GOE 504 AIRFOIL (goe504-il) Xfoil prediction polar at RE=200,000 Ncrit=5
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Airfoil: GOE 504 AIRFOIL (goe504-il) Reynolds number: 200,000 Max Cl/Cd: 62.79 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe504-il-200000-n5.txt Download as CSV file: xf-goe504-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 504 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.750 -0.2982 0.07902 0.07534 -0.1004 0.9666 0.0226
-12.500 -0.3466 0.06402 0.06007 -0.1139 0.9610 0.0220
-12.250 -0.3731 0.05423 0.04998 -0.1246 0.9516 0.0220
-12.000 -0.3826 0.04668 0.04205 -0.1354 0.9451 0.0223
-11.500 -0.4017 0.03885 0.03350 -0.1413 0.9187 0.0231
-11.250 -0.4069 0.03659 0.03089 -0.1402 0.9051 0.0234
-11.000 -0.4051 0.03466 0.02872 -0.1385 0.8933 0.0238
-10.750 -0.3909 0.03301 0.02696 -0.1382 0.8838 0.0243
-10.500 -0.3800 0.03176 0.02557 -0.1368 0.8725 0.0248
-10.250 -0.3659 0.03058 0.02425 -0.1357 0.8623 0.0255
-10.000 -0.3508 0.02933 0.02278 -0.1347 0.8530 0.0264
-9.750 -0.3389 0.02831 0.02151 -0.1329 0.8422 0.0273
-9.500 -0.3244 0.02730 0.02020 -0.1313 0.8327 0.0282
-9.250 -0.3073 0.02622 0.01888 -0.1301 0.8236 0.0288
-9.000 -0.2880 0.02498 0.01762 -0.1292 0.8149 0.0296
-8.750 -0.2675 0.02408 0.01663 -0.1285 0.8067 0.0306
-8.500 -0.2494 0.02334 0.01578 -0.1272 0.7978 0.0317
-8.250 -0.2282 0.02258 0.01486 -0.1263 0.7903 0.0327
-8.000 -0.2094 0.02191 0.01406 -0.1249 0.7817 0.0335
-7.750 -0.1877 0.02130 0.01328 -0.1240 0.7745 0.0342
-7.500 -0.1701 0.02048 0.01243 -0.1225 0.7665 0.0352
-7.250 -0.1511 0.01977 0.01167 -0.1213 0.7593 0.0363
-7.000 -0.1322 0.01922 0.01107 -0.1199 0.7519 0.0374
-6.750 -0.1124 0.01871 0.01047 -0.1186 0.7447 0.0381
-6.500 -0.0921 0.01825 0.00992 -0.1173 0.7380 0.0390
-6.250 -0.0720 0.01786 0.00943 -0.1160 0.7307 0.0403
-6.000 -0.0497 0.01749 0.00892 -0.1151 0.7247 0.0413
-5.750 -0.0312 0.01705 0.00844 -0.1135 0.7174 0.0426
-5.500 -0.0093 0.01669 0.00798 -0.1125 0.7110 0.0438
-5.250 0.0126 0.01640 0.00759 -0.1114 0.7045 0.0451
-5.000 0.0351 0.01615 0.00724 -0.1105 0.6978 0.0467
-4.750 0.0591 0.01590 0.00689 -0.1098 0.6921 0.0495
-4.500 0.0806 0.01563 0.00663 -0.1086 0.6850 0.0542
-4.250 0.1038 0.01534 0.00634 -0.1078 0.6789 0.0673
-4.000 0.1261 0.01504 0.00608 -0.1069 0.6728 0.0941
-3.750 0.1462 0.01454 0.00581 -0.1056 0.6663 0.1435
-3.500 0.1689 0.01425 0.00571 -0.1049 0.6607 0.2168
-3.250 0.1918 0.01418 0.00566 -0.1039 0.6537 0.2372
-3.000 0.2164 0.01414 0.00558 -0.1033 0.6476 0.2566
-2.750 0.2407 0.01411 0.00551 -0.1026 0.6416 0.2734
-2.500 0.2641 0.01408 0.00546 -0.1018 0.6350 0.2873
-2.250 0.2893 0.01406 0.00536 -0.1013 0.6294 0.2964
-2.000 0.3125 0.01404 0.00532 -0.1004 0.6229 0.3070
-1.750 0.3362 0.01400 0.00526 -0.0996 0.6166 0.3186
-1.500 0.3601 0.01397 0.00521 -0.0989 0.6110 0.3339
-1.250 0.3826 0.01393 0.00520 -0.0980 0.6044 0.3498
-1.000 0.4061 0.01389 0.00515 -0.0972 0.5985 0.3665
-0.750 0.4285 0.01385 0.00515 -0.0962 0.5925 0.3838
-0.500 0.4507 0.01380 0.00513 -0.0952 0.5862 0.4018
-0.250 0.4739 0.01376 0.00509 -0.0943 0.5809 0.4227
0.000 0.4948 0.01371 0.00513 -0.0930 0.5744 0.4464
0.250 0.5161 0.01364 0.00513 -0.0918 0.5686 0.4795
0.500 0.5363 0.01353 0.00516 -0.0904 0.5631 0.5285
