S9032 (9%) (s9032-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: S9032 (9%) (s9032-il) Reynolds number: 1,000,000 Max Cl/Cd: 74.23 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s9032-il-1000000.txt Download as CSV file: xf-s9032-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.500 -1.2006 0.08142 0.07872 -0.0047 1.0000 0.0057
-16.250 -1.2608 0.06640 0.06349 -0.0141 1.0000 0.0055
-16.000 -1.2980 0.05570 0.05258 -0.0211 1.0000 0.0055
-15.750 -1.3250 0.04734 0.04404 -0.0269 1.0000 0.0054
-15.500 -1.3435 0.04127 0.03779 -0.0307 1.0000 0.0054
-15.250 -1.3493 0.03770 0.03409 -0.0322 1.0000 0.0055
-15.000 -1.3599 0.03421 0.03045 -0.0329 1.0000 0.0056
-14.750 -1.3664 0.03171 0.02781 -0.0321 1.0000 0.0058
-14.500 -1.3751 0.02950 0.02547 -0.0300 1.0000 0.0060
-14.250 -1.3747 0.02810 0.02401 -0.0276 1.0000 0.0065
-14.000 -1.3700 0.02705 0.02290 -0.0251 1.0000 0.0068
-13.750 -1.3579 0.02622 0.02201 -0.0235 1.0000 0.0073
-13.500 -1.3419 0.02553 0.02126 -0.0224 1.0000 0.0078
-13.250 -1.3238 0.02494 0.02059 -0.0214 1.0000 0.0082
-13.000 -1.3089 0.02401 0.01957 -0.0201 1.0000 0.0086
-12.750 -1.2967 0.02274 0.01821 -0.0186 1.0000 0.0093
-12.500 -1.2763 0.02222 0.01767 -0.0179 1.0000 0.0098
-12.250 -1.2555 0.02170 0.01711 -0.0171 1.0000 0.0104
-12.000 -1.2341 0.02120 0.01656 -0.0164 1.0000 0.0109
-11.750 -1.2125 0.02071 0.01601 -0.0158 1.0000 0.0113
-11.500 -1.1894 0.02035 0.01560 -0.0152 1.0000 0.0117
-11.250 -1.1702 0.01951 0.01464 -0.0142 1.0000 0.0121
-11.000 -1.1537 0.01826 0.01328 -0.0130 1.0000 0.0129
-10.750 -1.1320 0.01764 0.01262 -0.0123 1.0000 0.0135
-10.500 -1.1088 0.01719 0.01215 -0.0117 1.0000 0.0141
-10.250 -1.0853 0.01676 0.01167 -0.0111 1.0000 0.0148
-10.000 -1.0618 0.01631 0.01117 -0.0106 1.0000 0.0154
-9.750 -1.0373 0.01599 0.01081 -0.0101 1.0000 0.0159
-9.500 -1.0125 0.01569 0.01046 -0.0096 1.0000 0.0162
-9.250 -0.9925 0.01469 0.00934 -0.0086 1.0000 0.0173
-9.000 -0.9702 0.01398 0.00858 -0.0078 1.0000 0.0184
-8.750 -0.9463 0.01353 0.00811 -0.0072 1.0000 0.0194
-8.500 -0.9221 0.01311 0.00765 -0.0066 1.0000 0.0202
-8.250 -0.8979 0.01267 0.00716 -0.0059 1.0000 0.0210
-8.000 -0.8735 0.01227 0.00670 -0.0053 1.0000 0.0217
-7.750 -0.8489 0.01193 0.00631 -0.0047 1.0000 0.0222
-7.500 -0.8257 0.01134 0.00565 -0.0038 1.0000 0.0240
-7.250 -0.8019 0.01089 0.00519 -0.0030 1.0000 0.0265
-7.000 -0.7775 0.01055 0.00485 -0.0023 1.0000 0.0287
-6.750 -0.7535 0.01017 0.00444 -0.0015 1.0000 0.0330
-6.500 -0.7293 0.00985 0.00415 -0.0007 1.0000 0.0387
