GOE 375 AIRFOIL (goe375-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 375 AIRFOIL (goe375-il) Reynolds number: 500,000 Max Cl/Cd: 88.9 at α=7.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe375-il-500000.txt Download as CSV file: xf-goe375-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 375 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.2846 0.08979 0.08770 -0.0129 1.0000 0.0120
-8.500 -0.2811 0.08652 0.08445 -0.0135 1.0000 0.0123
-8.250 -0.2777 0.08335 0.08130 -0.0142 1.0000 0.0124
-8.000 -0.2748 0.08012 0.07809 -0.0148 1.0000 0.0126
-7.750 -0.2725 0.07692 0.07492 -0.0154 1.0000 0.0129
-7.500 -0.2709 0.07386 0.07189 -0.0159 1.0000 0.0132
-7.250 -0.2705 0.07091 0.06896 -0.0162 1.0000 0.0133
-7.000 -0.2730 0.06818 0.06627 -0.0162 1.0000 0.0136
-6.750 -0.2774 0.06576 0.06390 -0.0161 1.0000 0.0138
-6.500 -0.2761 0.06276 0.06093 -0.0174 1.0000 0.0138
-6.250 -0.2740 0.05984 0.05804 -0.0195 1.0000 0.0140
-6.000 -0.2611 0.05599 0.05417 -0.0242 0.9980 0.0140
-5.750 -0.2300 0.05055 0.04865 -0.0328 0.9923 0.0141
-5.500 -0.1979 0.04515 0.04313 -0.0400 0.9859 0.0141
-5.250 -0.2272 0.05833 0.05609 -0.0377 0.9937 0.0141
-5.000 -0.2054 0.05320 0.05096 -0.0407 0.9880 0.0144
-4.750 -0.1749 0.04934 0.04706 -0.0450 0.9829 0.0147
-4.500 -0.1422 0.04583 0.04346 -0.0490 0.9739 0.0154
-4.250 -0.1040 0.04219 0.03968 -0.0534 0.9645 0.0166
-4.000 -0.0490 0.03952 0.03661 -0.0579 0.9521 0.0178
-3.750 -0.0100 0.03635 0.03317 -0.0608 0.9336 0.0178
-3.500 0.0165 0.03173 0.02847 -0.0633 0.9123 0.0181
-3.250 0.0407 0.02930 0.02590 -0.0640 0.8898 0.0185
-3.000 0.0652 0.02734 0.02374 -0.0639 0.8701 0.0191
-2.750 0.0903 0.02555 0.02171 -0.0633 0.8527 0.0205
-2.500 0.1228 0.02521 0.02091 -0.0616 0.8376 0.0222
-2.250 0.1491 0.02420 0.01951 -0.0604 0.8234 0.0224
-2.000 0.1693 0.02044 0.01570 -0.0603 0.8096 0.0230
-1.750 0.1928 0.01896 0.01408 -0.0597 0.7943 0.0238
-1.500 0.2179 0.01781 0.01274 -0.0590 0.7781 0.0251
-1.250 0.2473 0.01835 0.01286 -0.0574 0.7595 0.0280
-1.000 0.2713 0.01605 0.01034 -0.0566 0.7402 0.0288
-0.750 0.2955 0.01476 0.00896 -0.0561 0.7154 0.0299
-0.500 0.3202 0.01404 0.00802 -0.0552 0.6812 0.0319
-0.250 0.3463 0.01494 0.00847 -0.0538 0.6345 0.0351
0.000 0.0669 0.05082 0.04774 -0.0022 0.6831 0.0348
0.250 0.3937 0.01267 0.00578 -0.0523 0.5530 0.0404
0.500 0.4190 0.01240 0.00524 -0.0515 0.5221 0.0459
0.750 0.4439 0.01193 0.00468 -0.0510 0.4938 0.0509
1.000 0.4688 0.01151 0.00414 -0.0504 0.4668 0.0620
1.250 0.4937 0.01116 0.00369 -0.0499 0.4415 0.0756
1.500 0.5189 0.01084 0.00331 -0.0494 0.4203 0.0869
1.750 0.5444 0.01063 0.00304 -0.0487 0.4007 0.0878
2.250 0.5964 0.01059 0.00278 -0.0472 0.3617 0.0622
2.500 0.6228 0.01081 0.00286 -0.0467 0.3411 0.0551
