GOE 384 AIRFOIL (goe384-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 384 AIRFOIL (goe384-il) Reynolds number: 500,000 Max Cl/Cd: 78.37 at α=3.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe384-il-500000-n5.txt Download as CSV file: xf-goe384-il-500000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.750 -0.5833 0.04359 0.03948 -0.1207 0.7659 0.0326
-13.500 -0.6191 0.03564 0.03107 -0.1287 0.7505 0.0327
-13.250 -0.6301 0.03256 0.02767 -0.1288 0.7308 0.0329
-13.000 -0.6338 0.03065 0.02544 -0.1272 0.7090 0.0330
-12.750 -0.6247 0.02930 0.02389 -0.1263 0.6897 0.0332
-12.500 -0.6106 0.02830 0.02273 -0.1255 0.6755 0.0334
-12.250 -0.5938 0.02747 0.02176 -0.1249 0.6647 0.0336
-12.000 -0.5753 0.02671 0.02089 -0.1243 0.6569 0.0338
-11.750 -0.5559 0.02600 0.02006 -0.1238 0.6504 0.0340
-11.500 -0.5356 0.02530 0.01925 -0.1233 0.6457 0.0342
-11.250 -0.5146 0.02458 0.01844 -0.1228 0.6418 0.0345
-11.000 -0.4930 0.02390 0.01765 -0.1224 0.6382 0.0348
-10.750 -0.4708 0.02325 0.01688 -0.1220 0.6348 0.0351
-10.500 -0.4483 0.02260 0.01610 -0.1216 0.6318 0.0355
-10.000 -0.4024 0.02123 0.01444 -0.1209 0.6269 0.0364
-9.750 -0.3787 0.02054 0.01362 -0.1205 0.6245 0.0367
-9.500 -0.3543 0.01993 0.01287 -0.1202 0.6217 0.0371
-9.250 -0.3298 0.01935 0.01220 -0.1200 0.6186 0.0374
-9.000 -0.3046 0.01890 0.01170 -0.1197 0.6156 0.0377
-8.750 -0.2788 0.01854 0.01128 -0.1195 0.6126 0.0380
-8.250 -0.2263 0.01787 0.01049 -0.1193 0.6072 0.0388
-8.000 -0.1996 0.01751 0.01009 -0.1192 0.6052 0.0392
-7.750 -0.1728 0.01716 0.00968 -0.1191 0.6031 0.0397
-7.500 -0.1459 0.01681 0.00927 -0.1190 0.6011 0.0403
-7.250 -0.1188 0.01650 0.00888 -0.1190 0.5987 0.0409
-7.000 -0.0917 0.01621 0.00849 -0.1189 0.5962 0.0415
-6.750 -0.0649 0.01589 0.00811 -0.1188 0.5936 0.0420
-6.500 -0.0380 0.01562 0.00781 -0.1187 0.5908 0.0425
-6.250 -0.0105 0.01538 0.00755 -0.1187 0.5885 0.0431
-6.000 0.0173 0.01514 0.00729 -0.1187 0.5865 0.0437
-5.750 0.0451 0.01490 0.00704 -0.1188 0.5844 0.0443
-5.500 0.0729 0.01467 0.00678 -0.1188 0.5821 0.0451
-5.250 0.1007 0.01445 0.00652 -0.1188 0.5796 0.0458
-5.000 0.1286 0.01427 0.00628 -0.1189 0.5770 0.0465
-4.750 0.1560 0.01404 0.00603 -0.1189 0.5746 0.0474
-4.500 0.1837 0.01388 0.00585 -0.1189 0.5723 0.0482
-4.250 0.2117 0.01374 0.00570 -0.1190 0.5702 0.0492
-4.000 0.2399 0.01356 0.00552 -0.1191 0.5681 0.0501
-3.750 0.2681 0.01339 0.00535 -0.1192 0.5654 0.0511
-3.500 0.2962 0.01325 0.00518 -0.1193 0.5622 0.0520
-3.250 0.3239 0.01307 0.00500 -0.1193 0.5589 0.0531
-3.000 0.3516 0.01294 0.00486 -0.1193 0.5558 0.0543
-2.750 0.3793 0.01286 0.00474 -0.1194 0.5528 0.0558
-2.500 0.4077 0.01274 0.00464 -0.1195 0.5499 0.0572
-2.250 0.4359 0.01262 0.00453 -0.1196 0.5462 0.0585
-2.000 0.4636 0.01250 0.00441 -0.1197 0.5419 0.0602
-1.750 0.4910 0.01243 0.00432 -0.1197 0.5372 0.0621
-1.500 0.5188 0.01236 0.00425 -0.1197 0.5326 0.0644
-1.250 0.5465 0.01227 0.00418 -0.1198 0.5267 0.0670
-1.000 0.5736 0.01223 0.00413 -0.1197 0.5205 0.0701
-0.750 0.6009 0.01219 0.00410 -0.1197 0.5140 0.0740
-0.500 0.6276 0.01217 0.00408 -0.1196 0.5048 0.0799
-0.250 0.6536 0.01218 0.00408 -0.1194 0.4939 0.0875
0.000 0.6784 0.01223 0.00409 -0.1190 0.4809 0.0950
0.250 0.7022 0.01234 0.00413 -0.1184 0.4674 0.1019
0.500 0.7258 0.01247 0.00419 -0.1178 0.4554 0.1093
0.750 0.7497 0.01257 0.00427 -0.1172 0.4461 0.1184
1.000 0.7728 0.01270 0.00438 -0.1166 0.4376 0.1308
1.250 0.7962 0.01261 0.00451 -0.1161 0.4310 0.2111
