GOE 304 (FRIEDRICHSHAFEN G02) AIRFOIL (goe304-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 304 (FRIEDRICHSHAFEN G02) AIRFOIL (goe304-il) Reynolds number: 1,000,000 Max Cl/Cd: 117.18 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe304-il-1000000-n5.txt Download as CSV file: xf-goe304-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 304 (FRIEDRICHSHAFEN G02) 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
------ -------- --------- --------- -------- -------- --------
-9.250 -0.1930 0.09230 0.09028 -0.0580 0.9034 0.0156
-9.000 -0.1833 0.09035 0.08827 -0.0587 0.8856 0.0157
-8.750 -0.1733 0.08839 0.08624 -0.0595 0.8687 0.0159
-8.500 -0.1632 0.08631 0.08410 -0.0605 0.8533 0.0161
-8.250 -0.1531 0.08409 0.08182 -0.0618 0.8391 0.0163
-8.000 -0.1439 0.08156 0.07923 -0.0633 0.8254 0.0165
-7.750 -0.1348 0.07888 0.07650 -0.0652 0.8121 0.0167
-7.500 -0.1248 0.07609 0.07367 -0.0677 0.8001 0.0170
-7.250 -0.1109 0.07289 0.07041 -0.0714 0.7894 0.0172
-7.000 -0.0965 0.06631 0.06376 -0.0803 0.7783 0.0184
-6.750 -0.0773 0.06407 0.06147 -0.0831 0.7681 0.0185
-6.500 -0.0570 0.06171 0.05906 -0.0863 0.7578 0.0186
-6.250 -0.0352 0.05919 0.05649 -0.0898 0.7472 0.0188
-6.000 -0.0122 0.05648 0.05372 -0.0936 0.7371 0.0190
-5.750 0.0122 0.05356 0.05071 -0.0978 0.7264 0.0192
-5.500 0.0385 0.05040 0.04748 -0.1023 0.7168 0.0194
-5.000 0.0960 0.04346 0.04034 -0.1118 0.6989 0.0202
-4.000 0.2266 0.01197 0.00654 -0.1340 0.6723 0.0244
-3.750 0.2544 0.01123 0.00560 -0.1340 0.6649 0.0246
-3.500 0.2819 0.01059 0.00479 -0.1340 0.6575 0.0249
-3.250 0.3100 0.01026 0.00438 -0.1340 0.6508 0.0252
-3.000 0.3381 0.01009 0.00416 -0.1339 0.6436 0.0255
-2.750 0.3661 0.00995 0.00397 -0.1338 0.6372 0.0258
-2.500 0.3943 0.00978 0.00376 -0.1338 0.6306 0.0262
-2.250 0.4223 0.00958 0.00348 -0.1337 0.6238 0.0265
-2.000 0.4504 0.00937 0.00321 -0.1336 0.6182 0.0269
-1.750 0.4786 0.00917 0.00296 -0.1335 0.6115 0.0273
-1.250 0.5347 0.00887 0.00255 -0.1334 0.5994 0.0280
-1.000 0.5628 0.00876 0.00240 -0.1333 0.5928 0.0283
-0.750 0.5906 0.00862 0.00222 -0.1332 0.5863 0.0288
-0.500 0.6188 0.00854 0.00214 -0.1331 0.5798 0.0294
-0.250 0.6467 0.00851 0.00208 -0.1330 0.5724 0.0299
0.000 0.6744 0.00849 0.00204 -0.1328 0.5604 0.0306
0.250 0.7011 0.00856 0.00200 -0.1325 0.5388 0.0315
0.500 0.7278 0.00864 0.00198 -0.1322 0.5155 0.0321
0.750 0.7548 0.00868 0.00194 -0.1320 0.4981 0.0329
1.000 0.7821 0.00872 0.00195 -0.1318 0.4858 0.0338
1.250 0.8092 0.00879 0.00197 -0.1316 0.4719 0.0348
1.500 0.8360 0.00889 0.00201 -0.1313 0.4549 0.0360
1.750 0.8625 0.00902 0.00206 -0.1310 0.4373 0.0372
2.000 0.8894 0.00912 0.00213 -0.1307 0.4232 0.0390
2.250 0.9163 0.00922 0.00219 -0.1305 0.4114 0.0410
2.500 0.9430 0.00933 0.00227 -0.1303 0.3994 0.0429
2.750 0.9695 0.00946 0.00236 -0.1300 0.3866 0.0451
3.000 0.9961 0.00959 0.00245 -0.1297 0.3734 0.0473
3.250 1.0224 0.00973 0.00256 -0.1294 0.3596 0.0504
3.500 1.0484 0.00991 0.00268 -0.1290 0.3438 0.0536
3.750 1.0732 0.01018 0.00285 -0.1285 0.3211 0.0578
4.000 1.0980 0.01045 0.00304 -0.1280 0.2978 0.0660
4.250 1.1224 0.01066 0.00331 -0.1275 0.2745 0.1609
