S9032 (9%) (s9032-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: S9032 (9%) (s9032-il) Reynolds number: 1,000,000 Max Cl/Cd: 74.13 at α=7.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s9032-il-1000000-n5.txt Download as CSV file: xf-s9032-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-17.250 -1.1576 0.10163 0.09905 0.0067 1.0000 0.0039
-17.000 -1.2333 0.08311 0.08029 -0.0045 1.0000 0.0035
-16.750 -1.2874 0.06913 0.06609 -0.0131 1.0000 0.0033
-16.500 -1.3293 0.05768 0.05442 -0.0207 1.0000 0.0032
-16.250 -1.3534 0.04980 0.04636 -0.0260 1.0000 0.0032
-16.000 -1.3731 0.04340 0.03979 -0.0301 1.0000 0.0033
-15.750 -1.3846 0.03892 0.03516 -0.0323 1.0000 0.0033
-15.500 -1.3930 0.03546 0.03157 -0.0332 1.0000 0.0034
-15.250 -1.3989 0.03281 0.02878 -0.0330 1.0000 0.0035
-15.000 -1.4024 0.03075 0.02661 -0.0318 1.0000 0.0035
-14.750 -1.4040 0.02911 0.02485 -0.0298 1.0000 0.0037
-14.500 -1.4034 0.02778 0.02343 -0.0273 1.0000 0.0038
-14.250 -1.4011 0.02658 0.02213 -0.0245 1.0000 0.0042
-14.000 -1.3916 0.02547 0.02094 -0.0227 1.0000 0.0044
-13.750 -1.3790 0.02444 0.01984 -0.0212 1.0000 0.0048
-13.500 -1.3643 0.02352 0.01884 -0.0200 1.0000 0.0052
-13.250 -1.3480 0.02266 0.01790 -0.0188 1.0000 0.0056
-13.000 -1.3306 0.02184 0.01701 -0.0177 1.0000 0.0061
-12.750 -1.3120 0.02110 0.01621 -0.0168 1.0000 0.0066
-12.500 -1.2923 0.02043 0.01550 -0.0159 1.0000 0.0072
-12.250 -1.2719 0.01979 0.01479 -0.0151 1.0000 0.0076
-12.000 -1.2507 0.01921 0.01414 -0.0144 1.0000 0.0080
-11.750 -1.2291 0.01865 0.01350 -0.0136 1.0000 0.0083
-11.500 -1.2079 0.01800 0.01280 -0.0129 1.0000 0.0087
-11.250 -1.1861 0.01740 0.01215 -0.0122 1.0000 0.0092
-11.000 -1.1635 0.01688 0.01158 -0.0115 1.0000 0.0097
-10.750 -1.1405 0.01638 0.01103 -0.0109 1.0000 0.0102
-10.500 -1.1171 0.01593 0.01054 -0.0103 1.0000 0.0107
-10.250 -1.0934 0.01550 0.01006 -0.0098 1.0000 0.0111
-10.000 -1.0694 0.01509 0.00960 -0.0092 1.0000 0.0115
-9.750 -1.0449 0.01476 0.00923 -0.0088 1.0000 0.0118
-9.500 -1.0220 0.01415 0.00856 -0.0081 1.0000 0.0127
-9.250 -0.9981 0.01370 0.00809 -0.0075 1.0000 0.0137
-9.000 -0.9738 0.01331 0.00768 -0.0070 1.0000 0.0144
-8.750 -0.9492 0.01295 0.00729 -0.0064 1.0000 0.0152
-8.500 -0.9246 0.01259 0.00688 -0.0059 1.0000 0.0157
-8.250 -0.8999 0.01224 0.00649 -0.0053 1.0000 0.0160
-8.000 -0.8750 0.01192 0.00612 -0.0048 1.0000 0.0163
-7.750 -0.8508 0.01150 0.00567 -0.0041 1.0000 0.0177
-7.500 -0.8263 0.01115 0.00531 -0.0034 1.0000 0.0191
-7.250 -0.8018 0.01083 0.00499 -0.0028 1.0000 0.0204
