S9033 (7.5%) (s9033-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: S9033 (7.5%) (s9033-il) Reynolds number: 500,000 Max Cl/Cd: 58.94 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s9033-il-500000-n5.txt Download as CSV file: xf-s9033-il-500000-n5.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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.750 -1.0456 0.09498 0.09240 0.0140 1.0000 0.0071
-14.500 -1.1127 0.07768 0.07488 0.0035 1.0000 0.0067
-14.250 -1.1732 0.06130 0.05831 -0.0074 1.0000 0.0062
-14.000 -1.2131 0.04846 0.04521 -0.0180 1.0000 0.0059
-13.750 -1.2349 0.04160 0.03813 -0.0234 1.0000 0.0060
-13.500 -1.2503 0.03776 0.03410 -0.0243 1.0000 0.0060
-13.250 -1.2592 0.03534 0.03151 -0.0226 1.0000 0.0061
-13.000 -1.2592 0.03335 0.02934 -0.0209 1.0000 0.0064
-12.750 -1.2522 0.03157 0.02740 -0.0197 1.0000 0.0066
-12.500 -1.2413 0.03001 0.02571 -0.0187 1.0000 0.0070
-12.250 -1.2261 0.02885 0.02445 -0.0179 1.0000 0.0073
-12.000 -1.2088 0.02784 0.02333 -0.0172 1.0000 0.0078
-11.750 -1.1912 0.02681 0.02217 -0.0165 1.0000 0.0083
-11.500 -1.1725 0.02582 0.02105 -0.0158 1.0000 0.0089
-11.250 -1.1527 0.02494 0.02003 -0.0151 1.0000 0.0094
-11.000 -1.1314 0.02422 0.01915 -0.0145 1.0000 0.0098
-10.750 -1.1139 0.02288 0.01769 -0.0137 1.0000 0.0105
-10.500 -1.0925 0.02212 0.01685 -0.0132 1.0000 0.0111
-10.250 -1.0698 0.02153 0.01619 -0.0127 1.0000 0.0118
-10.000 -1.0471 0.02087 0.01544 -0.0122 1.0000 0.0125
-9.750 -1.0241 0.02023 0.01470 -0.0117 1.0000 0.0132
-9.500 -1.0006 0.01965 0.01400 -0.0112 1.0000 0.0138
-9.250 -0.9769 0.01908 0.01333 -0.0107 1.0000 0.0142
-9.000 -0.9567 0.01776 0.01185 -0.0099 1.0000 0.0150
-8.750 -0.9338 0.01695 0.01095 -0.0093 1.0000 0.0157
-8.500 -0.9099 0.01632 0.01026 -0.0088 1.0000 0.0165
-8.250 -0.8856 0.01575 0.00961 -0.0083 1.0000 0.0172
-8.000 -0.8613 0.01515 0.00893 -0.0077 1.0000 0.0179
-7.750 -0.8367 0.01458 0.00827 -0.0072 1.0000 0.0185
-7.500 -0.8119 0.01405 0.00764 -0.0067 1.0000 0.0192
-7.250 -0.7868 0.01358 0.00708 -0.0062 1.0000 0.0198
-7.000 -0.7619 0.01303 0.00646 -0.0057 1.0000 0.0208
-6.750 -0.7369 0.01250 0.00591 -0.0052 1.0000 0.0230
-6.500 -0.7115 0.01209 0.00549 -0.0047 1.0000 0.0254
-6.250 -0.6857 0.01174 0.00508 -0.0043 1.0000 0.0276
-6.000 -0.6603 0.01132 0.00467 -0.0038 1.0000 0.0323
-5.750 -0.6344 0.01101 0.00434 -0.0033 1.0000 0.0370
-5.500 -0.6088 0.01067 0.00402 -0.0029 1.0000 0.0429
-5.250 -0.5828 0.01041 0.00374 -0.0024 1.0000 0.0481
-5.000 -0.5570 0.01012 0.00345 -0.0019 1.0000 0.0543
-4.750 -0.5312 0.00987 0.00320 -0.0015 1.0000 0.0606
-4.500 -0.5055 0.00959 0.00297 -0.0010 1.0000 0.0699
-4.250 -0.4799 0.00932 0.00276 -0.0005 1.0000 0.0814
-4.000 -0.4545 0.00905 0.00256 0.0001 1.0000 0.0965
-3.750 -0.4290 0.00880 0.00236 0.0006 1.0000 0.1121
-3.250 -0.3783 0.00835 0.00204 0.0018 1.0000 0.1439
-3.000 -0.3530 0.00814 0.00190 0.0024 1.0000 0.1603
-2.750 -0.3277 0.00795 0.00177 0.0030 1.0000 0.1780
-2.500 -0.2982 0.00775 0.00166 0.0027 0.9974 0.1992
-2.250 -0.2615 0.00752 0.00156 0.0007 0.9879 0.2308
-2.000 -0.2252 0.00730 0.00146 -0.0010 0.9728 0.2621
-1.750 -0.1890 0.00706 0.00138 -0.0028 0.9497 0.3024
-1.500 -0.1518 0.00684 0.00129 -0.0046 0.9059 0.3507
-1.250 -0.1259 0.00681 0.00119 -0.0037 0.8399 0.3864
