GOE 547 AIRFOIL (goe547-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 547 AIRFOIL (goe547-il) Reynolds number: 500,000 Max Cl/Cd: 120.6 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe547-il-500000.txt Download as CSV file: xf-goe547-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 547 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
------ -------- --------- --------- -------- -------- --------
-9.750 -0.2428 0.08542 0.08323 -0.0598 0.9882 0.0332
-9.500 -0.2483 0.07783 0.07565 -0.0671 0.9861 0.0359
-9.250 -0.2461 0.07132 0.06914 -0.0722 0.9846 0.0361
-9.000 -0.2554 0.06374 0.06158 -0.0750 0.9810 0.0370
-8.750 -0.2425 0.06100 0.05883 -0.0765 0.9776 0.0377
-8.500 -0.2306 0.05740 0.05522 -0.0793 0.9749 0.0384
-8.250 -0.2194 0.05316 0.05098 -0.0834 0.9727 0.0396
-8.000 -0.2205 0.04786 0.04569 -0.0881 0.9654 0.0409
-7.750 -0.3206 0.03581 0.03265 -0.1150 0.9550 0.0348
-7.500 -0.3096 0.02895 0.02520 -0.1175 0.9492 0.0337
-7.250 -0.2839 0.02477 0.02051 -0.1198 0.9468 0.0343
-7.000 -0.2582 0.02209 0.01743 -0.1207 0.9433 0.0348
-6.750 -0.2354 0.02031 0.01536 -0.1204 0.9377 0.0352
-6.500 -0.2023 0.02002 0.01486 -0.1216 0.9348 0.0361
-6.250 -0.1739 0.01708 0.01155 -0.1228 0.9320 0.0366
-6.000 -0.1495 0.01548 0.00977 -0.1225 0.9265 0.0372
-5.750 -0.1210 0.01438 0.00857 -0.1229 0.9217 0.0380
-5.500 -0.0889 0.01369 0.00781 -0.1240 0.9183 0.0392
-5.250 -0.0611 0.01310 0.00715 -0.1241 0.9132 0.0401
-5.000 -0.0341 0.01249 0.00646 -0.1240 0.9075 0.0407
-4.750 -0.0033 0.01191 0.00580 -0.1246 0.9031 0.0415
-4.500 0.0217 0.01147 0.00529 -0.1240 0.8967 0.0423
-4.250 0.0488 0.01105 0.00482 -0.1239 0.8910 0.0431
-4.000 0.0783 0.01070 0.00438 -0.1242 0.8863 0.0441
-3.750 0.1023 0.01045 0.00410 -0.1233 0.8794 0.0451
-3.500 0.1291 0.00996 0.00354 -0.1231 0.8738 0.0474
-3.250 0.1547 0.00972 0.00329 -0.1226 0.8676 0.0498
-3.000 0.1812 0.00953 0.00307 -0.1223 0.8613 0.0527
-2.750 0.2095 0.00932 0.00282 -0.1223 0.8561 0.0579
-2.500 0.2340 0.00911 0.00265 -0.1215 0.8489 0.0706
-2.250 0.2614 0.00885 0.00241 -0.1214 0.8431 0.0953
-2.000 0.2847 0.00843 0.00230 -0.1206 0.8361 0.1793
-1.750 0.3109 0.00823 0.00223 -0.1203 0.8297 0.2330
-1.500 0.3367 0.00805 0.00217 -0.1199 0.8231 0.2792
-1.250 0.3617 0.00785 0.00213 -0.1193 0.8159 0.3373
-1.000 0.3876 0.00766 0.00212 -0.1190 0.8094 0.4036
-0.750 0.4118 0.00749 0.00213 -0.1182 0.8018 0.4713
-0.500 0.4376 0.00736 0.00213 -0.1177 0.7951 0.5316
-0.250 0.4612 0.00722 0.00215 -0.1167 0.7869 0.5884
0.000 0.4848 0.00705 0.00215 -0.1157 0.7785 0.6564
0.250 0.5064 0.00679 0.00213 -0.1142 0.7692 0.7368
0.500 0.5719 0.00638 0.00220 -0.1220 0.7588 0.9641
1.000 0.6527 0.00649 0.00214 -0.1275 0.7334 1.0000
1.250 0.6755 0.00657 0.00213 -0.1263 0.7224 1.0000
1.500 0.6980 0.00664 0.00216 -0.1251 0.7112 1.0000
1.750 0.7214 0.00672 0.00220 -0.1241 0.7021 1.0000
2.000 0.7450 0.00682 0.00224 -0.1231 0.6936 1.0000
2.250 0.7684 0.00691 0.00231 -0.1221 0.6846 1.0000
2.500 0.7920 0.00702 0.00238 -0.1212 0.6763 1.0000
2.750 0.8152 0.00712 0.00246 -0.1201 0.6670 1.0000
3.000 0.8379 0.00723 0.00254 -0.1189 0.6561 1.0000
3.250 0.8599 0.00736 0.00263 -0.1176 0.6435 1.0000
