S9032 (9%) (s9032-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: S9032 (9%) (s9032-il) Reynolds number: 500,000 Max Cl/Cd: 61.02 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s9032-il-500000-n5.txt Download as CSV file: xf-s9032-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: S9032 (9%)
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
------ -------- --------- --------- -------- -------- --------
-16.000 -1.0599 0.10032 0.09736 0.0080 1.0000 0.0083
-15.750 -1.1028 0.08790 0.08481 0.0006 1.0000 0.0080
-15.500 -1.1488 0.07518 0.07194 -0.0071 1.0000 0.0076
-15.250 -1.1786 0.06556 0.06216 -0.0132 1.0000 0.0076
-15.000 -1.2110 0.05566 0.05208 -0.0199 1.0000 0.0073
-14.750 -1.2281 0.04893 0.04517 -0.0246 1.0000 0.0074
-14.500 -1.2411 0.04356 0.03962 -0.0280 1.0000 0.0075
-14.250 -1.2468 0.03986 0.03576 -0.0298 1.0000 0.0078
-14.000 -1.2543 0.03655 0.03228 -0.0305 1.0000 0.0079
-13.750 -1.2590 0.03406 0.02963 -0.0300 1.0000 0.0081
-13.500 -1.2570 0.03243 0.02787 -0.0288 1.0000 0.0084
-13.250 -1.2588 0.03073 0.02607 -0.0266 1.0000 0.0087
-13.000 -1.2542 0.02954 0.02480 -0.0245 1.0000 0.0091
-12.750 -1.2444 0.02846 0.02362 -0.0228 1.0000 0.0095
-12.500 -1.2295 0.02762 0.02270 -0.0217 1.0000 0.0100
-12.250 -1.2156 0.02659 0.02155 -0.0204 1.0000 0.0104
-12.000 -1.1995 0.02569 0.02053 -0.0193 1.0000 0.0110
-11.750 -1.1825 0.02480 0.01952 -0.0183 1.0000 0.0114
-11.500 -1.1642 0.02399 0.01859 -0.0173 1.0000 0.0117
-11.250 -1.1485 0.02285 0.01730 -0.0161 1.0000 0.0122
-11.000 -1.1303 0.02191 0.01630 -0.0152 1.0000 0.0129
-10.750 -1.1097 0.02124 0.01557 -0.0144 1.0000 0.0136
-10.500 -1.0882 0.02064 0.01491 -0.0137 1.0000 0.0143
-10.250 -1.0666 0.02002 0.01420 -0.0130 1.0000 0.0151
-10.000 -1.0447 0.01939 0.01347 -0.0123 1.0000 0.0157
-9.750 -1.0225 0.01879 0.01277 -0.0116 1.0000 0.0161
-9.500 -1.0015 0.01799 0.01186 -0.0107 1.0000 0.0167
-9.250 -0.9806 0.01713 0.01093 -0.0098 1.0000 0.0177
-9.000 -0.9582 0.01649 0.01023 -0.0091 1.0000 0.0184
-8.750 -0.9352 0.01591 0.00959 -0.0084 1.0000 0.0192
-8.500 -0.9117 0.01539 0.00900 -0.0078 1.0000 0.0201
-8.250 -0.8879 0.01491 0.00845 -0.0071 1.0000 0.0211
-8.000 -0.8640 0.01445 0.00791 -0.0065 1.0000 0.0220
-7.750 -0.8404 0.01393 0.00733 -0.0057 1.0000 0.0231
-7.500 -0.8167 0.01341 0.00679 -0.0050 1.0000 0.0252
-7.250 -0.7925 0.01299 0.00635 -0.0044 1.0000 0.0275
-7.000 -0.7680 0.01263 0.00595 -0.0037 1.0000 0.0298
