S9027 (8%) (s9027-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: S9027 (8%) (s9027-il) Reynolds number: 1,000,000 Max Cl/Cd: 73.13 at α=7.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s9027-il-1000000-n5.txt Download as CSV file: xf-s9027-il-1000000-n5.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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.500 -1.1103 0.10448 0.10215 0.0123 1.0000 0.0041
-16.250 -1.2226 0.07864 0.07604 -0.0035 1.0000 0.0037
-16.000 -1.3045 0.05857 0.05569 -0.0169 1.0000 0.0035
-15.750 -1.3424 0.04732 0.04419 -0.0256 1.0000 0.0035
-15.500 -1.3629 0.04087 0.03756 -0.0300 1.0000 0.0035
-15.250 -1.3770 0.03670 0.03323 -0.0316 1.0000 0.0035
-15.000 -1.3860 0.03389 0.03028 -0.0312 1.0000 0.0036
-14.750 -1.3924 0.03179 0.02805 -0.0295 1.0000 0.0036
-14.500 -1.3951 0.03022 0.02635 -0.0269 1.0000 0.0037
-14.250 -1.3929 0.02886 0.02488 -0.0244 1.0000 0.0038
-14.000 -1.3840 0.02756 0.02345 -0.0228 1.0000 0.0039
-13.750 -1.3723 0.02636 0.02212 -0.0214 1.0000 0.0040
-13.500 -1.3596 0.02512 0.02078 -0.0201 1.0000 0.0043
-13.250 -1.3448 0.02400 0.01956 -0.0189 1.0000 0.0046
-13.000 -1.3279 0.02303 0.01850 -0.0179 1.0000 0.0048
-12.750 -1.3097 0.02214 0.01753 -0.0170 1.0000 0.0051
-12.500 -1.2906 0.02132 0.01663 -0.0161 1.0000 0.0054
-12.250 -1.2706 0.02054 0.01577 -0.0153 1.0000 0.0058
-12.000 -1.2498 0.01984 0.01497 -0.0146 1.0000 0.0061
-11.750 -1.2290 0.01909 0.01414 -0.0139 1.0000 0.0065
-11.500 -1.2073 0.01843 0.01344 -0.0132 1.0000 0.0070
-11.250 -1.1849 0.01785 0.01281 -0.0126 1.0000 0.0075
-11.000 -1.1619 0.01732 0.01223 -0.0120 1.0000 0.0081
-10.750 -1.1385 0.01684 0.01168 -0.0115 1.0000 0.0086
-10.500 -1.1147 0.01640 0.01118 -0.0109 1.0000 0.0089
-10.250 -1.0918 0.01579 0.01050 -0.0103 1.0000 0.0095
-10.000 -1.0683 0.01525 0.00991 -0.0098 1.0000 0.0102
-9.750 -1.0442 0.01480 0.00944 -0.0093 1.0000 0.0108
-9.500 -1.0197 0.01439 0.00899 -0.0088 1.0000 0.0114
-9.250 -0.9951 0.01400 0.00856 -0.0083 1.0000 0.0120
-9.000 -0.9704 0.01361 0.00812 -0.0078 1.0000 0.0124
-8.750 -0.9455 0.01325 0.00770 -0.0073 1.0000 0.0127
-8.500 -0.9209 0.01281 0.00720 -0.0068 1.0000 0.0132
-8.250 -0.8966 0.01232 0.00666 -0.0062 1.0000 0.0142
-8.000 -0.8717 0.01193 0.00625 -0.0057 1.0000 0.0151
-7.750 -0.8467 0.01158 0.00588 -0.0052 1.0000 0.0160
-7.500 -0.8215 0.01126 0.00553 -0.0047 1.0000 0.0168
-7.250 -0.7963 0.01095 0.00518 -0.0041 1.0000 0.0175