-7.000 -0.7771 0.01055 0.00468 -0.0021 1.0000 0.0217
-6.750 -0.7525 0.01027 0.00438 -0.0014 1.0000 0.0240
-6.500 -0.7283 0.00996 0.00410 -0.0007 1.0000 0.0275
-6.250 -0.7038 0.00970 0.00384 0.0000 1.0000 0.0312
-6.000 -0.6795 0.00942 0.00360 0.0007 1.0000 0.0368
-5.750 -0.6548 0.00921 0.00339 0.0015 1.0000 0.0401
-5.500 -0.6305 0.00896 0.00316 0.0022 1.0000 0.0456
-5.250 -0.6004 0.00875 0.00296 0.0017 0.9985 0.0501
-5.000 -0.5667 0.00850 0.00276 0.0004 0.9954 0.0581
-4.750 -0.5333 0.00829 0.00258 -0.0008 0.9921 0.0653
-4.500 -0.5006 0.00808 0.00240 -0.0018 0.9870 0.0747
-4.250 -0.4667 0.00785 0.00223 -0.0031 0.9803 0.0873
-4.000 -0.4343 0.00758 0.00206 -0.0041 0.9694 0.1056
-3.750 -0.4019 0.00734 0.00189 -0.0050 0.9528 0.1240
-3.250 -0.3450 0.00708 0.00160 -0.0048 0.8897 0.1542
-3.000 -0.3200 0.00705 0.00148 -0.0040 0.8486 0.1682
-2.750 -0.2945 0.00703 0.00137 -0.0033 0.8088 0.1832
-2.500 -0.2683 0.00699 0.00127 -0.0028 0.7743 0.1995
-2.250 -0.2418 0.00693 0.00118 -0.0024 0.7435 0.2190
-2.000 -0.2152 0.00684 0.00109 -0.0021 0.7166 0.2456
-1.750 -0.1887 0.00671 0.00102 -0.0018 0.6904 0.2813
-1.500 -0.1619 0.00666 0.00095 -0.0015 0.6589 0.3069
-1.250 -0.1352 0.00665 0.00090 -0.0012 0.6213 0.3325
-1.000 -0.1082 0.00664 0.00086 -0.0009 0.5892 0.3560
-0.500 -0.0538 0.00660 0.00080 -0.0005 0.5335 0.4038
-0.250 -0.0268 0.00654 0.00078 -0.0002 0.5078 0.4405
0.000 0.0000 0.00649 0.00078 0.0000 0.4793 0.4793
0.250 0.0269 0.00654 0.00078 0.0002 0.4406 0.5078
0.500 0.0539 0.00660 0.00080 0.0005 0.4043 0.5331
0.750 0.0810 0.00662 0.00082 0.0007 0.3769 0.5612
1.000 0.1082 0.00664 0.00086 0.0009 0.3558 0.5890
1.250 0.1352 0.00665 0.00090 0.0012 0.3329 0.6214
1.500 0.1619 0.00667 0.00095 0.0015 0.3066 0.6585
1.750 0.1887 0.00671 0.00102 0.0018 0.2809 0.6906
2.000 0.2152 0.00684 0.00109 0.0021 0.2458 0.7167
2.250 0.2418 0.00693 0.00118 0.0024 0.2192 0.7433
2.500 0.2683 0.00699 0.00127 0.0028 0.1995 0.7743
2.750 0.2945 0.00703 0.00137 0.0033 0.1833 0.8089
3.000 0.3200 0.00705 0.00148 0.0040 0.1682 0.8489
3.250 0.3450 0.00708 0.00160 0.0048 0.1542 0.8892
3.750 0.4018 0.00734 0.00189 0.0050 0.1240 0.9528
4.000 0.4341 0.00759 0.00206 0.0041 0.1047 0.9693
4.250 0.4666 0.00785 0.00223 0.0031 0.0874 0.9802
4.500 0.5003 0.00808 0.00240 0.0019 0.0747 0.9868
4.750 0.5330 0.00829 0.00258 0.0008 0.0655 0.9920
5.000 0.5662 0.00851 0.00276 -0.0003 0.0580 0.9952
5.250 0.6000 0.00875 0.00297 -0.0017 0.0502 0.9982
5.500 0.6312 0.00896 0.00316 -0.0024 0.0455 1.0000