4.750 1.1683 0.00997 0.00397 -0.1262 0.2389 1.0000
5.000 1.1928 0.01028 0.00419 -0.1256 0.2245 1.0000
5.250 1.2175 0.01056 0.00440 -0.1251 0.2124 1.0000
5.500 1.2423 0.01083 0.00461 -0.1245 0.2028 1.0000
5.750 1.2666 0.01112 0.00485 -0.1240 0.1932 1.0000
6.000 1.2912 0.01138 0.00507 -0.1234 0.1851 1.0000
6.250 1.3151 0.01168 0.00532 -0.1228 0.1763 1.0000
6.500 1.3385 0.01202 0.00559 -0.1221 0.1657 1.0000
6.750 1.3624 0.01230 0.00584 -0.1215 0.1588 1.0000
7.000 1.3857 0.01261 0.00612 -0.1207 0.1513 1.0000
7.250 1.4089 0.01291 0.00640 -0.1200 0.1442 1.0000
7.500 1.4304 0.01333 0.00674 -0.1190 0.1323 1.0000
7.750 1.4504 0.01383 0.00714 -0.1178 0.1156 1.0000
8.000 1.4688 0.01441 0.00761 -0.1163 0.0993 1.0000
8.250 1.4890 0.01484 0.00801 -0.1152 0.0931 1.0000
8.500 1.5095 0.01523 0.00839 -0.1140 0.0899 1.0000
8.750 1.5290 0.01563 0.00879 -0.1127 0.0866 1.0000
9.000 1.5475 0.01600 0.00917 -0.1112 0.0840 1.0000
9.250 1.5656 0.01638 0.00958 -0.1096 0.0821 1.0000
9.500 1.5828 0.01682 0.01003 -0.1080 0.0800 1.0000
9.750 1.5996 0.01730 0.01051 -0.1063 0.0781 1.0000
10.000 1.6160 0.01780 0.01103 -0.1046 0.0761 1.0000
10.250 1.6318 0.01834 0.01160 -0.1029 0.0740 1.0000
10.500 1.6492 0.01880 0.01210 -0.1014 0.0729 1.0000
10.750 1.6662 0.01928 0.01262 -0.1000 0.0718 1.0000
11.000 1.6824 0.01982 0.01321 -0.0985 0.0700 1.0000
11.250 1.6972 0.02047 0.01388 -0.0969 0.0676 1.0000
11.500 1.7104 0.02123 0.01464 -0.0951 0.0648 1.0000
11.750 1.7246 0.02195 0.01540 -0.0936 0.0625 1.0000
12.000 1.7384 0.02272 0.01620 -0.0920 0.0586 1.0000
12.250 1.7480 0.02379 0.01723 -0.0901 0.0513 1.0000
12.500 1.7512 0.02539 0.01873 -0.0877 0.0397 1.0000
12.750 1.7563 0.02690 0.02024 -0.0856 0.0341 1.0000
13.000 1.7623 0.02841 0.02177 -0.0837 0.0307 1.0000
13.250 1.7698 0.02984 0.02325 -0.0821 0.0285 1.0000
13.500 1.7759 0.03144 0.02489 -0.0805 0.0265 1.0000
13.750 1.7820 0.03308 0.02657 -0.0790 0.0249 1.0000
14.000 1.7888 0.03470 0.02825 -0.0777 0.0235 1.0000
14.250 1.7936 0.03655 0.03015 -0.0764 0.0222 1.0000
14.500 1.7977 0.03849 0.03214 -0.0751 0.0210 1.0000
14.750 1.8028 0.04039 0.03411 -0.0740 0.0200 1.0000
15.000 1.8063 0.04250 0.03629 -0.0730 0.0190 1.0000
15.250 1.8081 0.04485 0.03869 -0.0720 0.0179 1.0000
15.500 1.8105 0.04718 0.04109 -0.0712 0.0171 1.0000
15.750 1.8125 0.04963 0.04361 -0.0705 0.0164 1.0000
16.000 1.8127 0.05233 0.04637 -0.0698 0.0155 1.0000
16.250 1.8119 0.05521 0.04932 -0.0692 0.0149 1.0000
16.500 1.8110 0.05813 0.05231 -0.0688 0.0143 1.0000
16.750 1.8104 0.06109 0.05536 -0.0685 0.0139 1.0000
17.000 1.8087 0.06423 0.05859 -0.0682 0.0134 1.0000
17.250 1.8058 0.06759 0.06203 -0.0681 0.0130 1.0000
17.500 1.8015 0.07117 0.06569 -0.0681 0.0126 1.0000
17.750 1.7959 0.07497 0.06957 -0.0683 0.0122 1.0000
18.000 1.7892 0.07900 0.07369 -0.0685 0.0119 1.0000
18.250 1.7832 0.08301 0.07780 -0.0690 0.0116 1.0000
18.500 1.7769 0.08711 0.08199 -0.0695 0.0114 1.0000
18.750 1.7694 0.09141 0.08640 -0.0702 0.0112 1.0000
19.000 1.7610 0.09592 0.09102 -0.0710 0.0110 1.0000
19.250 1.7518 0.10062 0.09581 -0.0720 0.0107 1.0000
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