GOE 429 AIRFOIL (goe429-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 429 AIRFOIL (goe429-il) Reynolds number: 500,000 Max Cl/Cd: 58.55 at α=7.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe429-il-500000-n5.txt Download as CSV file: xf-goe429-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 429 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.500 -1.2336 0.09710 0.09335 0.0280 1.0000 0.0096
-16.250 -1.2574 0.08886 0.08498 0.0237 1.0000 0.0095
-16.000 -1.2812 0.08091 0.07689 0.0196 1.0000 0.0095
-15.750 -1.3035 0.07336 0.06919 0.0157 1.0000 0.0095
-15.500 -1.3231 0.06641 0.06210 0.0121 1.0000 0.0096
-15.250 -1.3397 0.06000 0.05554 0.0086 1.0000 0.0096
-15.000 -1.3527 0.05424 0.04963 0.0055 1.0000 0.0097
-14.750 -1.3622 0.04914 0.04439 0.0027 1.0000 0.0098
-14.500 -1.3684 0.04468 0.03979 0.0003 1.0000 0.0099
-14.250 -1.3716 0.04081 0.03580 -0.0017 1.0000 0.0100
-14.000 -1.3723 0.03743 0.03228 -0.0033 1.0000 0.0101
-13.750 -1.3705 0.03450 0.02922 -0.0047 1.0000 0.0103
-13.500 -1.3675 0.03201 0.02660 -0.0054 1.0000 0.0105
-13.250 -1.3633 0.03016 0.02463 -0.0048 1.0000 0.0107
-13.000 -1.3537 0.02873 0.02307 -0.0040 1.0000 0.0109
-12.750 -1.3398 0.02747 0.02169 -0.0033 1.0000 0.0112
-12.500 -1.3257 0.02611 0.02024 -0.0027 1.0000 0.0115
-12.250 -1.3096 0.02485 0.01889 -0.0021 1.0000 0.0120
-12.000 -1.2911 0.02380 0.01776 -0.0016 1.0000 0.0125
-11.750 -1.2709 0.02287 0.01675 -0.0012 1.0000 0.0130
-11.500 -1.2497 0.02202 0.01582 -0.0008 1.0000 0.0137
-11.250 -1.2275 0.02124 0.01495 -0.0004 1.0000 0.0143
-11.000 -1.2057 0.02035 0.01399 0.0000 1.0000 0.0151
-10.750 -1.1829 0.01955 0.01314 0.0003 1.0000 0.0161
-10.500 -1.1592 0.01885 0.01238 0.0005 1.0000 0.0173
-10.250 -1.1352 0.01815 0.01162 0.0008 1.0000 0.0188
-10.000 -1.1108 0.01746 0.01091 0.0010 1.0000 0.0213
-9.750 -1.0862 0.01678 0.01024 0.0011 1.0000 0.0251
-9.500 -1.0611 0.01615 0.00962 0.0013 1.0000 0.0304
-9.250 -1.0355 0.01560 0.00907 0.0013 1.0000 0.0361
-9.000 -1.0093 0.01512 0.00860 0.0014 1.0000 0.0411
-8.750 -0.9826 0.01471 0.00817 0.0015 1.0000 0.0458
-8.500 -0.9558 0.01428 0.00776 0.0015 1.0000 0.0505
-8.250 -0.9285 0.01393 0.00738 0.0015 1.0000 0.0546
-8.000 -0.9013 0.01354 0.00701 0.0014 1.0000 0.0587
-7.750 -0.8738 0.01322 0.00667 0.0014 1.0000 0.0628
-7.500 -0.8460 0.01291 0.00634 0.0014 1.0000 0.0665
-7.250 -0.8183 0.01255 0.00602 0.0013 1.0000 0.0717
