S9027 (8%) (s9027-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: S9027 (8%) (s9027-il) Reynolds number: 500,000 Max Cl/Cd: 57.89 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s9027-il-500000.txt Download as CSV file: xf-s9027-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: S9027 (8%)
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
------ -------- --------- --------- -------- -------- --------
-12.750 -1.0148 0.05721 0.05432 -0.0176 1.0000 0.0126
-12.500 -1.0392 0.04931 0.04621 -0.0242 1.0000 0.0124
-12.250 -1.0548 0.04452 0.04123 -0.0271 1.0000 0.0125
-12.000 -1.0620 0.04179 0.03832 -0.0273 1.0000 0.0127
-11.750 -1.0714 0.03937 0.03572 -0.0256 1.0000 0.0128
-11.500 -1.0919 0.03527 0.03128 -0.0228 1.0000 0.0130
-11.250 -1.0996 0.03135 0.02704 -0.0206 1.0000 0.0136
-11.000 -1.0879 0.02979 0.02537 -0.0195 1.0000 0.0142
-10.750 -1.0706 0.02892 0.02444 -0.0187 1.0000 0.0149
-10.500 -1.0528 0.02801 0.02340 -0.0178 1.0000 0.0157
-10.250 -1.0345 0.02698 0.02223 -0.0169 1.0000 0.0167
-10.000 -1.0145 0.02618 0.02127 -0.0161 1.0000 0.0175
-9.750 -0.9967 0.02477 0.01963 -0.0151 1.0000 0.0182
-9.500 -0.9849 0.02186 0.01646 -0.0136 1.0000 0.0194
-9.250 -0.9639 0.02095 0.01548 -0.0129 1.0000 0.0204
-9.000 -0.9415 0.02026 0.01471 -0.0122 1.0000 0.0215
-8.750 -0.9187 0.01959 0.01392 -0.0115 1.0000 0.0228
-8.500 -0.8957 0.01887 0.01310 -0.0108 1.0000 0.0238
-8.250 -0.8722 0.01819 0.01230 -0.0101 1.0000 0.0244
-8.000 -0.8527 0.01660 0.01054 -0.0090 1.0000 0.0258
-7.750 -0.8309 0.01561 0.00949 -0.0081 1.0000 0.0275
-7.500 -0.8073 0.01498 0.00881 -0.0074 1.0000 0.0290
-7.250 -0.7835 0.01438 0.00814 -0.0067 1.0000 0.0306
-7.000 -0.7590 0.01390 0.00758 -0.0060 1.0000 0.0324
-6.750 -0.7358 0.01317 0.00677 -0.0051 1.0000 0.0346
-6.500 -0.7126 0.01248 0.00607 -0.0043 1.0000 0.0385
-6.250 -0.6878 0.01209 0.00563 -0.0036 1.0000 0.0425
-6.000 -0.6642 0.01147 0.00502 -0.0028 1.0000 0.0495
-5.750 -0.6392 0.01117 0.00467 -0.0022 1.0000 0.0557
-5.500 -0.6151 0.01071 0.00425 -0.0014 1.0000 0.0654
-5.250 -0.5907 0.01034 0.00392 -0.0007 1.0000 0.0748
-5.000 -0.5661 0.01003 0.00362 0.0000 1.0000 0.0848
-4.750 -0.5416 0.00971 0.00333 0.0007 1.0000 0.0969
-4.500 -0.5172 0.00939 0.00308 0.0015 1.0000 0.1121
-4.250 -0.4929 0.00908 0.00285 0.0022 1.0000 0.1312
-4.000 -0.4686 0.00878 0.00265 0.0029 1.0000 0.1542
-3.750 -0.4443 0.00849 0.00247 0.0036 1.0000 0.1799
-3.250 -0.3958 0.00796 0.00214 0.0051 1.0000 0.2336
-3.000 -0.3718 0.00769 0.00201 0.0059 1.0000 0.2665
-2.750 -0.3479 0.00743 0.00189 0.0067 1.0000 0.3026
-2.500 -0.3242 0.00720 0.00180 0.0075 1.0000 0.3391
-2.250 -0.3005 0.00697 0.00173 0.0084 1.0000 0.3785
-2.000 -0.2774 0.00674 0.00168 0.0093 1.0000 0.4245
-1.750 -0.2459 0.00648 0.00165 0.0084 0.9974 0.4832
-1.500 -0.2057 0.00617 0.00163 0.0057 0.9911 0.5559
-1.250 -0.1657 0.00591 0.00161 0.0032 0.9839 0.6150
-1.000 -0.1283 0.00564 0.00158 0.0013 0.9740 0.6762
-0.750 -0.0926 0.00539 0.00155 0.0000 0.9596 0.7315
