GOE 288 AIRFOIL (goe288-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 288 AIRFOIL (goe288-il) Reynolds number: 200,000 Max Cl/Cd: 69.44 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe288-il-200000-n5.txt Download as CSV file: xf-goe288-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 288 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
------ -------- --------- --------- -------- -------- --------
-13.000 -0.5216 0.07535 0.07082 -0.0763 1.0000 0.0388
-12.750 -0.5858 0.06366 0.05889 -0.0840 1.0000 0.0386
-12.500 -0.6240 0.05737 0.05249 -0.0869 0.9997 0.0386
-12.250 -0.6354 0.04926 0.04408 -0.0982 0.9874 0.0387
-12.000 -0.6363 0.04296 0.03747 -0.1083 0.9713 0.0388
-11.750 -0.6243 0.03835 0.03253 -0.1166 0.9567 0.0390
-11.500 -0.6066 0.03579 0.02977 -0.1199 0.9451 0.0392
-11.250 -0.5833 0.03392 0.02782 -0.1220 0.9356 0.0395
-11.000 -0.5614 0.03231 0.02611 -0.1234 0.9234 0.0399
-10.750 -0.5390 0.03085 0.02454 -0.1245 0.9107 0.0402
-10.500 -0.5156 0.02949 0.02307 -0.1255 0.8977 0.0406
-10.250 -0.4920 0.02824 0.02168 -0.1262 0.8839 0.0410
-10.000 -0.4694 0.02711 0.02042 -0.1265 0.8683 0.0415
-9.750 -0.4462 0.02606 0.01922 -0.1268 0.8529 0.0420
-9.500 -0.4225 0.02509 0.01810 -0.1269 0.8371 0.0426
-9.250 -0.3983 0.02421 0.01704 -0.1270 0.8210 0.0433
-9.000 -0.3738 0.02342 0.01604 -0.1270 0.8043 0.0440
-8.750 -0.3495 0.02262 0.01514 -0.1269 0.7872 0.0446
-8.500 -0.3248 0.02191 0.01434 -0.1269 0.7706 0.0453
-8.250 -0.2995 0.02127 0.01358 -0.1269 0.7543 0.0460
-8.000 -0.2737 0.02067 0.01286 -0.1269 0.7395 0.0468
-7.750 -0.2475 0.02011 0.01217 -0.1270 0.7262 0.0476
-7.250 -0.1940 0.01912 0.01089 -0.1271 0.7026 0.0497
-7.000 -0.1671 0.01859 0.01028 -0.1273 0.6925 0.0509
-6.750 -0.1397 0.01814 0.00974 -0.1276 0.6823 0.0525
-6.500 -0.1120 0.01777 0.00924 -0.1277 0.6735 0.0546
-6.250 -0.0840 0.01735 0.00876 -0.1280 0.6648 0.0571
-6.000 -0.0560 0.01699 0.00830 -0.1282 0.6576 0.0605
-5.750 -0.0274 0.01661 0.00789 -0.1285 0.6508 0.0650
-5.500 0.0011 0.01627 0.00753 -0.1288 0.6443 0.0721
-5.250 0.0297 0.01599 0.00721 -0.1290 0.6387 0.0837
-5.000 0.0586 0.01575 0.00697 -0.1293 0.6329 0.0979
-4.750 0.0875 0.01555 0.00676 -0.1296 0.6269 0.1114
-4.500 0.1162 0.01541 0.00655 -0.1298 0.6209 0.1236
-4.250 0.1452 0.01528 0.00637 -0.1299 0.6149 0.1347
-4.000 0.1741 0.01511 0.00620 -0.1302 0.6084 0.1455
-3.750 0.2028 0.01500 0.00603 -0.1303 0.6023 0.1560