2.750 0.6476 0.01071 0.00268 -0.0460 0.3219 0.0530
3.000 0.6731 0.01074 0.00264 -0.0455 0.3035 0.0521
3.250 0.6987 0.01084 0.00264 -0.0450 0.2877 0.0494
3.500 0.7243 0.01096 0.00269 -0.0445 0.2746 0.0477
3.750 0.7499 0.01110 0.00276 -0.0440 0.2637 0.0470
4.000 0.7757 0.01122 0.00284 -0.0436 0.2541 0.0475
4.250 0.8014 0.01137 0.00294 -0.0432 0.2459 0.0493
4.500 0.8270 0.01156 0.00307 -0.0428 0.2378 0.0516
4.750 0.8529 0.01171 0.00322 -0.0424 0.2307 0.0592
5.250 0.9227 0.01054 0.00384 -0.0463 0.2150 1.0000
5.500 0.9470 0.01084 0.00407 -0.0457 0.2079 1.0000
5.750 0.9724 0.01103 0.00428 -0.0452 0.2015 1.0000
6.000 0.9968 0.01133 0.00454 -0.0446 0.1942 1.0000
6.250 1.0219 0.01154 0.00478 -0.0441 0.1876 1.0000
6.500 1.0462 0.01184 0.00504 -0.0436 0.1804 1.0000
6.750 1.0712 0.01205 0.00528 -0.0431 0.1728 1.0000
7.000 1.0952 0.01238 0.00558 -0.0425 0.1654 1.0000
7.250 1.1201 0.01260 0.00585 -0.0420 0.1597 1.0000
7.500 1.1440 0.01292 0.00614 -0.0415 0.1526 1.0000
7.750 1.1687 0.01316 0.00642 -0.0410 0.1460 1.0000
8.000 1.1922 0.01350 0.00676 -0.0404 0.1389 1.0000
8.250 1.2167 0.01375 0.00706 -0.0399 0.1323 1.0000
8.500 1.2400 0.01411 0.00740 -0.0394 0.1229 1.0000
8.750 1.2631 0.01449 0.00775 -0.0388 0.1105 1.0000
9.000 1.2839 0.01516 0.00826 -0.0379 0.0794 1.0000
9.250 1.2913 0.01742 0.01005 -0.0354 0.0193 1.0000
9.500 1.3104 0.01826 0.01101 -0.0341 0.0168 1.0000
9.750 1.3277 0.01927 0.01216 -0.0327 0.0147 1.0000
10.000 1.3439 0.02034 0.01341 -0.0311 0.0136 1.0000
10.250 1.3601 0.02131 0.01453 -0.0296 0.0130 1.0000
10.500 1.3744 0.02239 0.01575 -0.0279 0.0124 1.0000
10.750 1.3861 0.02360 0.01709 -0.0259 0.0118 1.0000
11.000 1.3953 0.02489 0.01851 -0.0236 0.0113 1.0000
11.250 1.3992 0.02635 0.02009 -0.0208 0.0108 1.0000
11.500 1.3950 0.02798 0.02183 -0.0169 0.0103 1.0000
11.750 1.3876 0.02996 0.02395 -0.0134 0.0101 1.0000
12.000 1.3764 0.03251 0.02663 -0.0106 0.0099 1.0000
12.250 1.3600 0.03602 0.03031 -0.0088 0.0097 1.0000
12.500 1.3555 0.03889 0.03331 -0.0083 0.0095 1.0000
12.750 1.3516 0.04199 0.03654 -0.0083 0.0095 1.0000
13.000 1.3470 0.04546 0.04014 -0.0089 0.0094 1.0000
13.250 1.3424 0.04924 0.04406 -0.0099 0.0093 1.0000
13.500 1.3374 0.05332 0.04827 -0.0114 0.0092 1.0000
13.750 1.3320 0.05771 0.05279 -0.0133 0.0090 1.0000
14.000 1.3243 0.06244 0.05764 -0.0151 0.0089 1.0000
14.250 1.3158 0.06721 0.06253 -0.0169 0.0089 1.0000
14.500 1.3077 0.07204 0.06747 -0.0187 0.0088 1.0000
14.750 1.2994 0.07688 0.07243 -0.0206 0.0088 1.0000
15.000 1.2912 0.08190 0.07756 -0.0226 0.0087 1.0000
15.250 1.2834 0.08697 0.08274 -0.0248 0.0086 1.0000
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Polar data table (+)
Polar graphs
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