GOE 304 (FRIEDRICHSHAFEN G02) AIRFOIL (goe304-il) Xfoil prediction polar at RE=500,000 Ncrit=9
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Airfoil: GOE 304 (FRIEDRICHSHAFEN G02) AIRFOIL (goe304-il) Reynolds number: 500,000 Max Cl/Cd: 122.78 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe304-il-500000.txt Download as CSV file: xf-goe304-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.2610 0.11637 0.11398 -0.0365 1.0000 0.0237
-10.000 -0.2602 0.11438 0.11203 -0.0349 1.0000 0.0238
-9.750 -0.2630 0.11287 0.11056 -0.0329 1.0000 0.0240
-9.500 -0.2461 0.10942 0.10711 -0.0362 0.9983 0.0243
-9.250 -0.2289 0.10594 0.10363 -0.0399 0.9962 0.0247
-9.000 -0.2112 0.10240 0.10008 -0.0439 0.9943 0.0253
-8.750 -0.1940 0.09880 0.09647 -0.0481 0.9911 0.0264
-8.500 -0.1770 0.09480 0.09246 -0.0572 0.9858 0.0271
-8.250 -0.1605 0.09057 0.08823 -0.0663 0.9789 0.0272
-8.000 -0.1409 0.08666 0.08431 -0.0656 0.9767 0.0273
-7.750 -0.1211 0.08335 0.08100 -0.0679 0.9723 0.0276
-7.500 -0.1053 0.08049 0.07814 -0.0701 0.9631 0.0278
-7.250 -0.0897 0.07769 0.07533 -0.0728 0.9530 0.0282
-7.000 -0.0742 0.07491 0.07253 -0.0757 0.9416 0.0288
-6.750 -0.0599 0.07218 0.06977 -0.0783 0.9277 0.0295
-6.500 -0.0422 0.06903 0.06656 -0.0829 0.9134 0.0307
-6.250 -0.0041 0.06355 0.06091 -0.0995 0.8971 0.0312
-6.000 0.0066 0.06070 0.05804 -0.0982 0.8859 0.0314
-5.750 0.0218 0.05839 0.05568 -0.0980 0.8751 0.0316
-5.500 0.0402 0.05608 0.05332 -0.0992 0.8632 0.0319
-5.250 0.0617 0.05368 0.05085 -0.1015 0.8516 0.0323
-5.000 0.0856 0.05119 0.04827 -0.1044 0.8408 0.0330
-4.750 0.1126 0.04844 0.04542 -0.1081 0.8295 0.0342
-4.500 0.1641 0.04237 0.03903 -0.1199 0.8192 0.0360
-4.000 0.2058 0.03857 0.03513 -0.1208 0.7991 0.0366
-3.750 0.2309 0.03673 0.03319 -0.1221 0.7900 0.0371
-3.500 0.2585 0.03473 0.03108 -0.1238 0.7804 0.0380
-3.250 0.3050 0.03021 0.02603 -0.1289 0.7725 0.0412
-3.000 0.3275 0.02835 0.02417 -0.1294 0.7633 0.0416
-2.750 0.3523 0.02701 0.02276 -0.1299 0.7549 0.0420
-2.500 0.3786 0.02570 0.02135 -0.1304 0.7462 0.0428
-2.250 0.4067 0.02425 0.01976 -0.1310 0.7384 0.0442
-2.000 0.4414 0.02138 0.01638 -0.1321 0.7305 0.0477
-1.750 0.4673 0.02028 0.01523 -0.1323 0.7230 0.0483
-1.500 0.4943 0.01936 0.01425 -0.1325 0.7148 0.0493
-1.250 0.5241 0.01878 0.01337 -0.1324 0.7076 0.0536
-1.000 0.5522 0.01703 0.01143 -0.1327 0.6999 0.0556
-0.750 0.5793 0.01629 0.01062 -0.1328 0.6927 0.0569
-0.500 0.6073 0.01565 0.00987 -0.1328 0.6852 0.0595
-0.250 0.6359 0.01479 0.00876 -0.1327 0.6778 0.0647
0.000 0.6672 0.01286 0.00622 -0.1320 0.6714 0.0473
0.250 0.6948 0.01194 0.00523 -0.1319 0.6638 0.0480
0.500 0.7224 0.01150 0.00468 -0.1317 0.6567 0.0484
0.750 0.7498 0.01111 0.00428 -0.1314 0.6474 0.0490
1.000 0.7767 0.01086 0.00398 -0.1310 0.6365 0.0500
1.250 0.8034 0.01067 0.00372 -0.1306 0.6249 0.0513
1.500 0.8306 0.01053 0.00356 -0.1303 0.6141 0.0532
1.750 0.8574 0.01033 0.00332 -0.1300 0.6045 0.0555
2.000 0.8844 0.01018 0.00319 -0.1297 0.5943 0.0579
2.250 0.9115 0.01012 0.00313 -0.1295 0.5855 0.0607
2.500 0.9385 0.01005 0.00304 -0.1292 0.5764 0.0644
2.750 0.9656 0.01002 0.00304 -0.1290 0.5673 0.0699
3.000 0.9922 0.01004 0.00303 -0.1286 0.5574 0.0765
