GOE 484 AIRFOIL (goe484-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 484 AIRFOIL (goe484-il) Reynolds number: 200,000 Max Cl/Cd: 86.38 at α=2.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe484-il-200000-n5.txt Download as CSV file: xf-goe484-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 484 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
------ -------- --------- --------- -------- -------- --------
-8.750 -0.2498 0.09121 0.08778 -0.0395 0.9915 0.0303
-8.500 -0.2401 0.08753 0.08411 -0.0417 0.9891 0.0312
-8.250 -0.3517 0.09922 0.09566 -0.0316 0.9974 0.0290
-8.000 -0.3367 0.09596 0.09240 -0.0340 0.9949 0.0298
-7.750 -0.3232 0.09275 0.08918 -0.0370 0.9914 0.0306
-7.500 -0.3086 0.08948 0.08591 -0.0406 0.9874 0.0317
-7.250 -0.2961 0.08628 0.08271 -0.0444 0.9820 0.0334
-7.000 -0.2689 0.08149 0.07789 -0.0594 0.9734 0.0358
-6.750 -0.2409 0.07661 0.07296 -0.0691 0.9684 0.0361
-6.500 -0.2303 0.07218 0.06854 -0.0686 0.9653 0.0370
-6.250 -0.2118 0.06925 0.06559 -0.0702 0.9600 0.0379
-6.000 -0.1846 0.06585 0.06215 -0.0749 0.9569 0.0392
-5.750 -0.1625 0.06254 0.05880 -0.0793 0.9504 0.0409
-5.500 -0.1053 0.05445 0.05048 -0.0997 0.9459 0.0465
-5.250 -0.0893 0.05197 0.04801 -0.0996 0.9409 0.0474
-5.000 -0.0640 0.04928 0.04526 -0.1020 0.9367 0.0486
-4.750 -0.0297 0.04594 0.04182 -0.1072 0.9341 0.0502
-4.500 0.0052 0.04196 0.03769 -0.1129 0.9298 0.0510
-4.250 0.0604 0.02942 0.02413 -0.1254 0.9244 0.0360
-4.000 0.0941 0.02572 0.02009 -0.1286 0.9215 0.0356
-3.750 0.1290 0.02279 0.01671 -0.1314 0.9195 0.0355
-3.500 0.1535 0.02099 0.01455 -0.1313 0.9134 0.0355
-3.250 0.1847 0.01978 0.01300 -0.1322 0.9097 0.0361
-3.000 0.2170 0.01779 0.01067 -0.1337 0.9070 0.0370
-2.750 0.2472 0.01676 0.00941 -0.1342 0.9033 0.0370
-2.500 0.2737 0.01596 0.00843 -0.1340 0.8978 0.0370
-2.250 0.3046 0.01512 0.00746 -0.1346 0.8941 0.0372
-2.000 0.3374 0.01437 0.00661 -0.1355 0.8911 0.0376
-1.750 0.3632 0.01384 0.00604 -0.1350 0.8847 0.0380
-1.500 0.3928 0.01332 0.00549 -0.1352 0.8796 0.0386
-1.250 0.4253 0.01284 0.00498 -0.1361 0.8758 0.0393
-1.000 0.4514 0.01254 0.00468 -0.1356 0.8689 0.0401
-0.750 0.4811 0.01223 0.00437 -0.1358 0.8633 0.0417
-0.500 0.5116 0.01196 0.00409 -0.1362 0.8578 0.0440
-0.250 0.5388 0.01177 0.00389 -0.1359 0.8500 0.0451
0.000 0.5703 0.01155 0.00363 -0.1364 0.8441 0.0461
0.250 0.5964 0.01140 0.00351 -0.1359 0.8352 0.0484
0.500 0.6269 0.01123 0.00336 -0.1362 0.8286 0.0527
0.750 0.6531 0.01107 0.00336 -0.1357 0.8190 0.0830
1.000 0.6814 0.01092 0.00338 -0.1357 0.8102 0.1470
1.250 0.7091 0.01080 0.00339 -0.1355 0.8001 0.1922
1.500 0.7339 0.01019 0.00355 -0.1351 0.7873 0.4694
2.000 0.7905 0.00929 0.00338 -0.1343 0.7334 1.0000
2.250 0.8146 0.00943 0.00322 -0.1330 0.6827 1.0000
