00254 -0.0113 0.8242 1.0000
1.500 0.2199 0.00771 0.00251 -0.0091 0.7516 1.0000
1.750 0.2410 0.00801 0.00253 -0.0071 0.6850 1.0000
2.000 0.2628 0.00833 0.00259 -0.0055 0.6191 1.0000
2.250 0.2850 0.00869 0.00265 -0.0041 0.5517 1.0000
2.500 0.3078 0.00907 0.00274 -0.0029 0.4856 1.0000
2.750 0.3311 0.00947 0.00287 -0.0019 0.4249 1.0000
3.000 0.3549 0.00987 0.00305 -0.0011 0.3695 1.0000
3.250 0.3790 0.01028 0.00326 -0.0003 0.3194 1.0000
3.500 0.4033 0.01072 0.00350 0.0003 0.2740 1.0000
3.750 0.4278 0.01118 0.00379 0.0010 0.2353 1.0000
4.000 0.4524 0.01167 0.00415 0.0016 0.2021 1.0000
4.250 0.4770 0.01220 0.00454 0.0022 0.1733 1.0000
4.500 0.5017 0.01274 0.00498 0.0028 0.1485 1.0000
4.750 0.5261 0.01335 0.00546 0.0034 0.1288 1.0000
5.000 0.5508 0.01393 0.00601 0.0041 0.1125 1.0000
5.250 0.5756 0.01453 0.00661 0.0047 0.0985 1.0000
5.500 0.5998 0.01528 0.00733 0.0053 0.0864 1.0000
5.750 0.6244 0.01596 0.00801 0.0059 0.0752 1.0000
6.000 0.6492 0.01665 0.00878 0.0066 0.0657 1.0000
6.250 0.6725 0.01797 0.01010 0.0074 0.0595 1.0000
6.500 0.6971 0.01896 0.01126 0.0082 0.0547 1.0000
6.750 0.7209 0.02015 0.01247 0.0088 0.0513 1.0000
7.000 0.7429 0.02264 0.01515 0.0097 0.0487 1.0000
7.250 0.7669 0.02375 0.01654 0.0105 0.0465 1.0000
7.500 0.7896 0.02532 0.01840 0.0113 0.0444 1.0000
7.750 0.8108 0.02739 0.02078 0.0121 0.0430 1.0000
8.000 0.8304 0.02979 0.02351 0.0130 0.0420 1.0000
8.250 0.8477 0.03262 0.02674 0.0139 0.0412 1.0000
8.500 0.8641 0.03509 0.02947 0.0146 0.0399 1.0000
8.750 0.8752 0.03875 0.03336 0.0152 0.0383 1.0000
9.000 0.8766 0.04431 0.03941 0.0158 0.0379 1.0000
9.250 0.8774 0.04906 0.04456 0.0162 0.0380 1.0000
9.500 0.8751 0.05345 0.04931 0.0164 0.0383 1.0000
9.750 0.7596 0.07808 0.07463 -0.0003 0.0473 1.0000
10.000 0.7697 0.07983 0.07641 0.0014 0.0501 1.0000
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Polar data table (+)
Polar graphs
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