3.250 1.0190 0.01004 0.00307 -0.1283 0.5453 0.0924
3.500 1.0425 0.00859 0.00334 -0.1278 0.5329 1.0000
3.750 1.0684 0.00877 0.00341 -0.1273 0.5200 1.0000
4.000 1.0941 0.00896 0.00350 -0.1268 0.5069 1.0000
4.250 1.1199 0.00913 0.00362 -0.1264 0.4934 1.0000
4.500 1.1455 0.00933 0.00376 -0.1259 0.4799 1.0000
4.750 1.1708 0.00955 0.00392 -0.1254 0.4661 1.0000
5.000 1.1957 0.00979 0.00409 -0.1249 0.4519 1.0000
5.250 1.2203 0.01005 0.00429 -0.1242 0.4370 1.0000
5.500 1.2445 0.01033 0.00450 -0.1236 0.4208 1.0000
5.750 1.2682 0.01064 0.00473 -0.1229 0.4026 1.0000
6.000 1.2916 0.01097 0.00499 -0.1221 0.3842 1.0000
6.250 1.3147 0.01132 0.00526 -0.1213 0.3657 1.0000
6.500 1.3370 0.01172 0.00556 -0.1204 0.3456 1.0000
6.750 1.3587 0.01215 0.00589 -0.1194 0.3235 1.0000
7.000 1.3798 0.01261 0.00626 -0.1183 0.3012 1.0000
7.500 1.4201 0.01363 0.00708 -0.1159 0.2622 1.0000
7.750 1.4400 0.01414 0.00753 -0.1146 0.2465 1.0000
8.000 1.4592 0.01466 0.00798 -0.1133 0.2325 1.0000
8.250 1.4781 0.01519 0.00845 -0.1119 0.2189 1.0000
8.500 1.4968 0.01569 0.00892 -0.1105 0.2064 1.0000
8.750 1.5150 0.01620 0.00940 -0.1090 0.1955 1.0000
9.000 1.5303 0.01675 0.00992 -0.1070 0.1848 1.0000
9.250 1.5453 0.01734 0.01047 -0.1049 0.1736 1.0000
9.500 1.5610 0.01790 0.01101 -0.1031 0.1628 1.0000
9.750 1.5751 0.01855 0.01165 -0.1011 0.1517 1.0000
10.000 1.5881 0.01929 0.01235 -0.0990 0.1402 1.0000
10.250 1.6000 0.02011 0.01312 -0.0968 0.1289 1.0000
10.500 1.6126 0.02090 0.01389 -0.0948 0.1200 1.0000
10.750 1.6245 0.02176 0.01476 -0.0928 0.1132 1.0000
11.000 1.6355 0.02270 0.01569 -0.0908 0.1073 1.0000
11.250 1.6463 0.02369 0.01670 -0.0889 0.1027 1.0000
11.500 1.6577 0.02466 0.01771 -0.0871 0.0990 1.0000
11.750 1.6669 0.02582 0.01889 -0.0852 0.0955 1.0000
12.000 1.6744 0.02716 0.02026 -0.0833 0.0921 1.0000
12.250 1.6863 0.02819 0.02138 -0.0819 0.0897 1.0000
12.500 1.6954 0.02947 0.02272 -0.0804 0.0866 1.0000
12.750 1.7010 0.03110 0.02438 -0.0786 0.0833 1.0000
13.000 1.7076 0.03267 0.02601 -0.0771 0.0802 1.0000
13.250 1.7190 0.03387 0.02731 -0.0760 0.0769 1.0000
13.500 1.7246 0.03563 0.02911 -0.0747 0.0728 1.0000
13.750 1.7319 0.03726 0.03081 -0.0735 0.0683 1.0000
14.000 1.7377 0.03906 0.03262 -0.0724 0.0612 1.0000
14.250 1.7417 0.04108 0.03462 -0.0713 0.0505 1.0000
14.500 1.7388 0.04386 0.03735 -0.0700 0.0425 1.0000
14.750 1.7338 0.04695 0.04045 -0.0688 0.0382 1.0000
15.000 1.7300 0.05003 0.04361 -0.0678 0.0356 1.0000
15.250 1.7227 0.05363 0.04726 -0.0670 0.0336 1.0000
15.500 1.7187 0.05693 0.05067 -0.0665 0.0322 1.0000
15.750 1.7140 0.06040 0.05425 -0.0661 0.0309 1.0000
16.000 1.7068 0.06430 0.05824 -0.0658 0.0299 1.0000
16.250 1.6962 0.06874 0.06277 -0.0658 0.0289 1.0000
16.500 1.6833 0.07358 0.06772 -0.0661 0.0281 1.0000
16.750 1.6788 0.07740 0.07167 -0.0663 0.0274 1.0000
17.000 1.6719 0.08163 0.07601 -0.0667 0.0266 1.0000
17.250 1.6635 0.08614 0.08063 -0.0674 0.0260 1.0000
17.500 1.6534 0.09095 0.08556 -0.0682 0.0254 1.0000
17.750 1.6413 0.09619 0.09089 -0.0693 0.0249 1.0000
18.000 1.6275 0.10176 0.09656 -0.0706 0.0244 1.0000
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Polar data table (+)
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