GOE 384 AIRFOIL (goe384-il) Xfoil prediction polar at RE=500,000 Ncrit=9
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Airfoil: GOE 384 AIRFOIL (goe384-il) Reynolds number: 500,000 Max Cl/Cd: 87.06 at α=2° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe384-il-500000.txt Download as CSV file: xf-goe384-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 384 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
------ -------- --------- --------- -------- -------- --------
-9.750 -0.0081 0.08877 0.08487 -0.0884 0.6650 0.0496
-9.500 -0.1930 0.04712 0.04296 -0.1241 0.6701 0.0471
-9.250 -0.1880 0.04459 0.04030 -0.1245 0.6656 0.0472
-9.000 -0.1783 0.04249 0.03813 -0.1248 0.6621 0.0474
-8.750 -0.2052 0.03361 0.02864 -0.1246 0.6599 0.0457
-8.500 -0.2119 0.02772 0.02203 -0.1231 0.6572 0.0460
-8.250 -0.1056 0.04524 0.04076 -0.1247 0.6512 0.0586
-8.000 -0.0860 0.04393 0.03943 -0.1248 0.6479 0.0589
-7.750 -0.0683 0.04242 0.03790 -0.1249 0.6453 0.0592
-7.500 -0.1299 0.02207 0.01547 -0.1213 0.6450 0.0483
-7.250 -0.1042 0.02143 0.01477 -0.1212 0.6421 0.0488
-7.000 -0.0789 0.02068 0.01391 -0.1211 0.6389 0.0494
-6.750 -0.0535 0.01990 0.01298 -0.1208 0.6357 0.0501
-6.500 -0.0278 0.01918 0.01207 -0.1206 0.6326 0.0509
-6.250 -0.0013 0.01861 0.01129 -0.1205 0.6298 0.0517
-6.000 0.0258 0.01822 0.01073 -0.1204 0.6274 0.0523
-5.750 0.0522 0.01727 0.00981 -0.1205 0.6254 0.0533
-5.500 0.0798 0.01692 0.00946 -0.1205 0.6228 0.0542
-5.250 0.1075 0.01657 0.00908 -0.1206 0.6200 0.0552
-5.000 0.1353 0.01620 0.00865 -0.1206 0.6173 0.0562
-4.750 0.1632 0.01587 0.00824 -0.1206 0.6148 0.0572
-4.500 0.1914 0.01566 0.00792 -0.1207 0.6121 0.0581
-4.250 0.2187 0.01515 0.00737 -0.1207 0.6090 0.0593
-4.000 0.2463 0.01485 0.00713 -0.1208 0.6069 0.0606
-3.750 0.2742 0.01463 0.00692 -0.1209 0.6041 0.0620
-3.500 0.3022 0.01441 0.00667 -0.1209 0.6010 0.0635
-3.250 0.3304 0.01423 0.00645 -0.1209 0.5979 0.0647
-3.000 0.3574 0.01383 0.00606 -0.1209 0.5951 0.0664
-2.750 0.3855 0.01372 0.00592 -0.1210 0.5919 0.0681
-2.500 0.4138 0.01364 0.00583 -0.1212 0.5888 0.0702
-2.250 0.4416 0.01348 0.00567 -0.1212 0.5858 0.0722
-2.000 0.4688 0.01321 0.00545 -0.1211 0.5822 0.0747
-1.750 0.4967 0.01307 0.00532 -0.1212 0.5783 0.0773
-1.500 0.5248 0.01300 0.00520 -0.1212 0.5747 0.0800
-1.250 0.5527 0.01291 0.00510 -0.1214 0.5707 0.0840
-1.000 0.5802 0.01279 0.00503 -0.1213 0.5673 0.0883
-0.750 0.6074 0.01261 0.00490 -0.1213 0.5629 0.0937
-0.500 0.6348 0.01248 0.00477 -0.1213 0.5582 0.1011
-0.250 0.6620 0.01239 0.00466 -0.1213 0.5535 0.1113
0.000 0.6887 0.01220 0.00456 -0.1212 0.5483 0.1259
0.250 0.7151 0.01199 0.00447 -0.1211 0.5422 0.1517
0.500 0.7392 0.01146 0.00444 -0.1208 0.5365 0.3262
0.750 0.7627 0.01092 0.00450 -0.1204 0.5298 0.5169
1.000 0.7820 0.01031 0.00460 -0.1189 0.5220 0.7450
1.250 0.7998 0.01007 0.00476 -0.1162 0.5139 0.9035
1.500 0.8408 0.01021 0.00487 -0.1189 0.5021 0.9715
1.750 0.8908 0.01042 0.00497 -0.1238 0.4886 0.9944
2.000 0.9263 0.01064 0.00507 -0.1257 0.4768 1.0000
2.500 0.9587 0.01105 0.00529 -0.1216 0.4590 1.0000
2.750 0.9746 0.01131 0.00544 -0.1196 0.4515 1.0000
3.000 0.9938 0.01153 0.00560 -0.1181 0.4453 1.0000
3.250 1.0125 0.01178 0.00579 -0.1167 0.4392 1.0000
3.500 1.0291 0.01211 0.00601 -0.1148 0.4336 1.0000
3.750 1.0490 0.01231 0.00620 -0.1135 0.4292 1.0000
