GOE 304 (FRIEDRICHSHAFEN G02) AIRFOIL (goe304-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 304 (FRIEDRICHSHAFEN G02) AIRFOIL (goe304-il) Reynolds number: 1,000,000 Max Cl/Cd: 145.35 at α=3.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe304-il-1000000.txt Download as CSV file: xf-goe304-il-1000000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.1380 0.08644 0.08470 -0.0634 0.9615 0.0210
-8.000 -0.1285 0.08401 0.08225 -0.0645 0.9462 0.0214
-7.750 -0.1205 0.08160 0.07979 -0.0655 0.9290 0.0218
-7.500 -0.1124 0.07910 0.07723 -0.0667 0.9115 0.0223
-7.250 -0.1009 0.07552 0.07357 -0.0721 0.8929 0.0233
-7.000 -0.0821 0.07103 0.06899 -0.0811 0.8759 0.0235
-6.750 -0.0667 0.06686 0.06475 -0.0851 0.8621 0.0236
-6.500 -0.0520 0.06463 0.06247 -0.0852 0.8497 0.0238
-6.250 -0.0342 0.06232 0.06011 -0.0870 0.8374 0.0239
-6.000 -0.0144 0.05996 0.05768 -0.0896 0.8252 0.0242
-5.750 0.0074 0.05747 0.05512 -0.0927 0.8131 0.0245
-5.500 0.0311 0.05482 0.05241 -0.0963 0.8019 0.0249
-5.250 0.0565 0.05199 0.04949 -0.1003 0.7911 0.0256
-5.000 0.1043 0.04584 0.04314 -0.1124 0.7809 0.0271
-4.750 0.1296 0.04161 0.03880 -0.1162 0.7715 0.0274
-4.500 0.1525 0.03982 0.03694 -0.1174 0.7616 0.0276
-4.250 0.1774 0.03805 0.03511 -0.1188 0.7523 0.0278
-4.000 0.2039 0.03621 0.03317 -0.1205 0.7430 0.0282
-3.750 0.2324 0.03414 0.03102 -0.1226 0.7341 0.0289
-3.500 0.2629 0.03170 0.02842 -0.1248 0.7254 0.0301
-3.250 0.3040 0.02540 0.02171 -0.1294 0.7182 0.0315
-3.000 0.3292 0.02431 0.02055 -0.1299 0.7095 0.0318
-2.750 0.3557 0.02333 0.01950 -0.1303 0.7016 0.0322
-2.500 0.3829 0.02217 0.01822 -0.1308 0.6935 0.0327
-2.250 0.4173 0.01956 0.01518 -0.1313 0.6866 0.0358
-2.000 0.4443 0.01673 0.01211 -0.1321 0.6792 0.0364
-1.750 0.4714 0.01599 0.01129 -0.1323 0.6722 0.0367
-1.500 0.4991 0.01533 0.01056 -0.1324 0.6649 0.0372
-1.000 0.5575 0.01079 0.00518 -0.1323 0.6519 0.0335
-0.750 0.5856 0.01016 0.00440 -0.1322 0.6448 0.0339
-0.500 0.6135 0.00971 0.00383 -0.1321 0.6382 0.0344
-0.250 0.6416 0.00937 0.00341 -0.1320 0.6310 0.0350
0.000 0.6692 0.00921 0.00316 -0.1318 0.6223 0.0356
0.250 0.6967 0.00884 0.00275 -0.1316 0.6112 0.0367
0.500 0.7242 0.00878 0.00267 -0.1314 0.5987 0.0377
0.750 0.7515 0.00871 0.00255 -0.1312 0.5868 0.0387
1.000 0.7791 0.00863 0.00243 -0.1310 0.5773 0.0398
1.250 0.8069 0.00859 0.00237 -0.1309 0.5695 0.0408
1.500 0.8345 0.00842 0.00219 -0.1308 0.5608 0.0423
1.750 0.8621 0.00841 0.00217 -0.1306 0.5522 0.0441
2.000 0.8894 0.00844 0.00218 -0.1304 0.5417 0.0462
2.250 0.9168 0.00841 0.00212 -0.1303 0.5300 0.0484
2.500 0.9439 0.00844 0.00212 -0.1301 0.5166 0.0511
2.750 0.9706 0.00852 0.00216 -0.1298 0.5020 0.0538
3.000 0.9974 0.00858 0.00218 -0.1295 0.4884 0.0585
3.500 1.0507 0.00876 0.00231 -0.1290 0.4612 0.0727
3.750 1.0741 0.00739 0.00269 -0.1286 0.4486 1.0000
4.000 1.1003 0.00759 0.00280 -0.1283 0.4348 1.0000
4.250 1.1263 0.00780 0.00293 -0.1279 0.4208 1.0000
4.500 1.1521 0.00802 0.00307 -0.1275 0.4062 1.0000
4.750 1.1776 0.00827 0.00322 -0.1271 0.3902 1.0000
5.000 1.2029 0.00852 0.00339 -0.1266 0.3729 1.0000
