GOE 429 AIRFOIL (goe429-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 429 AIRFOIL (goe429-il) Reynolds number: 1,000,000 Max Cl/Cd: 72.7 at α=8.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe429-il-1000000-n5.txt Download as CSV file: xf-goe429-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-17.750 -1.3059 0.10512 0.10196 0.0318 1.0000 0.0065
-17.500 -1.3468 0.09387 0.09054 0.0259 1.0000 0.0064
-17.250 -1.3840 0.08357 0.08007 0.0206 1.0000 0.0064
-17.000 -1.4171 0.07436 0.07070 0.0158 1.0000 0.0064
-16.750 -1.4448 0.06628 0.06246 0.0116 1.0000 0.0064
-16.500 -1.4656 0.05938 0.05541 0.0080 1.0000 0.0064
-16.250 -1.4817 0.05332 0.04921 0.0048 1.0000 0.0064
-16.000 -1.4927 0.04813 0.04389 0.0021 1.0000 0.0064
-15.750 -1.4995 0.04371 0.03934 -0.0001 1.0000 0.0065
-15.500 -1.5027 0.03995 0.03546 -0.0019 1.0000 0.0065
-15.250 -1.5036 0.03661 0.03201 -0.0034 1.0000 0.0066
-15.000 -1.5051 0.03329 0.02856 -0.0048 1.0000 0.0067
-14.750 -1.5037 0.03058 0.02574 -0.0058 1.0000 0.0068
-14.500 -1.5009 0.02858 0.02364 -0.0054 1.0000 0.0069
-14.250 -1.4944 0.02718 0.02216 -0.0041 1.0000 0.0071
-14.000 -1.4814 0.02598 0.02087 -0.0033 1.0000 0.0073
-13.750 -1.4658 0.02492 0.01975 -0.0026 1.0000 0.0074
-13.500 -1.4484 0.02396 0.01872 -0.0019 1.0000 0.0077
-13.250 -1.4295 0.02309 0.01779 -0.0013 1.0000 0.0079
-13.000 -1.4094 0.02229 0.01692 -0.0008 1.0000 0.0082
-12.750 -1.3885 0.02154 0.01611 -0.0004 1.0000 0.0084
-12.500 -1.3667 0.02084 0.01535 0.0000 1.0000 0.0086
-12.250 -1.3448 0.02009 0.01453 0.0005 1.0000 0.0089
-12.000 -1.3228 0.01931 0.01370 0.0009 1.0000 0.0092
-11.750 -1.2997 0.01863 0.01298 0.0012 1.0000 0.0096
-11.500 -1.2760 0.01801 0.01232 0.0015 1.0000 0.0101
-11.250 -1.2517 0.01744 0.01170 0.0017 1.0000 0.0105
-11.000 -1.2269 0.01691 0.01113 0.0020 1.0000 0.0109
-10.750 -1.2016 0.01642 0.01059 0.0022 1.0000 0.0113
-10.500 -1.1767 0.01584 0.00998 0.0024 1.0000 0.0121
-10.250 -1.1512 0.01530 0.00942 0.0025 1.0000 0.0130
-10.000 -1.1253 0.01483 0.00892 0.0027 1.0000 0.0139
-9.750 -1.0991 0.01437 0.00844 0.0028 1.0000 0.0150
-9.500 -1.0730 0.01388 0.00793 0.0029 1.0000 0.0167
-9.250 -1.0466 0.01341 0.00746 0.0029 1.0000 0.0193
-9.000 -1.0202 0.01291 0.00698 0.0030 1.0000 0.0238
-8.750 -0.9935 0.01242 0.00654 0.0030 1.0000 0.0301
-8.500 -0.9665 0.01200 0.00616 0.0030 1.0000 0.0362
-8.250 -0.9390 0.01165 0.00582 0.0030 1.0000 0.0410
-8.000 -0.9113 0.01134 0.00552 0.0030 1.0000 0.0452
-7.750 -0.8833 0.01103 0.00524 0.0029 1.0000 0.0491
-7.500 -0.8553 0.01075 0.00497 0.0028 1.0000 0.0532