-7.000 -0.7902 0.01229 0.00574 0.0012 1.0000 0.0758
-6.750 -0.7622 0.01195 0.00542 0.0011 1.0000 0.0809
-6.500 -0.7339 0.01166 0.00513 0.0010 1.0000 0.0862
-6.250 -0.7054 0.01142 0.00487 0.0008 1.0000 0.0898
-6.000 -0.6770 0.01108 0.00456 0.0007 1.0000 0.0948
-5.750 -0.6456 0.01088 0.00433 0.0000 0.9421 0.1002
-5.500 -0.6203 0.01074 0.00412 0.0007 0.9087 0.1055
-5.250 -0.5950 0.01054 0.00388 0.0014 0.8838 0.1129
-5.000 -0.5687 0.01033 0.00364 0.0019 0.8627 0.1229
-4.500 -0.5150 0.00972 0.00319 0.0023 0.8236 0.1796
-4.250 -0.4873 0.00956 0.00301 0.0025 0.8049 0.1976
-4.000 -0.4595 0.00944 0.00284 0.0027 0.7842 0.2118
-3.750 -0.4314 0.00931 0.00268 0.0027 0.7647 0.2256
-3.250 -0.3743 0.00907 0.00239 0.0027 0.7366 0.2528
-3.000 -0.3457 0.00889 0.00226 0.0026 0.7246 0.2731
-2.750 -0.3170 0.00874 0.00215 0.0025 0.7125 0.2950
-2.500 -0.2882 0.00862 0.00204 0.0025 0.6979 0.3159
-2.250 -0.2594 0.00848 0.00195 0.0024 0.6831 0.3425
-2.000 -0.2305 0.00834 0.00187 0.0023 0.6712 0.3699
-1.750 -0.2014 0.00824 0.00181 0.0022 0.6596 0.3905
-1.500 -0.1722 0.00816 0.00175 0.0021 0.6474 0.4086
-1.250 -0.1431 0.00809 0.00170 0.0020 0.6342 0.4277
-1.000 -0.1140 0.00802 0.00165 0.0018 0.6163 0.4487
-0.750 -0.0850 0.00798 0.00160 0.0018 0.5893 0.4700
-0.500 -0.0560 0.00798 0.00155 0.0017 0.5558 0.4876
-0.250 -0.0268 0.00802 0.00152 0.0015 0.5209 0.5019
0.000 0.0023 0.00809 0.00150 0.0014 0.4826 0.5165
0.250 0.0313 0.00819 0.00152 0.0012 0.4435 0.5333
0.500 0.0604 0.00830 0.00156 0.0010 0.4087 0.5518
0.750 0.0895 0.00840 0.00162 0.0008 0.3776 0.5708
1.000 0.1186 0.00852 0.00169 0.0006 0.3487 0.5887
1.250 0.1477 0.00865 0.00177 0.0005 0.3224 0.6055
1.500 0.1767 0.00879 0.00186 0.0003 0.2968 0.6225
1.750 0.2057 0.00896 0.00197 0.0002 0.2683 0.6400
2.000 0.2345 0.00915 0.00208 0.0000 0.2408 0.6561
2.500 0.2923 0.00948 0.00232 -0.0003 0.2033 0.6814
2.750 0.3212 0.00961 0.00244 -0.0004 0.1901 0.6919
3.250 0.3789 0.00991 0.00269 -0.0006 0.1649 0.7101
3.750 0.4363 0.01024 0.00297 -0.0008 0.1423 0.7253
4.000 0.4650 0.01040 0.00312 -0.0009 0.1326 0.7333
4.250 0.4935 0.01056 0.00329 -0.0009 0.1228 0.7412
4.750 0.5491 0.01131 0.00379 -0.0011 0.0600 0.7590
5.000 0.5768 0.01169 0.00416 -0.0011 0.0482 0.7693
5.250 0.6048 0.01190 0.00444 -0.0011 0.0448 0.7813
5.500 0.6324 0.01212 0.00474 -0.0010 0.0425 0.7961
5.750 0.6594 0.01235 0.00507 -0.0008 0.0404 0.8158
