S9032 (9%) (s9032-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: S9032 (9%) (s9032-il) Reynolds number: 500,000 Max Cl/Cd: 60.21 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s9032-il-500000.txt Download as CSV file: xf-s9032-il-500000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.750 -1.0419 0.08051 0.07761 -0.0050 1.0000 0.0123
-14.500 -1.0644 0.07188 0.06882 -0.0107 1.0000 0.0122
-14.250 -1.0827 0.06433 0.06114 -0.0160 1.0000 0.0123
-14.000 -1.1027 0.05684 0.05346 -0.0212 1.0000 0.0122
-13.750 -1.1209 0.05025 0.04667 -0.0256 1.0000 0.0122
-13.500 -1.1347 0.04514 0.04143 -0.0288 1.0000 0.0125
-13.250 -1.1424 0.04147 0.03764 -0.0304 1.0000 0.0128
-13.000 -1.1419 0.03928 0.03540 -0.0309 1.0000 0.0131
-12.750 -1.1445 0.03711 0.03312 -0.0305 1.0000 0.0135
-12.500 -1.1387 0.03605 0.03201 -0.0294 1.0000 0.0140
-12.250 -1.1409 0.03434 0.03017 -0.0273 1.0000 0.0145
-12.000 -1.1368 0.03319 0.02889 -0.0251 1.0000 0.0151
-11.750 -1.1278 0.03194 0.02747 -0.0235 1.0000 0.0157
-11.500 -1.1141 0.03107 0.02645 -0.0222 1.0000 0.0162
-11.250 -1.1124 0.02817 0.02326 -0.0202 1.0000 0.0168
-11.000 -1.1024 0.02625 0.02121 -0.0187 1.0000 0.0178
-10.750 -1.0837 0.02558 0.02050 -0.0178 1.0000 0.0186
-10.500 -1.0641 0.02493 0.01978 -0.0170 1.0000 0.0196
-10.250 -1.0444 0.02414 0.01888 -0.0161 1.0000 0.0206
-10.000 -1.0235 0.02349 0.01812 -0.0154 1.0000 0.0215
-9.750 -1.0017 0.02292 0.01742 -0.0146 1.0000 0.0221
-9.500 -0.9862 0.02089 0.01518 -0.0132 1.0000 0.0230
-9.250 -0.9686 0.01938 0.01356 -0.0120 1.0000 0.0242
-9.000 -0.9470 0.01860 0.01273 -0.0112 1.0000 0.0253
-8.750 -0.9247 0.01790 0.01196 -0.0104 1.0000 0.0264
-8.500 -0.9025 0.01714 0.01112 -0.0096 1.0000 0.0274
-8.250 -0.8799 0.01643 0.01031 -0.0087 1.0000 0.0284
-8.000 -0.8564 0.01587 0.00966 -0.0080 1.0000 0.0295
-7.750 -0.8351 0.01495 0.00864 -0.0069 1.0000 0.0310
-7.500 -0.8136 0.01409 0.00775 -0.0059 1.0000 0.0335
-7.250 -0.7898 0.01359 0.00722 -0.0052 1.0000 0.0361
-7.000 -0.7655 0.01318 0.00674 -0.0045 1.0000 0.0389
-6.750 -0.7433 0.01244 0.00599 -0.0035 1.0000 0.0448
-6.500 -0.7187 0.01212 0.00563 -0.0028 1.0000 0.0502
-6.250 -0.6957 0.01156 0.00512 -0.0019 1.0000 0.0592
-6.000 -0.6717 0.01118 0.00474 -0.0012 1.0000 0.0671
-5.750 -0.6473 0.01090 0.00445 -0.0004 1.0000 0.0749
-5.500 -0.6236 0.01050 0.00410 0.0004 1.0000 0.0855
-5.250 -0.5997 0.01016 0.00380 0.0012 1.0000 0.0971
-5.000 -0.5757 0.00983 0.00352 0.0020 1.0000 0.1109
-4.750 -0.5518 0.00952 0.00328 0.0028 1.0000 0.1282
-4.500 -0.5282 0.00919 0.00305 0.0036 1.0000 0.1505
-4.250 -0.5045 0.00888 0.00285 0.0044 1.0000 0.1747
-4.000 -0.4808 0.00860 0.00266 0.0052 1.0000 0.2003
-3.750 -0.4572 0.00832 0.00250 0.0061 1.0000 0.2277
-3.500 -0.4337 0.00807 0.00235 0.0069 1.0000 0.2547
-3.250 -0.4103 0.00783 0.00222 0.0078 1.0000 0.2832
-3.000 -0.3871 0.00761 0.00212 0.0087 1.0000 0.3134
-2.750 -0.3641 0.00741 0.00204 0.0097 1.0000 0.3449
-2.500 -0.3293 0.00718 0.00197 0.0080 0.9967 0.3870
-2.250 -0.2894 0.00692 0.00192 0.0054 0.9911 0.4359
-2.000 -0.2491 0.00666 0.00186 0.0027 0.9843 0.4882
-1.750 -0.2107 0.00642 0.00179 0.0006 0.9758 0.5340
-1.500 -0.1731 0.00620 0.00173 -0.0014 0.9659 0.5758
-1.250 -0.1386 0.00600 0.00167 -0.0025 0.9511 0.6145
-1.000 -0.1048 0.00580 0.00161 -0.0034 0.9309 0.6544