4.000 1.0684 0.01257 0.00642 -0.1122 0.4248 1.0000
4.250 1.0874 0.01289 0.00668 -0.1110 0.4206 1.0000
4.500 1.1067 0.01327 0.00698 -0.1098 0.4164 1.0000
4.750 1.1286 0.01352 0.00723 -0.1091 0.4134 1.0000
5.000 1.1504 0.01379 0.00751 -0.1084 0.4101 1.0000
5.250 1.1714 0.01411 0.00780 -0.1076 0.4067 1.0000
5.500 1.1918 0.01448 0.00813 -0.1067 0.4033 1.0000
5.750 1.2128 0.01491 0.00848 -0.1060 0.3995 1.0000
6.000 1.2344 0.01523 0.00882 -0.1054 0.3969 1.0000
6.250 1.2558 0.01555 0.00916 -0.1048 0.3943 1.0000
6.500 1.2770 0.01590 0.00952 -0.1042 0.3916 1.0000
6.750 1.2978 0.01628 0.00989 -0.1036 0.3889 1.0000
7.000 1.3184 0.01669 0.01028 -0.1029 0.3862 1.0000
7.250 1.3397 0.01713 0.01068 -0.1024 0.3833 1.0000
7.500 1.3618 0.01754 0.01107 -0.1020 0.3807 1.0000
7.750 1.3811 0.01796 0.01154 -0.1012 0.3786 1.0000
8.000 1.4006 0.01840 0.01201 -0.1005 0.3761 1.0000
8.250 1.4202 0.01885 0.01249 -0.0999 0.3735 1.0000
8.500 1.4396 0.01933 0.01298 -0.0992 0.3712 1.0000
8.750 1.4591 0.01982 0.01346 -0.0986 0.3689 1.0000
9.000 1.4800 0.02030 0.01391 -0.0981 0.3663 1.0000
9.250 1.5022 0.02074 0.01434 -0.0979 0.3638 1.0000
9.500 1.5191 0.02132 0.01500 -0.0970 0.3621 1.0000
9.750 1.5361 0.02191 0.01564 -0.0962 0.3599 1.0000
10.000 1.5527 0.02253 0.01630 -0.0954 0.3573 1.0000
10.250 1.5682 0.02321 0.01700 -0.0945 0.3544 1.0000
10.500 1.5840 0.02389 0.01769 -0.0936 0.3513 1.0000
10.750 1.6042 0.02443 0.01816 -0.0932 0.3475 1.0000
11.000 1.6149 0.02538 0.01921 -0.0919 0.3452 1.0000
11.250 1.6273 0.02628 0.02019 -0.0909 0.3423 1.0000
11.500 1.6406 0.02716 0.02112 -0.0900 0.3394 1.0000
11.750 1.6540 0.02806 0.02205 -0.0891 0.3367 1.0000
12.000 1.6683 0.02892 0.02290 -0.0883 0.3339 1.0000
12.250 1.6856 0.02960 0.02357 -0.0878 0.3308 1.0000
12.500 1.6954 0.03081 0.02489 -0.0868 0.3286 1.0000
12.750 1.7064 0.03199 0.02615 -0.0860 0.3258 1.0000
13.000 1.7162 0.03328 0.02750 -0.0851 0.3226 1.0000
13.250 1.7264 0.03455 0.02880 -0.0843 0.3192 1.0000
13.500 1.7385 0.03564 0.02985 -0.0836 0.3154 1.0000
13.750 1.7463 0.03723 0.03155 -0.0828 0.3126 1.0000
14.000 1.7541 0.03885 0.03326 -0.0821 0.3093 1.0000
14.250 1.7618 0.04051 0.03498 -0.0815 0.3058 1.0000
14.500 1.7696 0.04212 0.03660 -0.0808 0.3022 1.0000
14.750 1.7781 0.04366 0.03814 -0.0802 0.2987 1.0000
15.000 1.7840 0.04561 0.04022 -0.0797 0.2955 1.0000
15.250 1.7899 0.04755 0.04225 -0.0791 0.2917 1.0000
15.500 1.7937 0.04966 0.04438 -0.0785 0.2876 1.0000
15.750 1.7972 0.05176 0.04648 -0.0779 0.2832 1.0000
16.000 1.7998 0.05414 0.04899 -0.0774 0.2787 1.0000
16.250 1.8013 0.05657 0.05146 -0.0769 0.2740 1.0000
16.500 1.8010 0.05909 0.05397 -0.0762 0.2693 1.0000
16.750 1.8027 0.06157 0.05657 -0.0758 0.2648 1.0000
17.000 1.8027 0.06419 0.05925 -0.0754 0.2597 1.0000
17.250 1.7983 0.06724 0.06230 -0.0748 0.2547 1.0000
17.500 1.7982 0.06995 0.06511 -0.0744 0.2494 1.0000
17.750 1.7912 0.07342 0.06861 -0.0739 0.2432 1.0000
18.000 1.7857 0.07672 0.07196 -0.0735 0.2373 1.0000
18.250 1.7777 0.08039 0.07569 -0.0732 0.2305 1.0000
18.500 1.7661 0.08449 0.07981 -0.0728 0.2239 1.0000
18.750 1.7554 0.08856 0.08394 -0.0726 0.2162 1.0000
19.000 1.7409 0.09310 0.08850 -0.0725 0.2089 1.0000
19.250 1.7231 0.09813 0.09356 -0.0725 0.2007 1.0000
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