GOE 528 AIRFOIL (goe528-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: GOE 528 AIRFOIL (goe528-il) Reynolds number: 1,000,000 Max Cl/Cd: 128.91 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe528-il-1000000-n5.txt Download as CSV file: xf-goe528-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 528 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
------ -------- --------- --------- -------- -------- --------
-11.750 -0.5215 0.02682 0.02383 -0.1381 0.8373 0.0172
-11.500 -0.5068 0.02544 0.02229 -0.1375 0.8277 0.0174
-11.250 -0.4916 0.02406 0.02073 -0.1369 0.8184 0.0177
-11.000 -0.4753 0.02271 0.01921 -0.1363 0.8099 0.0179
-10.750 -0.4580 0.02147 0.01776 -0.1355 0.8013 0.0183
-10.500 -0.4399 0.02022 0.01630 -0.1348 0.7935 0.0187
-10.250 -0.4200 0.01918 0.01506 -0.1341 0.7860 0.0191
-10.000 -0.3991 0.01826 0.01393 -0.1334 0.7790 0.0193
-9.750 -0.3776 0.01742 0.01295 -0.1327 0.7714 0.0196
-9.500 -0.3542 0.01691 0.01235 -0.1321 0.7641 0.0198
-9.250 -0.3283 0.01674 0.01215 -0.1318 0.7570 0.0200
-9.000 -0.3032 0.01649 0.01183 -0.1313 0.7500 0.0202
-8.750 -0.2777 0.01621 0.01149 -0.1309 0.7435 0.0205
-8.500 -0.2530 0.01582 0.01100 -0.1304 0.7358 0.0207
-8.250 -0.2281 0.01543 0.01051 -0.1299 0.7286 0.0210
-8.000 -0.2032 0.01500 0.00997 -0.1294 0.7210 0.0214
-7.750 -0.1784 0.01456 0.00941 -0.1289 0.7141 0.0218
-7.500 -0.1533 0.01407 0.00879 -0.1284 0.7064 0.0221
-7.250 -0.1285 0.01361 0.00820 -0.1278 0.6982 0.0224
-7.000 -0.1030 0.01318 0.00765 -0.1273 0.6899 0.0226
-6.750 -0.0774 0.01287 0.00723 -0.1268 0.6817 0.0228
-6.500 -0.0516 0.01249 0.00674 -0.1264 0.6731 0.0231
-6.250 -0.0268 0.01200 0.00615 -0.1258 0.6636 0.0235
-6.000 -0.0010 0.01168 0.00576 -0.1253 0.6533 0.0237
-5.750 0.0251 0.01144 0.00545 -0.1249 0.6435 0.0240
-5.500 0.0510 0.01122 0.00514 -0.1244 0.6324 0.0242
-5.250 0.0772 0.01101 0.00486 -0.1240 0.6205 0.0245
-5.000 0.1033 0.01082 0.00459 -0.1235 0.6087 0.0249
-4.750 0.1293 0.01065 0.00434 -0.1230 0.5970 0.0252
-4.500 0.1555 0.01050 0.00411 -0.1226 0.5852 0.0256
-4.250 0.1817 0.01033 0.00386 -0.1221 0.5741 0.0259
-4.000 0.2079 0.01018 0.00363 -0.1216 0.5645 0.0263
-3.750 0.2342 0.01003 0.00342 -0.1212 0.5547 0.0265
-3.500 0.2607 0.00991 0.00323 -0.1208 0.5464 0.0268
-3.250 0.2873 0.00979 0.00306 -0.1204 0.5383 0.0270
-3.000 0.3138 0.00970 0.00291 -0.1200 0.5311 0.0272
-2.750 0.3402 0.00948 0.00265 -0.1196 0.5245 0.0277
-2.500 0.3665 0.00938 0.00250 -0.1192 0.5180 0.0282
-2.250 0.3935 0.00928 0.00238 -0.1189 0.5126 0.0287
-2.000 0.4204 0.00921 0.00229 -0.1186 0.5067 0.0293
-1.750 0.4470 0.00917 0.00222 -0.1182 0.5013 0.0299
-1.500 0.4742 0.00911 0.00214 -0.1180 0.4965 0.0305
-1.250 0.5012 0.00906 0.00207 -0.1177 0.4912 0.0310
-1.000 0.5279 0.00904 0.00201 -0.1173 0.4860 0.0315
-0.750 0.5549 0.00902 0.00197 -0.1170 0.4814 0.0320
-0.500 0.5820 0.00896 0.00191 -0.1168 0.4767 0.0331
-0.250 0.6088 0.00894 0.00188 -0.1165 0.4719 0.0344
0.000 0.6353 0.00896 0.00187 -0.1161 0.4669 0.0360
0.500 0.6892 0.00893 0.00186 -0.1156 0.4574 0.0440
0.750 0.7152 0.00891 0.00189 -0.1152 0.4519 0.0692
1.000 0.7418 0.00887 0.00191 -0.1149 0.4475 0.0938
1.250 0.7681 0.00881 0.00195 -0.1145 0.4423 0.1362
1.500 0.7932 0.00871 0.00202 -0.1141 0.4364 0.2226
1.750 0.8190 0.00865 0.00210 -0.1137 0.4314 0.2846