-6.250 -0.7053 0.00951 0.00385 0.0001 1.0000 0.0459
-6.000 -0.6805 0.00930 0.00363 0.0008 1.0000 0.0503
-5.750 -0.6564 0.00900 0.00337 0.0016 1.0000 0.0577
-5.500 -0.6318 0.00879 0.00315 0.0023 1.0000 0.0627
-5.250 -0.6077 0.00851 0.00293 0.0031 1.0000 0.0724
-5.000 -0.5836 0.00826 0.00273 0.0039 1.0000 0.0832
-4.750 -0.5595 0.00803 0.00255 0.0047 1.0000 0.0951
-4.500 -0.5355 0.00780 0.00238 0.0055 1.0000 0.1078
-4.250 -0.5116 0.00758 0.00221 0.0064 1.0000 0.1222
-4.000 -0.4879 0.00736 0.00207 0.0072 1.0000 0.1412
-3.750 -0.4528 0.00709 0.00194 0.0056 0.9977 0.1691
-3.500 -0.4157 0.00684 0.00181 0.0035 0.9948 0.1979
-3.250 -0.3799 0.00661 0.00170 0.0018 0.9914 0.2252
-3.000 -0.3434 0.00639 0.00159 0.0000 0.9865 0.2531
-2.750 -0.3041 0.00617 0.00148 -0.0025 0.9822 0.2834
-2.500 -0.2718 0.00596 0.00138 -0.0034 0.9714 0.3133
-2.250 -0.2388 0.00576 0.00128 -0.0044 0.9572 0.3446
-2.000 -0.2076 0.00554 0.00118 -0.0049 0.9354 0.3832
-1.750 -0.1808 0.00537 0.00109 -0.0044 0.9039 0.4260
-1.500 -0.1558 0.00531 0.00102 -0.0035 0.8653 0.4586
-1.250 -0.1309 0.00528 0.00096 -0.0026 0.8243 0.4922
-1.000 -0.1051 0.00525 0.00091 -0.0020 0.7889 0.5248
-0.750 -0.0788 0.00523 0.00088 -0.0015 0.7572 0.5552
-0.500 -0.0525 0.00521 0.00086 -0.0010 0.7261 0.5889
-0.250 -0.0262 0.00516 0.00085 -0.0005 0.6973 0.6280
0.000 0.0000 0.00513 0.00085 0.0000 0.6667 0.6667
0.250 0.0262 0.00516 0.00085 0.0005 0.6280 0.6973
0.500 0.0525 0.00521 0.00086 0.0010 0.5892 0.7259
0.750 0.0788 0.00523 0.00088 0.0015 0.5552 0.7570
1.000 0.1051 0.00525 0.00091 0.0020 0.5247 0.7889
1.250 0.1309 0.00528 0.00096 0.0026 0.4924 0.8243
1.500 0.1558 0.00531 0.00102 0.0035 0.4584 0.8651
1.750 0.1808 0.00537 0.00109 0.0044 0.4257 0.9040
2.000 0.2076 0.00554 0.00118 0.0049 0.3832 0.9355
2.250 0.2387 0.00576 0.00128 0.0044 0.3447 0.9571
2.500 0.2717 0.00596 0.00138 0.0034 0.3133 0.9713
2.750 0.3040 0.00617 0.00148 0.0025 0.2836 0.9822
3.000 0.3433 0.00639 0.00159 0.0001 0.2530 0.9864
3.250 0.3797 0.00661 0.00170 -0.0018 0.2253 0.9912
3.500 0.4155 0.00684 0.00181 -0.0035 0.1981 0.9947
3.750 0.4526 0.00709 0.00194 -0.0056 0.1698 0.9976
4.000 0.4886 0.00736 0.00207 -0.0074 0.1405 1.0000
4.250 0.5123 0.00758 0.00222 -0.0065 0.1220 1.0000
4.500 0.5362 0.00781 0.00238 -0.0057 0.1076 1.0000
4.750 0.5602 0.00803 0.00255 -0.0049 0.0950 1.0000
5.000 0.5843 0.00826 0.00273 -0.0040 0.0831 1.0000
5.250 0.6084 0.00851 0.00293 -0.0032 0.0724 1.0000
5.500 0.6325 0.00879 0.00316 -0.0024 0.0625 1.0000
5.750 0.6571 0.00900 0.00337 -0.0017 0.0576 1.0000