-7.000 -0.7710 0.01067 0.00485 -0.0036 1.0000 0.0179
-6.750 -0.7462 0.01032 0.00448 -0.0030 1.0000 0.0199
-6.500 -0.7213 0.01001 0.00418 -0.0024 1.0000 0.0221
-6.250 -0.6962 0.00974 0.00391 -0.0017 1.0000 0.0240
-6.000 -0.6713 0.00947 0.00364 -0.0011 1.0000 0.0273
-5.750 -0.6465 0.00920 0.00339 -0.0004 1.0000 0.0316
-5.500 -0.6215 0.00896 0.00316 0.0002 1.0000 0.0361
-5.250 -0.5967 0.00872 0.00295 0.0009 1.0000 0.0414
-5.000 -0.5716 0.00853 0.00276 0.0016 1.0000 0.0452
-4.750 -0.5468 0.00831 0.00256 0.0023 1.0000 0.0510
-4.500 -0.5181 0.00812 0.00239 0.0021 0.9990 0.0567
-4.250 -0.4839 0.00790 0.00222 0.0008 0.9958 0.0663
-4.000 -0.4495 0.00769 0.00206 -0.0007 0.9921 0.0770
-3.750 -0.4162 0.00747 0.00190 -0.0018 0.9863 0.0909
-3.500 -0.3837 0.00723 0.00176 -0.0028 0.9795 0.1103
-3.000 -0.3175 0.00686 0.00149 -0.0049 0.9471 0.1400
-2.750 -0.2882 0.00674 0.00136 -0.0049 0.9095 0.1579
-2.500 -0.2633 0.00670 0.00125 -0.0040 0.8669 0.1760
-2.250 -0.2381 0.00669 0.00115 -0.0032 0.8245 0.1922
-2.000 -0.2121 0.00667 0.00106 -0.0027 0.7857 0.2105
-1.750 -0.1860 0.00666 0.00099 -0.0022 0.7448 0.2306
-1.500 -0.1601 0.00664 0.00092 -0.0017 0.6958 0.2619
-1.250 -0.1339 0.00658 0.00085 -0.0013 0.6524 0.3018
-1.000 -0.1072 0.00657 0.00081 -0.0010 0.6135 0.3279
-0.750 -0.0803 0.00657 0.00077 -0.0008 0.5763 0.3530
-0.500 -0.0534 0.00656 0.00075 -0.0005 0.5393 0.3856
-0.250 -0.0266 0.00657 0.00073 -0.0003 0.5005 0.4165
0.000 0.0000 0.00661 0.00073 0.0000 0.4524 0.4515
0.250 0.0266 0.00657 0.00073 0.0003 0.4164 0.5003
0.500 0.0534 0.00655 0.00075 0.0005 0.3857 0.5396
0.750 0.0802 0.00657 0.00077 0.0008 0.3527 0.5765
1.000 0.1071 0.00657 0.00081 0.0010 0.3279 0.6138
1.250 0.1339 0.00657 0.00085 0.0013 0.3018 0.6529
1.500 0.1601 0.00664 0.00092 0.0017 0.2619 0.6958
1.750 0.1860 0.00666 0.00099 0.0022 0.2306 0.7447
2.000 0.2121 0.00667 0.00106 0.0027 0.2104 0.7860
2.250 0.2381 0.00669 0.00115 0.0032 0.1922 0.8243
2.500 0.2633 0.00670 0.00125 0.0040 0.1759 0.8672
2.750 0.2883 0.00674 0.00136 0.0049 0.1581 0.9096
3.000 0.3176 0.00686 0.00149 0.0049 0.1400 0.9471
3.500 0.3837 0.00723 0.00176 0.0028 0.1103 0.9797
3.750 0.4165 0.00747 0.00190 0.0018 0.0908 0.9864
4.000 0.4498 0.00769 0.00206 0.0006 0.0770 0.9922
4.250 0.4843 0.00790 0.00222 -0.0008 0.0663 0.9960
4.500 0.5185 0.00813 0.00239 -0.0022 0.0564 0.9992
4.750 0.5463 0.00831 0.00256 -0.0022 0.0512 1.0000
5.000 0.5710 0.00853 0.00276 -0.0015 0.0453 1.0000