5.250 1.2279 0.00879 0.00358 -0.1261 0.3552 1.0000
5.500 1.2524 0.00911 0.00379 -0.1256 0.3346 1.0000
5.750 1.2758 0.00950 0.00405 -0.1248 0.3109 1.0000
6.000 1.2994 0.00986 0.00431 -0.1241 0.2886 1.0000
6.250 1.3223 0.01028 0.00460 -0.1233 0.2668 1.0000
6.500 1.3450 0.01069 0.00490 -0.1225 0.2472 1.0000
6.750 1.3680 0.01107 0.00520 -0.1217 0.2314 1.0000
7.250 1.4138 0.01180 0.00580 -0.1202 0.2062 1.0000
7.500 1.4363 0.01217 0.00612 -0.1194 0.1940 1.0000
7.750 1.4584 0.01255 0.00645 -0.1185 0.1830 1.0000
8.000 1.4799 0.01296 0.00680 -0.1175 0.1723 1.0000
8.250 1.5016 0.01333 0.00713 -0.1166 0.1618 1.0000
8.500 1.5223 0.01376 0.00751 -0.1155 0.1498 1.0000
8.750 1.5417 0.01425 0.00793 -0.1141 0.1361 1.0000
9.000 1.5589 0.01484 0.00842 -0.1125 0.1195 1.0000
9.250 1.5748 0.01546 0.00894 -0.1106 0.1058 1.0000
9.500 1.5904 0.01597 0.00943 -0.1087 0.0991 1.0000
9.750 1.6052 0.01654 0.00997 -0.1066 0.0934 1.0000
10.000 1.6220 0.01700 0.01046 -0.1049 0.0906 1.0000
10.250 1.6380 0.01751 0.01099 -0.1031 0.0882 1.0000
10.500 1.6528 0.01810 0.01159 -0.1012 0.0855 1.0000
10.750 1.6663 0.01878 0.01228 -0.0992 0.0823 1.0000
11.000 1.6820 0.01934 0.01289 -0.0976 0.0804 1.0000
11.250 1.6984 0.01987 0.01347 -0.0962 0.0788 1.0000
11.500 1.7131 0.02052 0.01416 -0.0945 0.0766 1.0000
11.750 1.7260 0.02130 0.01495 -0.0928 0.0741 1.0000
12.000 1.7370 0.02224 0.01592 -0.0908 0.0709 1.0000
12.250 1.7529 0.02286 0.01660 -0.0895 0.0688 1.0000
12.500 1.7663 0.02367 0.01743 -0.0881 0.0649 1.0000
12.750 1.7767 0.02473 0.01848 -0.0863 0.0595 1.0000
13.000 1.7825 0.02616 0.01984 -0.0843 0.0473 1.0000
13.250 1.7816 0.02817 0.02177 -0.0818 0.0370 1.0000
13.500 1.7837 0.03006 0.02366 -0.0797 0.0325 1.0000
13.750 1.7871 0.03188 0.02553 -0.0779 0.0299 1.0000
14.000 1.7899 0.03383 0.02753 -0.0763 0.0278 1.0000
14.250 1.7948 0.03565 0.02941 -0.0749 0.0264 1.0000
14.500 1.7966 0.03780 0.03161 -0.0735 0.0250 1.0000
14.750 1.7964 0.04021 0.03409 -0.0721 0.0236 1.0000
15.000 1.8012 0.04220 0.03615 -0.0711 0.0228 1.0000
15.250 1.8035 0.04449 0.03852 -0.0702 0.0220 1.0000
15.500 1.8035 0.04709 0.04119 -0.0692 0.0211 1.0000
15.750 1.8004 0.05011 0.04428 -0.0684 0.0203 1.0000
16.000 1.7983 0.05311 0.04737 -0.0677 0.0197 1.0000
16.250 1.7995 0.05578 0.05012 -0.0673 0.0192 1.0000
16.500 1.7989 0.05870 0.05314 -0.0669 0.0187 1.0000
16.750 1.7966 0.06189 0.05642 -0.0666 0.0182 1.0000
17.000 1.7926 0.06539 0.05999 -0.0664 0.0177 1.0000
17.250 1.7860 0.06927 0.06396 -0.0665 0.0172 1.0000
17.500 1.7752 0.07379 0.06858 -0.0666 0.0168 1.0000
17.750 1.7660 0.07822 0.07311 -0.0670 0.0164 1.0000
18.000 1.7617 0.08201 0.07701 -0.0674 0.0161 1.0000
18.250 1.7552 0.08618 0.08128 -0.0680 0.0159 1.0000
18.500 1.7473 0.09058 0.08578 -0.0687 0.0156 1.0000
18.750 1.7382 0.09524 0.09054 -0.0696 0.0153 1.0000
19.000 1.7281 0.10012 0.09553 -0.0707 0.0151 1.0000
19.250 1.7170 0.10525 0.10076 -0.0720 0.0149 1.0000
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Polar data table (+)
Polar graphs
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