-1.000 -0.1017 0.00685 0.00112 -0.0026 0.7791 0.4176
-0.750 -0.0767 0.00687 0.00108 -0.0018 0.7274 0.4553
-0.500 -0.0512 0.00687 0.00104 -0.0012 0.6817 0.4964
-0.250 -0.0256 0.00683 0.00103 -0.0006 0.6390 0.5431
0.000 0.0000 0.00679 0.00102 0.0000 0.5956 0.5954
0.250 0.0255 0.00683 0.00103 0.0006 0.5433 0.6392
0.500 0.0512 0.00687 0.00105 0.0012 0.4962 0.6820
0.750 0.0767 0.00687 0.00108 0.0018 0.4555 0.7274
1.000 0.1017 0.00685 0.00112 0.0026 0.4178 0.7791
1.250 0.1259 0.00681 0.00119 0.0037 0.3864 0.8401
1.500 0.1518 0.00684 0.00129 0.0046 0.3506 0.9062
1.750 0.1890 0.00706 0.00138 0.0028 0.3023 0.9496
2.000 0.2253 0.00730 0.00147 0.0010 0.2623 0.9729
2.250 0.2614 0.00752 0.00156 -0.0007 0.2312 0.9878
2.500 0.2981 0.00775 0.00166 -0.0027 0.1993 0.9973
2.750 0.3278 0.00795 0.00177 -0.0030 0.1781 1.0000
3.000 0.3531 0.00814 0.00190 -0.0024 0.1603 1.0000
3.250 0.3784 0.00835 0.00204 -0.0018 0.1438 1.0000
3.500 0.4038 0.00857 0.00219 -0.0012 0.1281 1.0000
3.750 0.4292 0.00880 0.00236 -0.0007 0.1120 1.0000
4.000 0.4546 0.00905 0.00256 -0.0001 0.0964 1.0000
4.250 0.4800 0.00932 0.00276 0.0004 0.0815 1.0000
4.500 0.5056 0.00959 0.00297 0.0009 0.0701 1.0000
4.750 0.5312 0.00987 0.00320 0.0014 0.0606 1.0000
5.000 0.5571 0.01012 0.00345 0.0019 0.0543 1.0000
5.250 0.5829 0.01041 0.00374 0.0024 0.0481 1.0000
5.500 0.6088 0.01067 0.00402 0.0029 0.0428 1.0000
5.750 0.6344 0.01101 0.00434 0.0033 0.0370 1.0000
6.000 0.6603 0.01132 0.00467 0.0038 0.0322 1.0000
6.250 0.6857 0.01174 0.00508 0.0043 0.0276 1.0000
6.500 0.7114 0.01209 0.00549 0.0047 0.0254 1.0000
6.750 0.7368 0.01250 0.00591 0.0052 0.0231 1.0000
7.000 0.7618 0.01302 0.00646 0.0057 0.0209 1.0000
7.250 0.7867 0.01357 0.00708 0.0062 0.0198 1.0000
7.500 0.8118 0.01405 0.00764 0.0067 0.0192 1.0000
7.750 0.8366 0.01458 0.00827 0.0072 0.0185 1.0000
8.000 0.8611 0.01515 0.00893 0.0078 0.0179 1.0000
8.250 0.8854 0.01575 0.00961 0.0083 0.0172 1.0000
8.500 0.9097 0.01633 0.01026 0.0088 0.0165 1.0000
8.750 0.9336 0.01694 0.01094 0.0093 0.0157 1.0000
9.000 0.9565 0.01776 0.01185 0.0099 0.0150 1.0000
9.250 0.9766 0.01908 0.01334 0.0108 0.0141 1.0000
9.500 1.0004 0.01964 0.01400 0.0113 0.0138 1.0000
9.750 1.0239 0.02022 0.01469 0.0117 0.0132 1.0000
10.000 1.0467 0.02088 0.01545 0.0123 0.0125 1.0000
10.250 1.0694 0.02152 0.01619 0.0128 0.0118 1.0000
10.500 1.0919 0.02214 0.01688 0.0133 0.0111 1.0000
10.750 1.1135 0.02287 0.01768 0.0138 0.0105 1.0000
11.000 1.1311 0.02419 0.01912 0.0146 0.0098 1.0000
11.250 1.1515 0.02504 0.02013 0.0153 0.0095 1.0000
11.500 1.1719 0.02583 0.02105 0.0159 0.0089 1.0000
11.750 1.1907 0.02677 0.02213 0.0166 0.0083 1.0000
12.000 1.2082 0.02783 0.02332 0.0173 0.0078 1.0000
12.250 1.2252 0.02886 0.02446 0.0181 0.0074 1.0000
12.500 1.2407 0.02999 0.02569 0.0189 0.0070 1.0000
12.750 1.2517 0.03153 0.02735 0.0198 0.0066 1.0000
13.000 1.2588 0.03331 0.02930 0.0210 0.0063 1.0000
13.250 1.2594 0.03524 0.03141 0.0227 0.0061 1.0000
13.500 1.2515 0.03758 0.03392 0.0244 0.0059 1.0000
13.750 1.2344 0.04158 0.03811 0.0235 0.0060 1.0000
14.000 1.2129 0.04841 0.04516 0.0181 0.0059 1.0000
14.250 1.1718 0.06157 0.05857 0.0071 0.0062 1.0000
14.750 1.0205 0.10009 0.09758 -0.0172 0.0075 1.0000
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