GOE 630 AIRFOIL (goe630-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 630 AIRFOIL (goe630-il) Reynolds number: 200,000 Max Cl/Cd: 73.5 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe630-il-200000-n5.txt Download as CSV file: xf-goe630-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 630 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
------ -------- --------- --------- -------- -------- --------
-9.750 0.0937 0.09260 0.08848 -0.1122 0.8682 0.0382
-9.500 0.0988 0.09012 0.08594 -0.1154 0.8550 0.0387
-9.250 0.1018 0.08780 0.08355 -0.1180 0.8429 0.0389
-9.000 0.1145 0.08467 0.08038 -0.1182 0.8330 0.0393
-8.750 0.1303 0.08230 0.07795 -0.1179 0.8241 0.0401
-8.500 0.1397 0.08020 0.07580 -0.1183 0.8142 0.0408
-8.250 0.1469 0.07815 0.07371 -0.1187 0.8045 0.0417
-8.000 0.1535 0.07604 0.07155 -0.1192 0.7957 0.0425
-7.750 0.1550 0.07401 0.06951 -0.1199 0.7862 0.0442
-7.500 0.1492 0.07213 0.06760 -0.1211 0.7777 0.0449
-7.250 0.1461 0.07014 0.06562 -0.1226 0.7691 0.0451
-7.000 0.1502 0.06723 0.06265 -0.1268 0.7621 0.0453
-6.750 0.1614 0.06479 0.06022 -0.1248 0.7557 0.0458
-6.500 0.1743 0.06295 0.05835 -0.1236 0.7492 0.0464
-6.250 0.1862 0.06089 0.05624 -0.1242 0.7433 0.0471
-6.000 0.1973 0.05866 0.05400 -0.1255 0.7365 0.0477
-5.750 0.2104 0.05627 0.05155 -0.1274 0.7301 0.0483
-5.500 0.2250 0.05377 0.04899 -0.1296 0.7241 0.0490
-5.250 0.2498 0.04937 0.04439 -0.1385 0.7173 0.0526
-5.000 0.2630 0.04528 0.04019 -0.1391 0.7119 0.0447
-4.750 0.2799 0.04339 0.03826 -0.1392 0.7057 0.0436
-4.250 0.3251 0.03115 0.02521 -0.1470 0.6946 0.0393
-4.000 0.3470 0.03060 0.02465 -0.1467 0.6878 0.0399
-3.750 0.3697 0.02921 0.02311 -0.1468 0.6810 0.0407
-3.500 0.3932 0.02671 0.02029 -0.1471 0.6751 0.0413
-3.250 0.4155 0.02387 0.01703 -0.1470 0.6681 0.0412
-3.000 0.4392 0.02197 0.01474 -0.1466 0.6617 0.0415
-2.750 0.4630 0.02056 0.01301 -0.1461 0.6547 0.0420
-2.500 0.4873 0.01943 0.01157 -0.1455 0.6472 0.0426
-2.250 0.5123 0.01859 0.01042 -0.1448 0.6402 0.0440
-2.000 0.5371 0.01788 0.00942 -0.1441 0.6319 0.0450
-1.750 0.5621 0.01722 0.00856 -0.1435 0.6242 0.0456
-1.500 0.5866 0.01671 0.00797 -0.1428 0.6155 0.0464
-1.250 0.6115 0.01633 0.00749 -0.1422 0.6074 0.0472
-1.000 0.6361 0.01599 0.00706 -0.1415 0.5980 0.0483
-0.750 0.6607 0.01570 0.00668 -0.1407 0.5888 0.0496
-0.500 0.6851 0.01550 0.00636 -0.1400 0.5793 0.0517
-0.250 0.7092 0.01527 0.00606 -0.1392 0.5694 0.0535
0.000 0.7330 0.01506 0.00582 -0.1383 0.5604 0.0552
0.250 0.7567 0.01492 0.00565 -0.1375 0.5504 0.0572
0.500 0.7801 0.01484 0.00550 -0.1366 0.5408 0.0597
0.750 0.8032 0.01478 0.00537 -0.1356 0.5309 0.0628
1.000 0.8263 0.01475 0.00533 -0.1347 0.5213 0.0674
1.250 0.8492 0.01479 0.00527 -0.1337 0.5123 0.0722
1.500 0.8722 0.01478 0.00529 -0.1328 0.5034 0.0796
1.750 0.8947 0.01483 0.00531 -0.1318 0.4954 0.0926
2.000 0.9173 0.01483 0.00539 -0.1308 0.4870 0.1242
2.250 0.9385 0.01479 0.00554 -0.1297 0.4794 0.2199
2.500 0.9593 0.01448 0.00577 -0.1287 0.4714 0.4524