-6.750 -0.7440 0.01221 0.00553 -0.0031 1.0000 0.0342
-6.500 -0.7195 0.01189 0.00520 -0.0024 1.0000 0.0385
-6.250 -0.6952 0.01154 0.00485 -0.0017 1.0000 0.0436
-6.000 -0.6708 0.01124 0.00456 -0.0010 1.0000 0.0492
-5.750 -0.6466 0.01093 0.00426 -0.0003 1.0000 0.0551
-5.500 -0.6223 0.01065 0.00398 0.0005 1.0000 0.0611
-5.250 -0.5980 0.01037 0.00372 0.0012 1.0000 0.0682
-5.000 -0.5737 0.01012 0.00348 0.0019 1.0000 0.0762
-4.750 -0.5495 0.00985 0.00326 0.0027 1.0000 0.0876
-4.250 -0.5017 0.00929 0.00284 0.0043 1.0000 0.1178
-4.000 -0.4734 0.00902 0.00266 0.0041 0.9983 0.1360
-3.750 -0.4375 0.00878 0.00249 0.0023 0.9936 0.1557
-3.500 -0.4030 0.00855 0.00232 0.0009 0.9869 0.1742
-3.250 -0.3678 0.00832 0.00217 -0.0007 0.9792 0.1952
-3.000 -0.3337 0.00809 0.00204 -0.0020 0.9690 0.2178
-2.750 -0.3005 0.00785 0.00190 -0.0031 0.9551 0.2464
-2.500 -0.2661 0.00761 0.00177 -0.0045 0.9355 0.2790
-2.250 -0.2332 0.00737 0.00164 -0.0054 0.9057 0.3175
-2.000 -0.2059 0.00725 0.00152 -0.0049 0.8684 0.3476
-1.750 -0.1805 0.00718 0.00143 -0.0042 0.8316 0.3764
-1.500 -0.1550 0.00714 0.00135 -0.0034 0.7979 0.4025
-1.250 -0.1292 0.00709 0.00129 -0.0028 0.7668 0.4315
-1.000 -0.1036 0.00703 0.00123 -0.0022 0.7353 0.4647
-0.750 -0.0780 0.00698 0.00120 -0.0016 0.7000 0.5040
-0.500 -0.0525 0.00695 0.00117 -0.0010 0.6643 0.5424
-0.250 -0.0263 0.00694 0.00115 -0.0005 0.6330 0.5720
0.000 0.0000 0.00693 0.00114 0.0000 0.6023 0.6024
0.250 0.0263 0.00694 0.00115 0.0005 0.5719 0.6329
0.500 0.0525 0.00695 0.00117 0.0010 0.5422 0.6643
0.750 0.0780 0.00698 0.00120 0.0016 0.5037 0.7000
1.000 0.1036 0.00704 0.00123 0.0022 0.4643 0.7351
1.250 0.1292 0.00709 0.00129 0.0028 0.4312 0.7669
1.500 0.1550 0.00713 0.00135 0.0035 0.4026 0.7980
1.750 0.1805 0.00718 0.00143 0.0042 0.3765 0.8316
2.000 0.2059 0.00725 0.00152 0.0049 0.3479 0.8681
2.250 0.2332 0.00738 0.00164 0.0054 0.3171 0.9058
2.500 0.2661 0.00761 0.00177 0.0045 0.2786 0.9356
2.750 0.3005 0.00785 0.00190 0.0031 0.2468 0.9550
3.250 0.3678 0.00832 0.00218 0.0007 0.1952 0.9790
3.500 0.4028 0.00855 0.00232 -0.0008 0.1742 0.9867
3.750 0.4373 0.00878 0.00249 -0.0023 0.1558 0.9935
4.000 0.4732 0.00902 0.00266 -0.0041 0.1360 0.9981
4.250 0.5023 0.00929 0.00284 -0.0044 0.1174 1.0000
4.500 0.5261 0.00957 0.00304 -0.0036 0.1016 1.0000
4.750 0.5501 0.00985 0.00326 -0.0028 0.0876 1.0000
5.000 0.5742 0.01012 0.00349 -0.0021 0.0760 1.0000
5.250 0.5986 0.01037 0.00372 -0.0013 0.0681 1.0000