6.000 0.6849 0.01258 0.00546 -0.0002 0.0385 0.8499
6.250 0.7113 0.01260 0.00573 0.0005 0.0377 0.9812
6.500 0.7397 0.01293 0.00609 0.0003 0.0370 1.0000
6.750 0.7675 0.01328 0.00647 0.0002 0.0362 1.0000
7.000 0.7951 0.01367 0.00688 0.0002 0.0355 1.0000
7.250 0.8224 0.01408 0.00732 0.0002 0.0348 1.0000
7.500 0.8496 0.01451 0.00779 0.0002 0.0341 1.0000
7.750 0.8764 0.01498 0.00829 0.0002 0.0334 1.0000
8.000 0.9028 0.01552 0.00885 0.0002 0.0326 1.0000
8.250 0.9284 0.01618 0.00954 0.0003 0.0318 1.0000
8.500 0.9534 0.01693 0.01034 0.0004 0.0312 1.0000
8.750 0.9793 0.01744 0.01091 0.0005 0.0309 1.0000
9.000 1.0049 0.01798 0.01151 0.0007 0.0305 1.0000
9.250 1.0302 0.01852 0.01211 0.0008 0.0300 1.0000
9.500 1.0551 0.01911 0.01277 0.0010 0.0294 1.0000
9.750 1.0794 0.01974 0.01346 0.0012 0.0288 1.0000
10.000 1.1036 0.02037 0.01414 0.0014 0.0282 1.0000
10.250 1.1274 0.02100 0.01482 0.0017 0.0275 1.0000
10.500 1.1506 0.02167 0.01554 0.0019 0.0270 1.0000
10.750 1.1727 0.02246 0.01637 0.0022 0.0264 1.0000
11.000 1.1918 0.02361 0.01756 0.0027 0.0257 1.0000
11.250 1.2129 0.02442 0.01846 0.0031 0.0253 1.0000
11.500 1.2344 0.02512 0.01926 0.0035 0.0248 1.0000
11.750 1.2548 0.02590 0.02015 0.0040 0.0242 1.0000
12.000 1.2741 0.02675 0.02108 0.0045 0.0237 1.0000
12.250 1.2923 0.02764 0.02206 0.0050 0.0231 1.0000
12.500 1.3096 0.02855 0.02305 0.0055 0.0225 1.0000
12.750 1.3257 0.02949 0.02406 0.0061 0.0220 1.0000
13.000 1.3378 0.03054 0.02518 0.0069 0.0216 1.0000
13.250 1.3457 0.03201 0.02673 0.0075 0.0213 1.0000
13.500 1.3499 0.03408 0.02887 0.0075 0.0209 1.0000
13.750 1.3554 0.03627 0.03120 0.0070 0.0206 1.0000
14.000 1.3611 0.03864 0.03371 0.0061 0.0203 1.0000
14.250 1.3649 0.04136 0.03656 0.0050 0.0199 1.0000
14.500 1.3669 0.04442 0.03975 0.0036 0.0195 1.0000
14.750 1.3666 0.04791 0.04337 0.0018 0.0191 1.0000
15.000 1.3645 0.05178 0.04736 -0.0002 0.0187 1.0000
15.250 1.3598 0.05619 0.05190 -0.0027 0.0184 1.0000
15.500 1.3521 0.06119 0.05702 -0.0055 0.0182 1.0000
15.750 1.3421 0.06670 0.06266 -0.0086 0.0180 1.0000
16.000 1.3289 0.07277 0.06886 -0.0120 0.0178 1.0000
16.250 1.3134 0.07925 0.07546 -0.0155 0.0177 1.0000
16.500 1.2957 0.08605 0.08238 -0.0190 0.0175 1.0000
16.750 1.2782 0.09302 0.08946 -0.0227 0.0174 1.0000
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Polar data table (+)
Polar graphs
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