6.000 0.6811 0.00930 0.00363 -0.0009 0.0503 1.0000
6.250 0.7059 0.00951 0.00385 -0.0002 0.0459 1.0000
6.500 0.7299 0.00985 0.00416 0.0006 0.0386 1.0000
6.750 0.7540 0.01018 0.00446 0.0014 0.0328 1.0000
7.000 0.7780 0.01055 0.00485 0.0022 0.0287 1.0000
7.250 0.8023 0.01089 0.00519 0.0029 0.0264 1.0000
7.500 0.8259 0.01135 0.00565 0.0037 0.0240 1.0000
7.750 0.8489 0.01194 0.00632 0.0046 0.0222 1.0000
8.000 0.8735 0.01228 0.00670 0.0053 0.0217 1.0000
8.250 0.8977 0.01268 0.00717 0.0060 0.0210 1.0000
8.500 0.9218 0.01310 0.00764 0.0066 0.0202 1.0000
8.750 0.9459 0.01353 0.00810 0.0072 0.0193 1.0000
9.000 0.9697 0.01399 0.00859 0.0079 0.0184 1.0000
9.250 0.9916 0.01472 0.00937 0.0087 0.0171 1.0000
9.500 1.0118 0.01570 0.01047 0.0098 0.0163 1.0000
9.750 1.0366 0.01597 0.01079 0.0102 0.0159 1.0000
10.000 1.0609 0.01632 0.01118 0.0107 0.0154 1.0000
10.250 1.0847 0.01672 0.01163 0.0113 0.0148 1.0000
10.500 1.1078 0.01719 0.01214 0.0119 0.0142 1.0000
10.750 1.1310 0.01764 0.01262 0.0125 0.0135 1.0000
11.000 1.1528 0.01823 0.01325 0.0132 0.0129 1.0000
11.250 1.1696 0.01943 0.01455 0.0144 0.0121 1.0000
11.500 1.1880 0.02036 0.01561 0.0155 0.0117 1.0000
11.750 1.2110 0.02072 0.01602 0.0160 0.0114 1.0000
12.000 1.2327 0.02120 0.01657 0.0167 0.0109 1.0000
12.250 1.2538 0.02171 0.01713 0.0174 0.0104 1.0000
12.500 1.2746 0.02222 0.01768 0.0182 0.0099 1.0000
12.750 1.2950 0.02275 0.01823 0.0189 0.0093 1.0000
13.000 1.3086 0.02387 0.01942 0.0203 0.0086 1.0000
13.250 1.3212 0.02499 0.02065 0.0218 0.0082 1.0000
13.500 1.3396 0.02554 0.02127 0.0227 0.0078 1.0000
13.750 1.3561 0.02618 0.02197 0.0239 0.0073 1.0000
14.000 1.3684 0.02697 0.02281 0.0255 0.0068 1.0000
14.250 1.3733 0.02800 0.02391 0.0280 0.0066 1.0000
14.500 1.3738 0.02940 0.02537 0.0303 0.0061 1.0000
14.750 1.3657 0.03157 0.02768 0.0324 0.0059 1.0000
15.000 1.3486 0.03505 0.03133 0.0331 0.0057 1.0000
15.250 1.3489 0.03750 0.03388 0.0326 0.0055 1.0000
15.500 1.3389 0.04162 0.03815 0.0307 0.0054 1.0000
15.750 1.3244 0.04715 0.04384 0.0273 0.0053 1.0000
16.000 1.2981 0.05537 0.05225 0.0216 0.0055 1.0000
16.250 1.2500 0.06804 0.06514 0.0131 0.0057 1.0000
16.500 1.2122 0.07898 0.07625 0.0064 0.0058 1.0000
16.750 1.1818 0.08859 0.08600 0.0008 0.0061 1.0000
17.000 1.1369 0.10107 0.09867 -0.0066 0.0065 1.0000
17.250 1.0874 0.11538 0.11315 -0.0151 0.0067 1.0000
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Polar data table (+)
Polar graphs
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