3.500 0.8820 0.00750 0.00272 -0.1163 0.6314 1.0000
3.750 0.9048 0.00762 0.00284 -0.1152 0.6211 1.0000
4.000 0.9275 0.00775 0.00296 -0.1141 0.6104 1.0000
4.250 0.9495 0.00790 0.00309 -0.1128 0.5975 1.0000
4.500 0.9708 0.00805 0.00322 -0.1114 0.5829 1.0000
4.750 0.9909 0.00823 0.00336 -0.1097 0.5632 1.0000
5.000 1.0089 0.00846 0.00351 -0.1076 0.5356 1.0000
5.250 1.0235 0.00879 0.00369 -0.1048 0.4953 1.0000
5.500 1.0327 0.00936 0.00397 -0.1010 0.4352 1.0000
5.750 1.0411 0.01007 0.00436 -0.0973 0.3745 1.0000
6.000 1.0523 0.01072 0.00477 -0.0941 0.3276 1.0000
6.250 1.0655 0.01127 0.00517 -0.0914 0.2936 1.0000
6.500 1.0785 0.01178 0.00554 -0.0886 0.2640 1.0000
6.750 1.0903 0.01235 0.00595 -0.0857 0.2320 1.0000
7.000 1.1036 0.01288 0.00635 -0.0830 0.2033 1.0000
7.250 1.1143 0.01356 0.00682 -0.0800 0.1595 1.0000
7.500 1.1236 0.01434 0.00739 -0.0769 0.1256 1.0000
7.750 1.1360 0.01499 0.00795 -0.0743 0.1082 1.0000
8.000 1.1504 0.01555 0.00847 -0.0721 0.0930 1.0000
8.250 1.1603 0.01637 0.00909 -0.0692 0.0614 1.0000
8.500 1.1692 0.01728 0.00989 -0.0662 0.0407 1.0000
8.750 1.1788 0.01819 0.01070 -0.0634 0.0276 1.0000
9.000 1.1912 0.01895 0.01146 -0.0611 0.0239 1.0000
9.250 1.2028 0.01977 0.01233 -0.0587 0.0217 1.0000
9.500 1.2156 0.02053 0.01315 -0.0566 0.0204 1.0000
9.750 1.2263 0.02143 0.01409 -0.0543 0.0190 1.0000
10.000 1.2335 0.02259 0.01531 -0.0516 0.0179 1.0000
10.250 1.2407 0.02378 0.01658 -0.0491 0.0173 1.0000
10.500 1.2504 0.02484 0.01773 -0.0469 0.0168 1.0000
10.750 1.2592 0.02597 0.01895 -0.0448 0.0164 1.0000
11.000 1.2666 0.02726 0.02031 -0.0426 0.0158 1.0000
11.250 1.2736 0.02861 0.02173 -0.0405 0.0154 1.0000
11.500 1.2805 0.03001 0.02320 -0.0386 0.0151 1.0000
11.750 1.2861 0.03155 0.02480 -0.0366 0.0146 1.0000
12.000 1.2893 0.03337 0.02668 -0.0345 0.0142 1.0000
12.250 1.2905 0.03548 0.02888 -0.0324 0.0138 1.0000
12.500 1.2937 0.03754 0.03104 -0.0305 0.0134 1.0000
12.750 1.3013 0.03917 0.03278 -0.0291 0.0132 1.0000
13.000 1.3093 0.04070 0.03442 -0.0279 0.0129 1.0000
13.250 1.3153 0.04259 0.03642 -0.0265 0.0127 1.0000
13.500 1.3210 0.04449 0.03843 -0.0252 0.0124 1.0000
13.750 1.3263 0.04651 0.04056 -0.0241 0.0122 1.0000
14.000 1.3306 0.04868 0.04285 -0.0229 0.0119 1.0000
14.250 1.3345 0.05098 0.04528 -0.0219 0.0119 1.0000
14.500 1.3373 0.05340 0.04782 -0.0210 0.0117 1.0000
14.750 1.3392 0.05593 0.05047 -0.0202 0.0115 1.0000
15.000 1.3399 0.05873 0.05341 -0.0196 0.0114 1.0000
15.250 1.3387 0.06168 0.05647 -0.0192 0.0112 1.0000
15.500 1.3362 0.06501 0.05997 -0.0188 0.0112 1.0000
15.750 1.3329 0.06844 0.06353 -0.0188 0.0110 1.0000
16.000 1.3276 0.07228 0.06752 -0.0190 0.0110 1.0000
16.250 1.3203 0.07649 0.07189 -0.0195 0.0109 1.0000
16.500 1.3117 0.08104 0.07661 -0.0204 0.0109 1.0000
16.750 1.3010 0.08606 0.08180 -0.0217 0.0108 1.0000
17.000 1.2895 0.09137 0.08728 -0.0234 0.0108 1.0000
17.250 1.2759 0.09722 0.09329 -0.0255 0.0107 1.0000
17.500 1.2600 0.10383 0.10010 -0.0285 0.0108 1.0000
17.750 1.2447 0.11062 0.10708 -0.0319 0.0108 1.0000
18.000 1.2297 0.11760 0.11421 -0.0357 0.0108 1.0000
18.250 1.2135 0.12509 0.12185 -0.0400 0.0107 1.0000
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