5.250 0.5961 0.00872 0.00295 -0.0008 0.0415 1.0000
5.500 0.6211 0.00896 0.00316 -0.0001 0.0362 1.0000
5.750 0.6460 0.00920 0.00338 0.0005 0.0316 1.0000
6.000 0.6708 0.00947 0.00364 0.0012 0.0274 1.0000
6.250 0.6958 0.00974 0.00390 0.0018 0.0240 1.0000
6.500 0.7209 0.01001 0.00418 0.0024 0.0221 1.0000
6.750 0.7459 0.01032 0.00448 0.0030 0.0199 1.0000
7.000 0.7708 0.01068 0.00485 0.0036 0.0179 1.0000
7.250 0.7962 0.01095 0.00518 0.0042 0.0175 1.0000
7.500 0.8215 0.01126 0.00553 0.0047 0.0168 1.0000
7.750 0.8468 0.01158 0.00588 0.0052 0.0160 1.0000
8.000 0.8719 0.01193 0.00625 0.0057 0.0151 1.0000
8.250 0.8968 0.01232 0.00666 0.0062 0.0142 1.0000
8.500 0.9211 0.01282 0.00720 0.0068 0.0132 1.0000
8.750 0.9458 0.01325 0.00770 0.0073 0.0127 1.0000
9.000 0.9707 0.01362 0.00812 0.0077 0.0124 1.0000
9.250 0.9956 0.01399 0.00854 0.0082 0.0120 1.0000
9.500 1.0202 0.01439 0.00899 0.0087 0.0114 1.0000
9.750 1.0447 0.01480 0.00943 0.0092 0.0108 1.0000
10.000 1.0689 0.01525 0.00991 0.0096 0.0102 1.0000
10.250 1.0924 0.01580 0.01051 0.0102 0.0095 1.0000
10.500 1.1155 0.01639 0.01117 0.0108 0.0089 1.0000
10.750 1.1392 0.01686 0.01170 0.0113 0.0086 1.0000
11.000 1.1627 0.01734 0.01225 0.0118 0.0081 1.0000
11.250 1.1858 0.01786 0.01282 0.0124 0.0075 1.0000
11.500 1.2082 0.01845 0.01346 0.0130 0.0070 1.0000
11.750 1.2300 0.01911 0.01415 0.0136 0.0065 1.0000
12.000 1.2509 0.01985 0.01499 0.0144 0.0060 1.0000
12.250 1.2717 0.02057 0.01580 0.0151 0.0058 1.0000
12.500 1.2918 0.02133 0.01665 0.0159 0.0055 1.0000
12.750 1.3110 0.02217 0.01756 0.0167 0.0051 1.0000
13.000 1.3293 0.02305 0.01853 0.0176 0.0048 1.0000
13.250 1.3462 0.02404 0.01959 0.0186 0.0045 1.0000
13.500 1.3611 0.02517 0.02082 0.0198 0.0042 1.0000
13.750 1.3743 0.02637 0.02214 0.0210 0.0040 1.0000
14.000 1.3862 0.02757 0.02346 0.0224 0.0039 1.0000
14.250 1.3953 0.02888 0.02490 0.0240 0.0038 1.0000
14.500 1.3975 0.03028 0.02642 0.0264 0.0037 1.0000
14.750 1.3954 0.03181 0.02807 0.0290 0.0036 1.0000
15.000 1.3897 0.03384 0.03023 0.0308 0.0036 1.0000
15.250 1.3804 0.03665 0.03318 0.0312 0.0035 1.0000
15.500 1.3653 0.04093 0.03762 0.0296 0.0035 1.0000
15.750 1.3445 0.04745 0.04433 0.0250 0.0034 1.0000
16.000 1.3023 0.05961 0.05675 0.0156 0.0035 1.0000
16.250 1.2102 0.08163 0.07906 0.0012 0.0038 1.0000
16.500 1.1182 0.10348 0.10114 -0.0121 0.0042 1.0000
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Polar data table (+)
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