-3.500 0.2317 0.01488 0.00588 -0.1305 0.5965 0.1687
-3.250 0.2605 0.01469 0.00577 -0.1308 0.5899 0.1897
-3.000 0.2891 0.01455 0.00569 -0.1310 0.5838 0.2182
-2.750 0.3179 0.01449 0.00566 -0.1312 0.5783 0.2459
-2.500 0.3469 0.01445 0.00566 -0.1313 0.5722 0.2683
-2.250 0.3758 0.01447 0.00565 -0.1314 0.5670 0.2859
-2.000 0.4046 0.01452 0.00565 -0.1315 0.5624 0.3009
-1.750 0.4336 0.01456 0.00568 -0.1316 0.5577 0.3141
-1.500 0.4626 0.01460 0.00570 -0.1317 0.5526 0.3259
-1.250 0.4914 0.01466 0.00571 -0.1318 0.5480 0.3367
-1.000 0.5201 0.01473 0.00572 -0.1318 0.5437 0.3455
-0.750 0.5488 0.01480 0.00575 -0.1319 0.5390 0.3551
-0.500 0.5774 0.01483 0.00580 -0.1319 0.5335 0.3633
-0.250 0.6058 0.01490 0.00582 -0.1319 0.5282 0.3716
0.000 0.6341 0.01499 0.00582 -0.1319 0.5235 0.3795
0.250 0.6625 0.01502 0.00591 -0.1319 0.5182 0.3876
0.500 0.6908 0.01510 0.00596 -0.1319 0.5127 0.3978
0.750 0.7186 0.01517 0.00603 -0.1319 0.5075 0.4083
1.000 0.7466 0.01524 0.00609 -0.1318 0.5021 0.4171
1.250 0.7743 0.01527 0.00616 -0.1318 0.4956 0.4235
1.500 0.8018 0.01534 0.00619 -0.1316 0.4892 0.4301
1.750 0.8293 0.01541 0.00625 -0.1315 0.4827 0.4360
2.000 0.8565 0.01546 0.00634 -0.1314 0.4754 0.4424
2.250 0.8833 0.01556 0.00640 -0.1312 0.4689 0.4498
2.500 0.9105 0.01563 0.00652 -0.1311 0.4611 0.4568
2.750 0.9368 0.01572 0.00662 -0.1308 0.4533 0.4640
3.000 0.9634 0.01584 0.00674 -0.1305 0.4447 0.4728
3.250 0.9889 0.01595 0.00687 -0.1301 0.4355 0.4822
3.500 1.0146 0.01608 0.00702 -0.1298 0.4254 0.4931
3.750 1.0392 0.01624 0.00718 -0.1292 0.4153 0.5049
4.000 1.0639 0.01640 0.00737 -0.1287 0.4046 0.5193
4.250 1.0880 0.01659 0.00759 -0.1281 0.3951 0.5387
4.500 1.1113 0.01679 0.00783 -0.1274 0.3859 0.5656
4.750 1.1344 0.01696 0.00811 -0.1266 0.3777 0.6062
5.000 1.1559 0.01705 0.00840 -0.1255 0.3702 0.6933
5.250 1.1729 0.01689 0.00858 -0.1231 0.3640 1.0000
5.500 1.1959 0.01726 0.00890 -0.1224 0.3575 1.0000
5.750 1.2174 0.01768 0.00924 -0.1215 0.3517 1.0000
6.000 1.2397 0.01807 0.00959 -0.1207 0.3466 1.0000
6.250 1.2617 0.01846 0.00997 -0.1198 0.3417 1.0000
6.500 1.2827 0.01890 0.01036 -0.1188 0.3375 1.0000
6.750 1.3028 0.01938 0.01078 -0.1177 0.3339 1.0000
7.000 1.3239 0.01979 0.01120 -0.1168 0.3306 1.0000
7.250 1.3442 0.02020 0.01164 -0.1157 0.3273 1.0000
7.500 1.3631 0.02065 0.01209 -0.1143 0.3242 1.0000
7.750 1.3817 0.02114 0.01258 -0.1130 0.3212 1.0000
8.000 1.3999 0.02168 0.01309 -0.1117 0.3184 1.0000