5.750 0.6554 0.00921 0.00339 -0.0016 0.0400 1.0000
6.000 0.6801 0.00942 0.00360 -0.0009 0.0368 1.0000
6.250 0.7044 0.00970 0.00384 -0.0001 0.0312 1.0000
6.500 0.7288 0.00996 0.00410 0.0006 0.0275 1.0000
6.750 0.7530 0.01027 0.00438 0.0013 0.0239 1.0000
7.000 0.7775 0.01055 0.00468 0.0020 0.0217 1.0000
7.250 0.8021 0.01083 0.00499 0.0027 0.0204 1.0000
7.500 0.8266 0.01115 0.00531 0.0034 0.0191 1.0000
7.750 0.8510 0.01150 0.00567 0.0041 0.0178 1.0000
8.000 0.8750 0.01193 0.00613 0.0048 0.0163 1.0000
8.250 0.8997 0.01224 0.00650 0.0053 0.0160 1.0000
8.500 0.9244 0.01259 0.00688 0.0059 0.0156 1.0000
8.750 0.9489 0.01295 0.00729 0.0065 0.0152 1.0000
9.000 0.9734 0.01331 0.00769 0.0071 0.0145 1.0000
9.250 0.9977 0.01369 0.00808 0.0076 0.0135 1.0000
9.500 1.0215 0.01415 0.00856 0.0082 0.0128 1.0000
9.750 1.0443 0.01475 0.00922 0.0089 0.0118 1.0000
10.000 1.0687 0.01509 0.00961 0.0094 0.0115 1.0000
10.250 1.0927 0.01548 0.01004 0.0099 0.0111 1.0000
10.500 1.1163 0.01592 0.01053 0.0105 0.0107 1.0000
10.750 1.1396 0.01637 0.01103 0.0111 0.0102 1.0000
11.000 1.1626 0.01686 0.01156 0.0117 0.0097 1.0000
11.250 1.1851 0.01739 0.01214 0.0124 0.0092 1.0000
11.500 1.2068 0.01799 0.01278 0.0131 0.0087 1.0000
11.750 1.2279 0.01864 0.01350 0.0139 0.0083 1.0000
12.000 1.2494 0.01920 0.01413 0.0146 0.0080 1.0000
12.250 1.2705 0.01979 0.01479 0.0154 0.0077 1.0000
12.500 1.2908 0.02041 0.01548 0.0162 0.0072 1.0000
12.750 1.3105 0.02108 0.01620 0.0171 0.0066 1.0000
13.000 1.3290 0.02182 0.01698 0.0181 0.0060 1.0000
13.250 1.3463 0.02264 0.01788 0.0191 0.0056 1.0000
13.500 1.3625 0.02349 0.01881 0.0203 0.0053 1.0000
13.750 1.3772 0.02441 0.01981 0.0216 0.0048 1.0000
14.000 1.3895 0.02544 0.02091 0.0231 0.0044 1.0000
14.250 1.3990 0.02652 0.02208 0.0249 0.0042 1.0000
14.500 1.4012 0.02772 0.02337 0.0277 0.0038 1.0000
14.750 1.4021 0.02905 0.02479 0.0302 0.0037 1.0000
15.000 1.4006 0.03070 0.02656 0.0321 0.0036 1.0000
15.250 1.3972 0.03276 0.02873 0.0333 0.0035 1.0000
15.500 1.3915 0.03540 0.03150 0.0336 0.0034 1.0000
15.750 1.3822 0.03897 0.03521 0.0326 0.0033 1.0000
16.000 1.3727 0.04319 0.03957 0.0304 0.0033 1.0000
16.250 1.3559 0.04913 0.04568 0.0267 0.0033 1.0000
16.500 1.3311 0.05706 0.05379 0.0213 0.0033 1.0000
16.750 1.2926 0.06793 0.06487 0.0141 0.0034 1.0000
17.000 1.2368 0.08218 0.07934 0.0052 0.0036 1.0000
17.250 1.1664 0.09959 0.09698 -0.0053 0.0039 1.0000
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Polar data table (+)
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