2.500 0.8376 0.00973 0.00321 -0.1316 0.6389 1.0000
2.750 0.8610 0.01005 0.00334 -0.1304 0.6108 1.0000
3.000 0.8838 0.01039 0.00351 -0.1292 0.5823 1.0000
3.250 0.9058 0.01076 0.00371 -0.1279 0.5488 1.0000
3.500 0.9275 0.01113 0.00394 -0.1265 0.5133 1.0000
3.750 0.9460 0.01166 0.00420 -0.1246 0.4493 1.0000
4.000 0.9520 0.01316 0.00478 -0.1208 0.2877 1.0000
4.250 0.9583 0.01506 0.00569 -0.1174 0.1123 1.0000
4.500 0.9755 0.01603 0.00636 -0.1156 0.0670 1.0000
4.750 0.9971 0.01656 0.00689 -0.1145 0.0600 1.0000
5.000 1.0191 0.01702 0.00740 -0.1134 0.0564 1.0000
5.250 1.0403 0.01756 0.00797 -0.1121 0.0535 1.0000
5.500 1.0604 0.01818 0.00864 -0.1107 0.0511 1.0000
5.750 1.0785 0.01895 0.00946 -0.1090 0.0487 1.0000
6.000 1.0986 0.01951 0.01009 -0.1077 0.0472 1.0000
6.250 1.1176 0.02016 0.01082 -0.1061 0.0457 1.0000
6.500 1.1355 0.02089 0.01161 -0.1044 0.0444 1.0000
6.750 1.1533 0.02165 0.01242 -0.1027 0.0427 1.0000
7.000 1.1708 0.02242 0.01325 -0.1010 0.0408 1.0000
7.250 1.1870 0.02336 0.01420 -0.0992 0.0392 1.0000
7.500 1.2012 0.02482 0.01567 -0.0972 0.0375 1.0000
7.750 1.2197 0.02558 0.01651 -0.0956 0.0363 1.0000
8.000 1.2379 0.02634 0.01741 -0.0941 0.0345 1.0000
8.250 1.2561 0.02729 0.01845 -0.0926 0.0329 1.0000
8.500 1.2732 0.02816 0.01939 -0.0910 0.0311 1.0000
8.750 1.2892 0.02907 0.02032 -0.0894 0.0296 1.0000
9.000 1.3083 0.03076 0.02204 -0.0885 0.0279 1.0000
9.250 1.3261 0.03179 0.02330 -0.0869 0.0267 1.0000
9.500 1.3427 0.03289 0.02458 -0.0853 0.0249 1.0000
9.750 1.3567 0.03385 0.02567 -0.0834 0.0235 1.0000
10.000 1.3689 0.03478 0.02667 -0.0814 0.0224 1.0000
10.250 1.3809 0.03597 0.02791 -0.0795 0.0216 1.0000
10.500 1.3951 0.03783 0.02997 -0.0780 0.0206 1.0000
10.750 1.4082 0.03978 0.03227 -0.0761 0.0194 1.0000
11.000 1.4175 0.04155 0.03428 -0.0740 0.0182 1.0000
11.250 1.4240 0.04294 0.03585 -0.0716 0.0174 1.0000
11.500 1.4293 0.04427 0.03730 -0.0693 0.0168 1.0000
11.750 1.4337 0.04573 0.03888 -0.0672 0.0164 1.0000
12.000 1.4368 0.04752 0.04079 -0.0651 0.0160 1.0000
12.250 1.4366 0.05006 0.04352 -0.0630 0.0156 1.0000
12.500 1.4310 0.05393 0.04781 -0.0607 0.0153 1.0000
12.750 1.4194 0.05837 0.05266 -0.0585 0.0148 1.0000
13.000 1.4045 0.06306 0.05771 -0.0568 0.0145 1.0000
13.250 1.3870 0.06812 0.06310 -0.0558 0.0143 1.0000
13.500 1.3669 0.07370 0.06897 -0.0556 0.0141 1.0000
13.750 1.3450 0.07989 0.07544 -0.0564 0.0140 1.0000
14.000 1.3204 0.08699 0.08280 -0.0585 0.0139 1.0000
14.250 1.2937 0.09515 0.09121 -0.0620 0.0140 1.0000
14.500 1.2642 0.10475 0.10104 -0.0671 0.0141 1.0000
14.750 1.2333 0.11596 0.11246 -0.0740 0.0144 1.0000
15.000 1.2012 0.12949 0.12616 -0.0832 0.0148 1.0000
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Polar data table (+)
Polar graphs
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