-7.250 -0.8270 0.01050 0.00473 0.0027 1.0000 0.0567
-7.000 -0.7998 0.01035 0.00454 0.0030 0.9269 0.0616
-6.750 -0.7746 0.01025 0.00435 0.0037 0.8980 0.0648
-6.500 -0.7480 0.01007 0.00413 0.0041 0.8757 0.0694
-6.250 -0.7208 0.00991 0.00392 0.0044 0.8536 0.0741
-6.000 -0.6931 0.00979 0.00373 0.0045 0.8322 0.0777
-5.750 -0.6652 0.00960 0.00351 0.0046 0.8113 0.0837
-5.500 -0.6369 0.00948 0.00332 0.0046 0.7919 0.0876
-5.250 -0.6084 0.00937 0.00314 0.0046 0.7749 0.0907
-5.000 -0.5800 0.00920 0.00295 0.0046 0.7598 0.0967
-4.750 -0.5513 0.00908 0.00278 0.0045 0.7428 0.1018
-4.500 -0.5226 0.00895 0.00261 0.0045 0.7264 0.1086
-4.250 -0.4939 0.00880 0.00245 0.0044 0.7138 0.1175
-3.750 -0.4367 0.00823 0.00209 0.0041 0.6937 0.1773
-3.500 -0.4077 0.00811 0.00198 0.0040 0.6840 0.1918
-3.250 -0.3786 0.00801 0.00187 0.0038 0.6709 0.2041
-3.000 -0.3495 0.00789 0.00176 0.0037 0.6557 0.2162
-2.750 -0.3203 0.00779 0.00167 0.0036 0.6437 0.2275
-2.500 -0.2911 0.00769 0.00158 0.0034 0.6330 0.2399
-2.250 -0.2618 0.00759 0.00149 0.0033 0.6210 0.2547
-2.000 -0.2326 0.00750 0.00141 0.0031 0.6049 0.2702
-1.750 -0.2034 0.00738 0.00132 0.0029 0.5826 0.2948
-1.500 -0.1742 0.00730 0.00125 0.0027 0.5517 0.3222
-1.250 -0.1449 0.00730 0.00119 0.0024 0.5093 0.3472
-1.000 -0.1156 0.00734 0.00116 0.0022 0.4661 0.3667
-0.750 -0.0863 0.00739 0.00115 0.0019 0.4314 0.3846
-0.500 -0.0569 0.00742 0.00115 0.0017 0.4014 0.4066
-0.250 -0.0275 0.00745 0.00116 0.0014 0.3742 0.4270
0.000 0.0018 0.00750 0.00117 0.0012 0.3481 0.4455
0.250 0.0312 0.00755 0.00119 0.0010 0.3239 0.4602
0.500 0.0606 0.00762 0.00122 0.0008 0.3009 0.4728
0.750 0.0900 0.00771 0.00125 0.0005 0.2759 0.4852
1.000 0.1193 0.00783 0.00130 0.0003 0.2483 0.4980
1.250 0.1486 0.00791 0.00135 0.0001 0.2286 0.5125
1.500 0.1779 0.00798 0.00141 -0.0001 0.2100 0.5299
1.750 0.2072 0.00804 0.00148 -0.0003 0.1963 0.5484
2.000 0.2364 0.00811 0.00155 -0.0005 0.1817 0.5680
2.250 0.2655 0.00819 0.00165 -0.0007 0.1670 0.5923
2.500 0.2946 0.00828 0.00175 -0.0008 0.1540 0.6162
2.750 0.3237 0.00842 0.00186 -0.0010 0.1403 0.6321
3.000 0.3528 0.00854 0.00198 -0.0011 0.1305 0.6454
3.250 0.3819 0.00864 0.00209 -0.0013 0.1231 0.6577
3.500 0.4109 0.00880 0.00222 -0.0014 0.1137 0.6686
3.750 0.4398 0.00894 0.00235 -0.0015 0.1043 0.6775
4.250 0.4968 0.00967 0.00286 -0.0019 0.0451 0.6923
4.500 0.5255 0.00988 0.00306 -0.0020 0.0405 0.6986
4.750 0.5542 0.01006 0.00326 -0.0020 0.0378 0.7045
5.000 0.5829 0.01023 0.00345 -0.0021 0.0364 0.7109
5.250 0.6115 0.01042 0.00365 -0.0022 0.0349 0.7170
5.500 0.6400 0.01062 0.00388 -0.0022 0.0337 0.7236
