S9027 (8%) (s9027-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: S9027 (8%) (s9027-il) Reynolds number: 200,000 Max Cl/Cd: 43.35 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s9027-il-200000-n5.txt Download as CSV file: xf-s9027-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.500 -0.8849 0.08379 0.08013 0.0025 1.0000 0.0174
-12.250 -0.9280 0.06942 0.06564 -0.0079 1.0000 0.0165
-12.000 -0.9583 0.05871 0.05472 -0.0172 1.0000 0.0162
-11.750 -0.9836 0.05135 0.04713 -0.0231 1.0000 0.0160
-11.500 -1.0018 0.04686 0.04241 -0.0248 1.0000 0.0161
-11.250 -1.0163 0.04357 0.03888 -0.0236 1.0000 0.0163
-11.000 -1.0215 0.04078 0.03580 -0.0222 1.0000 0.0169
-10.750 -1.0199 0.03812 0.03279 -0.0210 1.0000 0.0175
-10.500 -1.0137 0.03570 0.03002 -0.0197 1.0000 0.0180
-10.250 -1.0068 0.03305 0.02716 -0.0185 1.0000 0.0188
-10.000 -0.9928 0.03139 0.02534 -0.0175 1.0000 0.0195
-9.750 -0.9768 0.02991 0.02369 -0.0166 1.0000 0.0203
-9.500 -0.9590 0.02864 0.02223 -0.0157 1.0000 0.0215
-9.250 -0.9405 0.02729 0.02066 -0.0149 1.0000 0.0228
-9.000 -0.9212 0.02588 0.01899 -0.0139 1.0000 0.0238
-8.750 -0.9011 0.02457 0.01740 -0.0130 1.0000 0.0246
-8.500 -0.8826 0.02290 0.01563 -0.0120 1.0000 0.0258
-8.250 -0.8614 0.02193 0.01458 -0.0113 1.0000 0.0273
-8.000 -0.8390 0.02111 0.01366 -0.0106 1.0000 0.0291
-7.750 -0.8167 0.02019 0.01261 -0.0098 1.0000 0.0308
-7.500 -0.7942 0.01929 0.01156 -0.0090 1.0000 0.0325
-7.250 -0.7722 0.01831 0.01047 -0.0081 1.0000 0.0344
-7.000 -0.7495 0.01752 0.00963 -0.0073 1.0000 0.0372
-6.750 -0.7257 0.01691 0.00895 -0.0067 1.0000 0.0410
-6.500 -0.7022 0.01625 0.00822 -0.0060 1.0000 0.0454
-6.250 -0.6784 0.01565 0.00759 -0.0053 1.0000 0.0510
-6.000 -0.6543 0.01511 0.00696 -0.0046 1.0000 0.0567
-5.750 -0.6302 0.01459 0.00645 -0.0039 1.0000 0.0641
-5.500 -0.6060 0.01411 0.00598 -0.0033 1.0000 0.0729
-5.250 -0.5815 0.01370 0.00555 -0.0027 1.0000 0.0828
-5.000 -0.5571 0.01329 0.00515 -0.0020 1.0000 0.0948
-4.750 -0.5328 0.01287 0.00477 -0.0014 1.0000 0.1093
-4.500 -0.5086 0.01247 0.00443 -0.0007 1.0000 0.1254
-4.250 -0.4842 0.01211 0.00412 0.0000 1.0000 0.1425
-4.000 -0.4599 0.01178 0.00384 0.0007 1.0000 0.1626
-3.750 -0.4358 0.01143 0.00357 0.0014 1.0000 0.1848
-3.500 -0.4116 0.01112 0.00334 0.0021 1.0000 0.2074
-3.250 -0.3875 0.01082 0.00313 0.0029 1.0000 0.2336
-3.000 -0.3636 0.01051 0.00295 0.0036 1.0000 0.2648
-2.750 -0.3399 0.01020 0.00278 0.0044 1.0000 0.3001
-2.500 -0.3164 0.00989 0.00265 0.0052 1.0000 0.3406
-2.250 -0.2930 0.00960 0.00254 0.0061 1.0000 0.3842
-2.000 -0.2698 0.00933 0.00245 0.0070 1.0000 0.4267
-1.750 -0.2469 0.00908 0.00238 0.0080 1.0000 0.4717
-1.500 -0.2157 0.00882 0.00236 0.0072 0.9947 0.5249
-1.250 -0.1782 0.00855 0.00236 0.0052 0.9833 0.5869
-1.000 -0.1426 0.00828 0.00235 0.0038 0.9686 0.6509