5.500 0.6228 0.01065 0.00398 -0.0006 0.0611 1.0000
5.750 0.6471 0.01093 0.00426 0.0002 0.0549 1.0000
6.000 0.6713 0.01124 0.00456 0.0009 0.0492 1.0000
6.250 0.6956 0.01154 0.00485 0.0016 0.0436 1.0000
6.500 0.7198 0.01189 0.00520 0.0023 0.0385 1.0000
6.750 0.7442 0.01221 0.00554 0.0030 0.0341 1.0000
7.000 0.7682 0.01263 0.00595 0.0037 0.0298 1.0000
7.250 0.7926 0.01299 0.00635 0.0044 0.0274 1.0000
7.500 0.8166 0.01341 0.00680 0.0050 0.0252 1.0000
7.750 0.8403 0.01392 0.00732 0.0058 0.0232 1.0000
8.000 0.8637 0.01445 0.00791 0.0065 0.0219 1.0000
8.250 0.8876 0.01491 0.00846 0.0072 0.0211 1.0000
8.500 0.9113 0.01539 0.00900 0.0078 0.0201 1.0000
8.750 0.9347 0.01591 0.00958 0.0085 0.0192 1.0000
9.000 0.9576 0.01648 0.01022 0.0092 0.0185 1.0000
9.250 0.9799 0.01713 0.01093 0.0100 0.0177 1.0000
9.500 1.0008 0.01797 0.01184 0.0109 0.0168 1.0000
9.750 1.0216 0.01879 0.01277 0.0118 0.0162 1.0000
10.000 1.0438 0.01937 0.01346 0.0125 0.0157 1.0000
10.250 1.0656 0.02000 0.01418 0.0132 0.0151 1.0000
10.500 1.0874 0.02059 0.01485 0.0139 0.0143 1.0000
10.750 1.1086 0.02123 0.01556 0.0147 0.0136 1.0000
11.000 1.1292 0.02189 0.01628 0.0154 0.0129 1.0000
11.250 1.1474 0.02280 0.01726 0.0164 0.0123 1.0000
11.500 1.1626 0.02401 0.01860 0.0176 0.0117 1.0000
11.750 1.1810 0.02479 0.01951 0.0186 0.0114 1.0000
12.000 1.1981 0.02566 0.02050 0.0196 0.0110 1.0000
12.250 1.2135 0.02661 0.02158 0.0208 0.0105 1.0000
12.500 1.2284 0.02754 0.02261 0.0220 0.0100 1.0000
12.750 1.2426 0.02843 0.02359 0.0232 0.0095 1.0000
13.000 1.2537 0.02941 0.02465 0.0247 0.0090 1.0000
13.250 1.2563 0.03073 0.02607 0.0271 0.0088 1.0000
13.500 1.2553 0.03239 0.02783 0.0291 0.0084 1.0000
13.750 1.2570 0.03405 0.02961 0.0304 0.0081 1.0000
14.000 1.2547 0.03633 0.03205 0.0309 0.0079 1.0000
14.250 1.2463 0.03969 0.03559 0.0301 0.0078 1.0000
14.500 1.2381 0.04373 0.03979 0.0281 0.0077 1.0000
14.750 1.2234 0.04941 0.04565 0.0244 0.0076 1.0000
15.000 1.2009 0.05714 0.05359 0.0190 0.0076 1.0000
15.250 1.1818 0.06470 0.06130 0.0139 0.0075 1.0000
15.500 1.1433 0.07593 0.07270 0.0068 0.0078 1.0000
15.750 1.1028 0.08767 0.08459 -0.0004 0.0080 1.0000
16.000 1.0616 0.09978 0.09681 -0.0076 0.0083 1.0000
16.250 1.0278 0.11103 0.10820 -0.0141 0.0085 1.0000
16.500 0.9956 0.12275 0.12005 -0.0208 0.0086 1.0000
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Polar data table (+)
Polar graphs
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