5.750 0.6684 0.01084 0.00413 -0.0023 0.0326 0.7306
6.000 0.6966 0.01110 0.00442 -0.0023 0.0315 0.7378
6.250 0.7248 0.01131 0.00468 -0.0024 0.0311 0.7462
6.500 0.7529 0.01151 0.00494 -0.0024 0.0307 0.7555
7.000 0.8087 0.01195 0.00551 -0.0024 0.0299 0.7813
7.250 0.8361 0.01215 0.00582 -0.0023 0.0295 0.8023
7.500 0.8626 0.01230 0.00614 -0.0020 0.0290 0.8438
7.750 0.8864 0.01227 0.00641 -0.0009 0.0284 1.0000
8.000 0.9140 0.01260 0.00675 -0.0009 0.0280 1.0000
8.250 0.9414 0.01295 0.00713 -0.0009 0.0275 1.0000
8.500 0.9686 0.01334 0.00753 -0.0009 0.0271 1.0000
8.750 0.9954 0.01377 0.00799 -0.0009 0.0265 1.0000
9.000 1.0215 0.01433 0.00859 -0.0008 0.0258 1.0000
9.250 1.0479 0.01479 0.00909 -0.0008 0.0254 1.0000
9.500 1.0747 0.01512 0.00945 -0.0007 0.0252 1.0000
9.750 1.1013 0.01547 0.00983 -0.0006 0.0248 1.0000
10.000 1.1276 0.01584 0.01024 -0.0005 0.0244 1.0000
10.250 1.1537 0.01623 0.01067 -0.0004 0.0239 1.0000
10.500 1.1796 0.01663 0.01110 -0.0003 0.0233 1.0000
10.750 1.2053 0.01704 0.01153 -0.0002 0.0228 1.0000
11.000 1.2307 0.01747 0.01198 0.0000 0.0223 1.0000
11.250 1.2557 0.01792 0.01245 0.0001 0.0218 1.0000
11.500 1.2799 0.01848 0.01303 0.0004 0.0212 1.0000
11.750 1.3033 0.01913 0.01373 0.0007 0.0207 1.0000
12.000 1.3276 0.01959 0.01425 0.0009 0.0204 1.0000
12.250 1.3516 0.02007 0.01478 0.0012 0.0200 1.0000
12.500 1.3751 0.02056 0.01532 0.0015 0.0195 1.0000
12.750 1.3984 0.02107 0.01587 0.0018 0.0189 1.0000
13.000 1.4211 0.02160 0.01644 0.0021 0.0183 1.0000
13.250 1.4433 0.02217 0.01704 0.0025 0.0178 1.0000
13.500 1.4646 0.02280 0.01769 0.0029 0.0172 1.0000
13.750 1.4843 0.02355 0.01848 0.0035 0.0167 1.0000
14.000 1.5034 0.02430 0.01932 0.0040 0.0162 1.0000
14.250 1.5214 0.02510 0.02018 0.0047 0.0156 1.0000
14.500 1.5383 0.02595 0.02108 0.0054 0.0150 1.0000
14.750 1.5530 0.02687 0.02203 0.0062 0.0143 1.0000
15.000 1.5617 0.02802 0.02323 0.0074 0.0137 1.0000
15.250 1.5679 0.02959 0.02488 0.0081 0.0133 1.0000
15.500 1.5731 0.03151 0.02690 0.0081 0.0129 1.0000
15.750 1.5771 0.03380 0.02929 0.0077 0.0125 1.0000
16.000 1.5793 0.03651 0.03210 0.0067 0.0121 1.0000
16.250 1.5788 0.03970 0.03540 0.0054 0.0118 1.0000
16.500 1.5745 0.04350 0.03930 0.0037 0.0115 1.0000
16.750 1.5658 0.04809 0.04401 0.0014 0.0112 1.0000
17.000 1.5516 0.05372 0.04977 -0.0016 0.0111 1.0000
17.250 1.5306 0.06068 0.05689 -0.0054 0.0110 1.0000
17.500 1.5018 0.06916 0.06554 -0.0101 0.0109 1.0000
17.750 1.4648 0.07904 0.07561 -0.0154 0.0110 1.0000
18.000 1.4231 0.08970 0.08645 -0.0209 0.0112 1.0000
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