3.000 1.0340 0.01419 0.00615 -0.1331 0.4551 1.0000
3.250 1.0556 0.01447 0.00630 -0.1320 0.4488 1.0000
3.500 1.0779 0.01471 0.00649 -0.1310 0.4428 1.0000
3.750 1.0996 0.01498 0.00668 -0.1299 0.4367 1.0000
4.000 1.1206 0.01528 0.00688 -0.1288 0.4314 1.0000
4.250 1.1422 0.01554 0.00710 -0.1277 0.4256 1.0000
4.500 1.1631 0.01583 0.00734 -0.1266 0.4201 1.0000
4.750 1.1832 0.01615 0.00758 -0.1253 0.4151 1.0000
5.000 1.2038 0.01643 0.00785 -0.1241 0.4102 1.0000
5.250 1.2235 0.01672 0.00813 -0.1228 0.4055 1.0000
5.500 1.2427 0.01705 0.00841 -0.1213 0.4013 1.0000
5.750 1.2620 0.01740 0.00871 -0.1200 0.3976 1.0000
6.000 1.2817 0.01771 0.00905 -0.1187 0.3936 1.0000
6.250 1.3008 0.01804 0.00939 -0.1173 0.3894 1.0000
6.500 1.3194 0.01841 0.00974 -0.1159 0.3855 1.0000
6.750 1.3384 0.01881 0.01010 -0.1146 0.3820 1.0000
7.000 1.3571 0.01916 0.01050 -0.1133 0.3782 1.0000
7.250 1.3759 0.01954 0.01092 -0.1121 0.3746 1.0000
7.500 1.3945 0.01995 0.01134 -0.1108 0.3714 1.0000
7.750 1.4131 0.02037 0.01177 -0.1096 0.3683 1.0000
8.000 1.4328 0.02082 0.01219 -0.1086 0.3656 1.0000
8.250 1.4508 0.02125 0.01270 -0.1073 0.3626 1.0000
8.500 1.4683 0.02171 0.01324 -0.1060 0.3594 1.0000
8.750 1.4853 0.02219 0.01377 -0.1047 0.3560 1.0000
9.000 1.5027 0.02269 0.01429 -0.1035 0.3531 1.0000
9.250 1.5215 0.02319 0.01479 -0.1025 0.3506 1.0000
9.500 1.5399 0.02371 0.01537 -0.1014 0.3481 1.0000
9.750 1.5554 0.02428 0.01606 -0.1000 0.3452 1.0000
10.000 1.5706 0.02488 0.01675 -0.0987 0.3421 1.0000
10.250 1.5862 0.02548 0.01743 -0.0974 0.3392 1.0000
10.500 1.6025 0.02608 0.01808 -0.0962 0.3366 1.0000
10.750 1.6199 0.02667 0.01866 -0.0952 0.3334 1.0000
11.000 1.6288 0.02751 0.01965 -0.0932 0.3293 1.0000
11.250 1.6372 0.02839 0.02065 -0.0913 0.3245 1.0000
11.500 1.6468 0.02925 0.02152 -0.0896 0.3196 1.0000
11.750 1.6554 0.03022 0.02258 -0.0878 0.3148 1.0000
12.000 1.6614 0.03137 0.02387 -0.0860 0.3095 1.0000
12.250 1.6680 0.03250 0.02504 -0.0843 0.3041 1.0000
12.500 1.6744 0.03374 0.02636 -0.0826 0.2989 1.0000
12.750 1.6795 0.03513 0.02789 -0.0811 0.2934 1.0000
13.000 1.6834 0.03659 0.02939 -0.0794 0.2874 1.0000
13.250 1.6867 0.03823 0.03117 -0.0780 0.2812 1.0000
13.500 1.6885 0.04003 0.03305 -0.0765 0.2745 1.0000
13.750 1.6897 0.04198 0.03508 -0.0752 0.2675 1.0000
14.000 1.6891 0.04417 0.03737 -0.0739 0.2596 1.0000
14.250 1.6871 0.04660 0.03989 -0.0727 0.2506 1.0000
14.500 1.6818 0.04943 0.04278 -0.0716 0.2403 1.0000
14.750 1.6765 0.05242 0.04584 -0.0707 0.2294 1.0000
15.000 1.6694 0.05574 0.04921 -0.0698 0.2171 1.0000
15.250 1.6560 0.05984 0.05333 -0.0691 0.2021 1.0000
15.500 1.6380 0.06470 0.05816 -0.0686 0.1860 1.0000
15.750 1.6145 0.07043 0.06387 -0.0684 0.1686 1.0000
16.000 1.5926 0.07621 0.06964 -0.0685 0.1547 1.0000
16.250 1.5707 0.08220 0.07565 -0.0689 0.1416 1.0000
16.500 1.5470 0.08863 0.08209 -0.0696 0.1275 1.0000
16.750 1.5230 0.09528 0.08875 -0.0706 0.1137 1.0000
17.000 1.4989 0.10213 0.09560 -0.0719 0.1004 1.0000
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