-0.750 -0.0745 0.00565 0.00155 -0.0035 0.9010 0.6948
-0.500 -0.0490 0.00557 0.00151 -0.0024 0.8650 0.7317
-0.250 -0.0244 0.00555 0.00148 -0.0012 0.8300 0.7638
0.000 0.0000 0.00554 0.00147 0.0000 0.7965 0.7965
0.250 0.0244 0.00555 0.00148 0.0012 0.7638 0.8299
0.500 0.0490 0.00557 0.00151 0.0024 0.7316 0.8650
0.750 0.0745 0.00565 0.00155 0.0035 0.6947 0.9010
1.000 0.1048 0.00581 0.00161 0.0035 0.6541 0.9308
1.250 0.1386 0.00600 0.00167 0.0025 0.6142 0.9511
1.500 0.1731 0.00620 0.00173 0.0013 0.5759 0.9658
1.750 0.2107 0.00642 0.00179 -0.0006 0.5340 0.9757
2.000 0.2489 0.00666 0.00186 -0.0027 0.4882 0.9842
2.250 0.2894 0.00692 0.00192 -0.0054 0.4353 0.9910
2.500 0.3292 0.00718 0.00197 -0.0080 0.3871 0.9966
2.750 0.3646 0.00741 0.00204 -0.0097 0.3449 1.0000
3.000 0.3876 0.00762 0.00212 -0.0088 0.3131 1.0000
3.250 0.4108 0.00783 0.00222 -0.0079 0.2829 1.0000
3.500 0.4342 0.00807 0.00235 -0.0070 0.2545 1.0000
3.750 0.4578 0.00832 0.00250 -0.0062 0.2275 1.0000
4.250 0.5050 0.00889 0.00285 -0.0045 0.1743 1.0000
4.500 0.5287 0.00919 0.00305 -0.0037 0.1502 1.0000
4.750 0.5524 0.00953 0.00328 -0.0029 0.1281 1.0000
5.000 0.5763 0.00983 0.00353 -0.0021 0.1107 1.0000
5.250 0.6002 0.01016 0.00380 -0.0013 0.0969 1.0000
5.500 0.6241 0.01050 0.00410 -0.0005 0.0854 1.0000
5.750 0.6478 0.01090 0.00445 0.0003 0.0748 1.0000
6.000 0.6721 0.01119 0.00474 0.0011 0.0671 1.0000
6.250 0.6960 0.01156 0.00512 0.0018 0.0591 1.0000
6.500 0.7190 0.01212 0.00563 0.0027 0.0502 1.0000
6.750 0.7435 0.01244 0.00599 0.0034 0.0447 1.0000
7.000 0.7656 0.01318 0.00675 0.0045 0.0389 1.0000
7.250 0.7899 0.01359 0.00721 0.0052 0.0361 1.0000
7.500 0.8135 0.01409 0.00775 0.0060 0.0335 1.0000
7.750 0.8351 0.01493 0.00862 0.0070 0.0311 1.0000
8.000 0.8560 0.01589 0.00967 0.0081 0.0295 1.0000
8.250 0.8795 0.01643 0.01032 0.0088 0.0284 1.0000
8.500 0.9020 0.01714 0.01111 0.0097 0.0274 1.0000
8.750 0.9242 0.01789 0.01196 0.0105 0.0263 1.0000
9.000 0.9463 0.01861 0.01274 0.0114 0.0253 1.0000
9.250 0.9679 0.01937 0.01355 0.0122 0.0242 1.0000
9.500 0.9857 0.02084 0.01512 0.0134 0.0231 1.0000
9.750 1.0003 0.02302 0.01753 0.0148 0.0222 1.0000
10.000 1.0227 0.02344 0.01807 0.0155 0.0215 1.0000
10.250 1.0434 0.02411 0.01886 0.0164 0.0206 1.0000
10.500 1.0634 0.02481 0.01966 0.0172 0.0196 1.0000
10.750 1.0825 0.02556 0.02048 0.0181 0.0187 1.0000
11.000 1.1010 0.02623 0.02119 0.0189 0.0178 1.0000
11.250 1.1119 0.02801 0.02309 0.0204 0.0169 1.0000
11.500 1.1116 0.03119 0.02658 0.0226 0.0162 1.0000
11.750 1.1255 0.03201 0.02754 0.0239 0.0157 1.0000
12.000 1.1352 0.03313 0.02883 0.0254 0.0152 1.0000
12.250 1.1371 0.03450 0.03034 0.0278 0.0146 1.0000
12.500 1.1378 0.03593 0.03188 0.0297 0.0141 1.0000
12.750 1.1424 0.03712 0.03314 0.0308 0.0135 1.0000
13.000 1.1469 0.03853 0.03458 0.0312 0.0131 1.0000
13.250 1.1366 0.04199 0.03821 0.0306 0.0129 1.0000
13.500 1.1324 0.04524 0.04153 0.0290 0.0126 1.0000
13.750 1.1223 0.04982 0.04623 0.0261 0.0122 1.0000
14.000 1.0982 0.05732 0.05394 0.0210 0.0120 1.0000
14.250 1.0860 0.06351 0.06029 0.0167 0.0123 1.0000
14.500 1.0636 0.07182 0.06878 0.0109 0.0123 1.0000
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Polar data table (+)
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