-0.750 -0.1090 0.00804 0.00236 0.0031 0.9495 0.7099
-0.500 -0.0731 0.00786 0.00237 0.0019 0.9274 0.7647
-0.250 -0.0367 0.00773 0.00238 0.0009 0.8990 0.8144
0.000 0.0000 0.00768 0.00239 0.0000 0.8607 0.8605
0.250 0.0367 0.00773 0.00238 -0.0009 0.8145 0.8990
0.500 0.0730 0.00786 0.00237 -0.0019 0.7649 0.9274
0.750 0.1090 0.00804 0.00236 -0.0031 0.7100 0.9496
1.000 0.1425 0.00828 0.00235 -0.0038 0.6513 0.9687
1.250 0.1781 0.00855 0.00236 -0.0052 0.5867 0.9833
1.500 0.2157 0.00882 0.00236 -0.0072 0.5248 0.9947
1.750 0.2466 0.00908 0.00238 -0.0079 0.4716 1.0000
2.000 0.2696 0.00933 0.00245 -0.0070 0.4268 1.0000
2.250 0.2928 0.00960 0.00254 -0.0060 0.3840 1.0000
2.500 0.3160 0.00989 0.00264 -0.0052 0.3405 1.0000
2.750 0.3396 0.01020 0.00278 -0.0043 0.3003 1.0000
3.000 0.3633 0.01051 0.00295 -0.0036 0.2647 1.0000
3.250 0.3872 0.01082 0.00313 -0.0028 0.2339 1.0000
3.500 0.4113 0.01112 0.00333 -0.0021 0.2075 1.0000
3.750 0.4355 0.01143 0.00357 -0.0013 0.1849 1.0000
4.000 0.4596 0.01178 0.00384 -0.0006 0.1628 1.0000
4.250 0.4839 0.01211 0.00412 0.0001 0.1426 1.0000
4.500 0.5083 0.01247 0.00443 0.0007 0.1255 1.0000
4.750 0.5326 0.01287 0.00477 0.0014 0.1093 1.0000
5.000 0.5569 0.01329 0.00515 0.0021 0.0949 1.0000
5.250 0.5813 0.01370 0.00555 0.0027 0.0829 1.0000
5.500 0.6059 0.01411 0.00598 0.0033 0.0730 1.0000
5.750 0.6302 0.01459 0.00644 0.0040 0.0641 1.0000
6.000 0.6543 0.01511 0.00696 0.0046 0.0566 1.0000
6.250 0.6784 0.01565 0.00759 0.0053 0.0510 1.0000
6.500 0.7022 0.01625 0.00822 0.0059 0.0454 1.0000
6.750 0.7258 0.01691 0.00894 0.0067 0.0409 1.0000
7.000 0.7496 0.01752 0.00964 0.0073 0.0372 1.0000
7.250 0.7724 0.01832 0.01047 0.0081 0.0344 1.0000
7.500 0.7944 0.01930 0.01157 0.0089 0.0325 1.0000
7.750 0.8170 0.02020 0.01261 0.0097 0.0309 1.0000
8.000 0.8394 0.02111 0.01366 0.0105 0.0291 1.0000
8.250 0.8618 0.02194 0.01459 0.0112 0.0273 1.0000
8.500 0.8831 0.02291 0.01563 0.0119 0.0257 1.0000
8.750 0.9017 0.02458 0.01741 0.0129 0.0246 1.0000
9.000 0.9220 0.02589 0.01900 0.0138 0.0238 1.0000
9.250 0.9412 0.02731 0.02067 0.0147 0.0227 1.0000
9.500 0.9599 0.02865 0.02224 0.0156 0.0214 1.0000
9.750 0.9778 0.02993 0.02370 0.0164 0.0203 1.0000
10.000 0.9939 0.03144 0.02539 0.0173 0.0195 1.0000
10.250 1.0081 0.03305 0.02714 0.0182 0.0188 1.0000
10.500 1.0147 0.03580 0.03011 0.0194 0.0179 1.0000
10.750 1.0217 0.03811 0.03278 0.0206 0.0174 1.0000
11.000 1.0230 0.04082 0.03585 0.0219 0.0168 1.0000
11.250 1.0177 0.04366 0.03898 0.0233 0.0162 1.0000
11.500 1.0027 0.04702 0.04258 0.0244 0.0160 1.0000
11.750 0.9839 0.05161 0.04741 0.0226 0.0159 1.0000
12.000 0.9602 0.05879 0.05480 0.0168 0.0161 1.0000
12.250 0.9254 0.07039 0.06661 0.0070 0.0169 1.0000
12.500 0.8845 0.08444 0.08078 -0.0033 0.0175 1.0000
|
Polar data table (+)
Polar graphs
<< Back to S9027 (8%) (s9027-il)