-0.500 -0.0578 0.00517 0.00153 -0.0010 0.9411 0.7863
-0.250 -0.0269 0.00500 0.00150 -0.0010 0.9141 0.8373
0.000 0.0000 0.00494 0.00149 0.0000 0.8786 0.8789
0.250 0.0269 0.00500 0.00150 0.0010 0.8374 0.9141
0.500 0.0578 0.00517 0.00153 0.0010 0.7864 0.9412
0.750 0.0925 0.00539 0.00155 0.0000 0.7313 0.9596
1.000 0.1283 0.00564 0.00158 -0.0013 0.6761 0.9740
1.250 0.1657 0.00591 0.00161 -0.0032 0.6154 0.9839
1.500 0.2058 0.00617 0.00163 -0.0057 0.5559 0.9912
1.750 0.2460 0.00647 0.00165 -0.0084 0.4834 0.9975
2.000 0.2770 0.00674 0.00168 -0.0092 0.4242 1.0000
2.250 0.3002 0.00697 0.00173 -0.0083 0.3786 1.0000
2.500 0.3238 0.00719 0.00180 -0.0074 0.3394 1.0000
2.750 0.3475 0.00743 0.00189 -0.0066 0.3027 1.0000
3.000 0.3714 0.00768 0.00201 -0.0058 0.2667 1.0000
3.250 0.3954 0.00796 0.00214 -0.0050 0.2338 1.0000
3.500 0.4196 0.00822 0.00229 -0.0043 0.2059 1.0000
3.750 0.4439 0.00848 0.00246 -0.0035 0.1802 1.0000
4.000 0.4681 0.00877 0.00265 -0.0028 0.1545 1.0000
4.250 0.4924 0.00908 0.00285 -0.0021 0.1314 1.0000
4.500 0.5168 0.00939 0.00307 -0.0014 0.1122 1.0000
4.750 0.5412 0.00971 0.00333 -0.0006 0.0970 1.0000
5.000 0.5657 0.01002 0.00362 0.0001 0.0850 1.0000
5.250 0.5903 0.01034 0.00392 0.0008 0.0747 1.0000
5.500 0.6148 0.01070 0.00425 0.0015 0.0654 1.0000
5.750 0.6389 0.01116 0.00466 0.0022 0.0558 1.0000
6.000 0.6640 0.01147 0.00502 0.0028 0.0495 1.0000
6.250 0.6876 0.01209 0.00563 0.0037 0.0425 1.0000
6.500 0.7125 0.01248 0.00607 0.0043 0.0384 1.0000
6.750 0.7357 0.01320 0.00680 0.0051 0.0344 1.0000
7.000 0.7591 0.01389 0.00757 0.0060 0.0323 1.0000
7.250 0.7836 0.01438 0.00813 0.0066 0.0306 1.0000
7.500 0.8075 0.01497 0.00881 0.0073 0.0290 1.0000
7.750 0.8312 0.01561 0.00949 0.0080 0.0275 1.0000
8.000 0.8531 0.01659 0.01054 0.0089 0.0259 1.0000
8.250 0.8726 0.01822 0.01233 0.0100 0.0245 1.0000
8.500 0.8962 0.01889 0.01311 0.0107 0.0238 1.0000
8.750 0.9192 0.01963 0.01396 0.0114 0.0228 1.0000
9.000 0.9421 0.02032 0.01477 0.0121 0.0215 1.0000
9.250 0.9647 0.02096 0.01548 0.0127 0.0204 1.0000
9.500 0.9859 0.02187 0.01646 0.0134 0.0194 1.0000
9.750 0.9967 0.02504 0.01993 0.0150 0.0181 1.0000
10.000 1.0155 0.02622 0.02132 0.0159 0.0175 1.0000
10.250 1.0358 0.02699 0.02223 0.0167 0.0166 1.0000
10.500 1.0549 0.02785 0.02322 0.0175 0.0156 1.0000
10.750 1.0728 0.02875 0.02425 0.0183 0.0148 1.0000
11.000 1.0890 0.02982 0.02540 0.0193 0.0142 1.0000
11.250 1.1005 0.03143 0.02712 0.0204 0.0136 1.0000
11.500 1.0917 0.03550 0.03153 0.0226 0.0130 1.0000
11.750 1.0744 0.03927 0.03562 0.0253 0.0127 1.0000
12.000 1.0689 0.04128 0.03781 0.0269 0.0126 1.0000
12.250 1.0465 0.04579 0.04253 0.0263 0.0127 1.0000
12.500 1.0406 0.04940 0.04631 0.0238 0.0124 1.0000
12.750 1.0137 0.05784 0.05496 0.0168 0.0126 1.0000
13.000 0.9791 0.06926 0.06656 0.0077 0.0128 1.0000
13.250 0.8829 0.09779 0.09552 -0.0117 0.0146 1.0000
13.500 0.9033 0.09708 0.09476 -0.0111 0.0140 1.0000
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Polar data table (+)
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