2.000 0.8440 0.00851 0.00219 -0.1132 0.4255 0.3886
2.250 0.8674 0.00836 0.00231 -0.1124 0.4189 0.5209
2.750 0.9476 0.00773 0.00265 -0.1181 0.4021 1.0000
3.000 0.9725 0.00784 0.00272 -0.1175 0.3953 1.0000
3.250 0.9966 0.00799 0.00282 -0.1167 0.3881 1.0000
3.500 1.0213 0.00811 0.00291 -0.1161 0.3823 1.0000
3.750 1.0458 0.00825 0.00301 -0.1154 0.3760 1.0000
4.000 1.0698 0.00841 0.00313 -0.1146 0.3701 1.0000
4.250 1.0944 0.00853 0.00323 -0.1140 0.3644 1.0000
4.500 1.1182 0.00870 0.00336 -0.1133 0.3578 1.0000
4.750 1.1421 0.00886 0.00350 -0.1125 0.3509 1.0000
5.000 1.1649 0.00908 0.00366 -0.1116 0.3412 1.0000
5.250 1.1881 0.00926 0.00381 -0.1108 0.3325 1.0000
5.500 1.2103 0.00949 0.00399 -0.1098 0.3238 1.0000
5.750 1.2335 0.00967 0.00415 -0.1090 0.3163 1.0000
6.000 1.2553 0.00992 0.00435 -0.1079 0.3081 1.0000
6.250 1.2777 0.01012 0.00454 -0.1070 0.3002 1.0000
6.500 1.2989 0.01037 0.00475 -0.1058 0.2930 1.0000
6.750 1.3208 0.01058 0.00495 -0.1048 0.2856 1.0000
7.000 1.3406 0.01087 0.00519 -0.1035 0.2768 1.0000
7.250 1.3594 0.01114 0.00543 -0.1019 0.2674 1.0000
7.500 1.3772 0.01141 0.00568 -0.1001 0.2599 1.0000
7.750 1.3946 0.01171 0.00595 -0.0983 0.2515 1.0000
8.000 1.4114 0.01204 0.00625 -0.0965 0.2424 1.0000
8.250 1.4286 0.01236 0.00656 -0.0947 0.2354 1.0000
8.500 1.4458 0.01269 0.00687 -0.0930 0.2282 1.0000
8.750 1.4618 0.01308 0.00723 -0.0911 0.2204 1.0000
9.000 1.4781 0.01346 0.00761 -0.0894 0.2126 1.0000
9.250 1.4925 0.01394 0.00805 -0.0874 0.2043 1.0000
9.500 1.5095 0.01431 0.00844 -0.0858 0.1989 1.0000
9.750 1.5229 0.01485 0.00895 -0.0838 0.1908 1.0000
10.000 1.5375 0.01536 0.00946 -0.0820 0.1830 1.0000
10.250 1.5481 0.01609 0.01013 -0.0798 0.1715 1.0000
10.500 1.5590 0.01682 0.01084 -0.0777 0.1625 1.0000
10.750 1.5661 0.01781 0.01176 -0.0752 0.1477 1.0000
11.000 1.5743 0.01879 0.01269 -0.0731 0.1356 1.0000
11.250 1.5682 0.02069 0.01442 -0.0696 0.1038 1.0000
11.500 1.5629 0.02272 0.01633 -0.0665 0.0841 1.0000
11.750 1.5694 0.02406 0.01768 -0.0648 0.0781 1.0000
12.000 1.5771 0.02537 0.01901 -0.0633 0.0730 1.0000
12.250 1.5841 0.02678 0.02044 -0.0619 0.0693 1.0000
12.500 1.5925 0.02812 0.02183 -0.0607 0.0661 1.0000
12.750 1.6023 0.02938 0.02314 -0.0596 0.0645 1.0000
13.000 1.6078 0.03104 0.02482 -0.0584 0.0604 1.0000
13.250 1.6120 0.03285 0.02666 -0.0573 0.0567 1.0000
13.500 1.6188 0.03449 0.02834 -0.0563 0.0543 1.0000
13.750 1.6218 0.03650 0.03039 -0.0553 0.0506 1.0000
14.000 1.6251 0.03858 0.03249 -0.0544 0.0476 1.0000
14.250 1.6289 0.04063 0.03459 -0.0537 0.0450 1.0000
14.500 1.6284 0.04317 0.03716 -0.0529 0.0416 1.0000
14.750 1.6304 0.04554 0.03957 -0.0523 0.0390 1.0000
15.000 1.6290 0.04831 0.04238 -0.0517 0.0357 1.0000
15.250 1.6277 0.05114 0.04525 -0.0513 0.0329 1.0000
15.500 1.6227 0.05443 0.04858 -0.0509 0.0292 1.0000
15.750 1.6173 0.05786 0.05205 -0.0506 0.0255 1.0000
16.000 1.6085 0.06174 0.05597 -0.0505 0.0214 1.0000
16.250 1.5994 0.06573 0.06000 -0.0505 0.0183 1.0000
16.500 1.5941 0.06933 0.06367 -0.0505 0.0171 1.0000
16.750 1.5872 0.07321 0.06762 -0.0507 0.0157 1.0000
17.250 1.5733 0.08110 0.07565 -0.0514 0.0137 1.0000
17.500 1.5675 0.08498 0.07960 -0.0519 0.0129 1.0000
17.750 1.5604 0.08912 0.08382 -0.0525 0.0123 1.0000
|
Polar data table (+)
Polar graphs
<< Back to GOE 528 AIRFOIL (goe528-il)