8.250 1.4184 0.02227 0.01363 -0.1105 0.3156 1.0000
8.500 1.4375 0.02276 0.01419 -0.1093 0.3131 1.0000
8.750 1.4562 0.02329 0.01478 -0.1082 0.3104 1.0000
9.000 1.4745 0.02385 0.01539 -0.1071 0.3080 1.0000
9.250 1.4926 0.02445 0.01602 -0.1059 0.3057 1.0000
9.500 1.5104 0.02508 0.01667 -0.1048 0.3035 1.0000
9.750 1.5283 0.02572 0.01733 -0.1037 0.3014 1.0000
10.000 1.5471 0.02638 0.01797 -0.1027 0.2995 1.0000
10.250 1.5658 0.02704 0.01866 -0.1018 0.2977 1.0000
10.500 1.5816 0.02776 0.01950 -0.1006 0.2957 1.0000
10.750 1.5963 0.02854 0.02038 -0.0993 0.2933 1.0000
11.000 1.6104 0.02937 0.02129 -0.0980 0.2907 1.0000
11.250 1.6241 0.03023 0.02222 -0.0967 0.2881 1.0000
11.500 1.6379 0.03111 0.02315 -0.0955 0.2855 1.0000
11.750 1.6530 0.03197 0.02401 -0.0944 0.2832 1.0000
12.000 1.6696 0.03280 0.02483 -0.0935 0.2809 1.0000
12.250 1.6800 0.03392 0.02612 -0.0921 0.2789 1.0000
12.500 1.6911 0.03506 0.02738 -0.0909 0.2769 1.0000
12.750 1.7023 0.03621 0.02866 -0.0898 0.2750 1.0000
13.000 1.7130 0.03743 0.02998 -0.0887 0.2729 1.0000
13.250 1.7223 0.03873 0.03138 -0.0875 0.2706 1.0000
13.500 1.7315 0.04004 0.03274 -0.0864 0.2679 1.0000
13.750 1.7438 0.04113 0.03381 -0.0855 0.2650 1.0000
14.000 1.7465 0.04303 0.03588 -0.0843 0.2622 1.0000
14.250 1.7484 0.04509 0.03811 -0.0832 0.2593 1.0000
14.500 1.7505 0.04716 0.04032 -0.0823 0.2561 1.0000
14.750 1.7532 0.04923 0.04248 -0.0815 0.2529 1.0000
15.000 1.7591 0.05098 0.04424 -0.0807 0.2495 1.0000
15.250 1.7580 0.05362 0.04702 -0.0801 0.2460 1.0000
15.500 1.7534 0.05675 0.05033 -0.0796 0.2420 1.0000
15.750 1.7510 0.05969 0.05339 -0.0793 0.2380 1.0000
16.000 1.7520 0.06222 0.05595 -0.0790 0.2340 1.0000
16.250 1.7453 0.06587 0.05977 -0.0789 0.2296 1.0000
16.500 1.7360 0.06993 0.06399 -0.0790 0.2244 1.0000
16.750 1.7305 0.07348 0.06757 -0.0791 0.2190 1.0000
17.000 1.7170 0.07829 0.07255 -0.0795 0.2132 1.0000
17.250 1.7046 0.08299 0.07737 -0.0800 0.2070 1.0000
17.500 1.6922 0.08777 0.08225 -0.0806 0.2011 1.0000
17.750 1.6751 0.09331 0.08793 -0.0814 0.1946 1.0000
18.000 1.6589 0.09877 0.09349 -0.0824 0.1881 1.0000
18.250 1.6371 0.10522 0.10007 -0.0838 0.1809 1.0000
18.500 1.6146 0.11184 0.10679 -0.0854 0.1733 1.0000
18.750 1.5901 0.11890 0.11392 -0.0874 0.1643 1.0000
19.000 1.5610 0.12690 0.12201 -0.0900 0.1540 1.0000
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Polar graphs
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