0.750 0.5539 0.01337 0.00525 -0.0884 0.5571 0.6003
1.000 0.5724 0.01317 0.00534 -0.0864 0.5516 0.6964
1.250 0.6043 0.01307 0.00556 -0.0870 0.5456 0.8113
1.500 0.6683 0.01328 0.00586 -0.0946 0.5383 0.8964
1.750 0.7214 0.01353 0.00602 -0.1000 0.5322 0.9351
2.000 0.7628 0.01374 0.00620 -0.1031 0.5254 0.9582
2.250 0.8016 0.01396 0.00633 -0.1056 0.5193 0.9744
2.500 0.8384 0.01417 0.00650 -0.1079 0.5129 0.9878
2.750 0.8779 0.01440 0.00667 -0.1107 0.5063 0.9988
3.000 0.8977 0.01457 0.00676 -0.1094 0.5009 1.0000
3.250 0.9114 0.01472 0.00690 -0.1069 0.4949 1.0000
3.500 0.9259 0.01488 0.00701 -0.1045 0.4893 1.0000
3.750 0.9404 0.01506 0.00713 -0.1021 0.4838 1.0000
4.000 0.9536 0.01523 0.00729 -0.0994 0.4778 1.0000
4.250 0.9660 0.01540 0.00742 -0.0966 0.4723 1.0000
4.500 0.9782 0.01558 0.00758 -0.0938 0.4669 1.0000
4.750 0.9901 0.01577 0.00776 -0.0909 0.4609 1.0000
5.000 1.0035 0.01599 0.00792 -0.0883 0.4556 1.0000
5.250 1.0171 0.01621 0.00815 -0.0859 0.4500 1.0000
5.500 1.0305 0.01646 0.00839 -0.0834 0.4440 1.0000
5.750 1.0452 0.01673 0.00861 -0.0813 0.4388 1.0000
6.250 1.0736 0.01732 0.00922 -0.0770 0.4270 1.0000
6.500 1.0881 0.01765 0.00952 -0.0749 0.4215 1.0000
6.750 1.1024 0.01799 0.00990 -0.0729 0.4153 1.0000
7.000 1.1166 0.01837 0.01026 -0.0709 0.4096 1.0000
7.250 1.1314 0.01875 0.01066 -0.0691 0.4042 1.0000
7.500 1.1457 0.01917 0.01111 -0.0673 0.3984 1.0000
7.750 1.1600 0.01961 0.01153 -0.0655 0.3932 1.0000
8.000 1.1743 0.02008 0.01205 -0.0638 0.3876 1.0000
8.250 1.1876 0.02059 0.01258 -0.0620 0.3816 1.0000
8.500 1.2008 0.02113 0.01309 -0.0602 0.3762 1.0000
8.750 1.2141 0.02170 0.01373 -0.0585 0.3703 1.0000
9.000 1.2251 0.02236 0.01439 -0.0566 0.3634 1.0000
9.250 1.2344 0.02310 0.01516 -0.0545 0.3553 1.0000
9.500 1.2428 0.02393 0.01597 -0.0525 0.3472 1.0000
9.750 1.2510 0.02482 0.01690 -0.0505 0.3383 1.0000
10.000 1.2571 0.02585 0.01789 -0.0484 0.3296 1.0000
10.250 1.2653 0.02686 0.01896 -0.0467 0.3210 1.0000
10.500 1.2720 0.02798 0.02008 -0.0449 0.3131 1.0000
10.750 1.2791 0.02915 0.02129 -0.0433 0.3047 1.0000
11.000 1.2853 0.03042 0.02257 -0.0417 0.2970 1.0000
11.250 1.2904 0.03183 0.02400 -0.0401 0.2880 1.0000
11.500 1.2946 0.03336 0.02556 -0.0386 0.2784 1.0000
11.750 1.2953 0.03519 0.02738 -0.0370 0.2678 1.0000
12.000 1.3001 0.03683 0.02906 -0.0358 0.2589 1.0000
12.250 1.3012 0.03880 0.03104 -0.0344 0.2481 1.0000
12.500 1.3006 0.04099 0.03323 -0.0331 0.2375 1.0000
12.750 1.2984 0.04340 0.03564 -0.0319 0.2257 1.0000
13.000 1.2925 0.04626 0.03847 -0.0307 0.2110 1.0000
13.250 1.2843 0.04943 0.04160 -0.0296 0.1931 1.0000
13.500 1.2737 0.05297 0.04507 -0.0286 0.1733 1.0000
13.750 1.2622 0.05673 0.04877 -0.0278 0.1540 1.0000
14.000 1.2335 0.06243 0.05426 -0.0269 0.1205 1.0000
14.250 1.2078 0.06806 0.05974 -0.0263 0.0918 1.0000
14.500 1.1790 0.07428 0.06581 -0.0260 0.0556 1.0000
14.750 1.1542 0.08030 0.07177 -0.0260 0.0298 1.0000
15.000 1.1447 0.08459 0.07610 -0.0263 0.0240 1.0000
15.250 1.1377 0.08866 0.08025 -0.0266 0.0211 1.0000
15.500 1.1351 0.09217 0.08386 -0.0269 0.0202 1.0000
15.750 1.1312 0.09593 0.08772 -0.0274 0.0192 1.0000
16.000 1.1254 0.10002 0.09193 -0.0280 0.0182 1.0000
16.250 1.1207 0.10400 0.09602 -0.0287 0.0177 1.0000
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