1.500 0.8191 0.01254 0.00467 -0.1156 0.4245 0.3092
1.750 0.8407 0.01254 0.00487 -0.1148 0.4186 0.4025
2.000 0.8640 0.01236 0.00505 -0.1144 0.4139 0.5312
2.250 0.8839 0.01204 0.00530 -0.1132 0.4095 0.7258
2.500 0.8969 0.01189 0.00560 -0.1100 0.4056 0.8860
2.750 0.9393 0.01216 0.00589 -0.1132 0.4012 0.9968
3.000 0.9609 0.01234 0.00604 -0.1123 0.3983 1.0000
3.250 0.9813 0.01254 0.00622 -0.1112 0.3952 1.0000
3.500 1.0016 0.01278 0.00642 -0.1101 0.3919 1.0000
3.750 1.0215 0.01307 0.00667 -0.1090 0.3885 1.0000
4.000 1.0410 0.01340 0.00694 -0.1079 0.3851 1.0000
4.250 1.0617 0.01371 0.00722 -0.1070 0.3823 1.0000
4.500 1.0845 0.01396 0.00746 -0.1065 0.3800 1.0000
4.750 1.1067 0.01423 0.00773 -0.1059 0.3776 1.0000
5.000 1.1284 0.01454 0.00803 -0.1053 0.3750 1.0000
5.250 1.1496 0.01488 0.00835 -0.1046 0.3724 1.0000
5.500 1.1699 0.01527 0.00871 -0.1039 0.3698 1.0000
5.750 1.1895 0.01570 0.00911 -0.1030 0.3671 1.0000
6.000 1.2096 0.01612 0.00952 -0.1023 0.3646 1.0000
6.250 1.2316 0.01646 0.00987 -0.1019 0.3625 1.0000
6.500 1.2530 0.01683 0.01025 -0.1014 0.3602 1.0000
6.750 1.2738 0.01724 0.01067 -0.1008 0.3579 1.0000
7.000 1.2937 0.01769 0.01113 -0.1002 0.3556 1.0000
7.250 1.3131 0.01818 0.01161 -0.0995 0.3534 1.0000
7.500 1.3317 0.01873 0.01215 -0.0988 0.3511 1.0000
7.750 1.3493 0.01933 0.01274 -0.0979 0.3489 1.0000
8.000 1.3684 0.01986 0.01328 -0.0973 0.3469 1.0000
8.250 1.3886 0.02034 0.01381 -0.0968 0.3450 1.0000
8.500 1.4077 0.02088 0.01438 -0.0963 0.3427 1.0000
8.750 1.4264 0.02146 0.01498 -0.0957 0.3405 1.0000
9.000 1.4441 0.02209 0.01564 -0.0950 0.3383 1.0000
9.250 1.4609 0.02279 0.01635 -0.0943 0.3362 1.0000
9.500 1.4772 0.02352 0.01708 -0.0935 0.3341 1.0000
9.750 1.4921 0.02435 0.01792 -0.0926 0.3320 1.0000
10.000 1.5084 0.02510 0.01870 -0.0919 0.3302 1.0000
10.250 1.5261 0.02578 0.01944 -0.0914 0.3280 1.0000
10.500 1.5414 0.02663 0.02033 -0.0907 0.3247 1.0000
10.750 1.5551 0.02760 0.02132 -0.0899 0.3208 1.0000
11.000 1.5664 0.02876 0.02249 -0.0889 0.3173 1.0000
11.250 1.5778 0.02993 0.02366 -0.0880 0.3141 1.0000
11.500 1.5929 0.03090 0.02469 -0.0875 0.3111 1.0000
11.750 1.6060 0.03202 0.02587 -0.0869 0.3071 1.0000
12.000 1.6163 0.03338 0.02724 -0.0861 0.3033 1.0000
12.250 1.6252 0.03485 0.02873 -0.0852 0.2999 1.0000
12.500 1.6368 0.03615 0.03006 -0.0846 0.2972 1.0000
12.750 1.6501 0.03733 0.03132 -0.0841 0.2945 1.0000
13.000 1.6609 0.03874 0.03278 -0.0835 0.2912 1.0000
13.250 1.6689 0.04040 0.03447 -0.0828 0.2874 1.0000
13.500 1.6745 0.04229 0.03636 -0.0820 0.2836 1.0000
13.750 1.6844 0.04384 0.03799 -0.0816 0.2798 1.0000
14.000 1.6919 0.04563 0.03983 -0.0810 0.2750 1.0000
14.250 1.6938 0.04796 0.04216 -0.0802 0.2697 1.0000
14.500 1.6996 0.04992 0.04417 -0.0796 0.2652 1.0000
14.750 1.7050 0.05193 0.04622 -0.0791 0.2600 1.0000
15.000 1.7047 0.05450 0.04882 -0.0783 0.2549 1.0000
15.250 1.7095 0.05658 0.05094 -0.0778 0.2503 1.0000
15.500 1.7112 0.05901 0.05341 -0.0772 0.2447 1.0000
15.750 1.7078 0.06195 0.05637 -0.0764 0.2389 1.0000
16.000 1.7080 0.06457 0.05904 -0.0759 0.2321 1.0000
16.250 1.7004 0.06804 0.06251 -0.0751 0.2248 1.0000
16.500 1.6959 0.07124 0.06575 -0.0746 0.2167 1.0000
16.750 1.6858 0.07511 0.06963 -0.0740 0.2089 1.0000
17.000 1.6751 0.07907 0.07360 -0.0734 0.1998 1.0000
17.250 1.6618 0.08343 0.07798 -0.0729 0.1913 1.0000
17.500 1.6454 0.08824 0.08282 -0.0726 0.1834 1.0000
17.750 1.6308 0.09291 0.08751 -0.0724 0.1755 1.0000
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