GOE 449 AIRFOIL (goe449-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 449 AIRFOIL (goe449-il) Reynolds number: 200,000 Max Cl/Cd: 65.61 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe449-il-200000-n5.txt Download as CSV file: xf-goe449-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 449 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
------ -------- --------- --------- -------- -------- --------
-12.250 -0.4044 0.04042 0.03520 -0.1575 0.9244 0.0394
-12.000 -0.4203 0.03692 0.03137 -0.1579 0.9126 0.0396
-11.750 -0.4253 0.03421 0.02831 -0.1574 0.9044 0.0400
-11.500 -0.4329 0.03242 0.02624 -0.1541 0.8944 0.0403
-11.250 -0.4300 0.03067 0.02413 -0.1522 0.8879 0.0408
-11.000 -0.4231 0.02970 0.02308 -0.1498 0.8803 0.0412
-10.750 -0.4062 0.02885 0.02217 -0.1489 0.8754 0.0417
-10.500 -0.3872 0.02798 0.02119 -0.1484 0.8714 0.0423
-10.250 -0.3781 0.02730 0.02042 -0.1458 0.8646 0.0428
-10.000 -0.3628 0.02646 0.01943 -0.1444 0.8594 0.0435
-9.750 -0.3432 0.02545 0.01824 -0.1437 0.8555 0.0442
-9.500 -0.3290 0.02465 0.01727 -0.1418 0.8502 0.0448
-9.250 -0.3136 0.02385 0.01630 -0.1400 0.8445 0.0456
-9.000 -0.2930 0.02300 0.01526 -0.1391 0.8397 0.0463
-8.750 -0.2704 0.02234 0.01455 -0.1385 0.8351 0.0471
-8.500 -0.2546 0.02189 0.01407 -0.1365 0.8280 0.0479
-8.250 -0.2327 0.02137 0.01346 -0.1356 0.8226 0.0489
-8.000 -0.2067 0.02076 0.01272 -0.1355 0.8186 0.0503
-7.750 -0.1906 0.02032 0.01218 -0.1334 0.8125 0.0516
-7.500 -0.1700 0.01984 0.01165 -0.1323 0.8078 0.0529
-7.250 -0.1464 0.01941 0.01118 -0.1316 0.8039 0.0542
-7.000 -0.1201 0.01895 0.01064 -0.1315 0.8007 0.0560
-6.750 -0.1027 0.01862 0.01026 -0.1296 0.7952 0.0578
-6.500 -0.0816 0.01825 0.00985 -0.1284 0.7905 0.0598
-6.250 -0.0574 0.01793 0.00950 -0.1278 0.7867 0.0621
-6.000 -0.0302 0.01758 0.00905 -0.1277 0.7835 0.0655
-5.750 -0.0112 0.01733 0.00882 -0.1261 0.7784 0.0683
-5.500 0.0103 0.01709 0.00856 -0.1249 0.7733 0.0718
-5.250 0.0348 0.01679 0.00820 -0.1243 0.7690 0.0756
-5.000 0.0624 0.01651 0.00788 -0.1243 0.7655 0.0800
-4.750 0.0823 0.01637 0.00770 -0.1227 0.7604 0.0845
-4.500 0.1036 0.01614 0.00752 -0.1215 0.7554 0.0891
-4.250 0.1290 0.01594 0.00725 -0.1210 0.7510 0.0944
-4.000 0.1569 0.01567 0.00696 -0.1211 0.7472 0.1002
-3.750 0.1751 0.01557 0.00686 -0.1192 0.7410 0.1057
-3.500 0.1976 0.01537 0.00668 -0.1181 0.7356 0.1121
-3.250 0.2246 0.01519 0.00645 -0.1180 0.7314 0.1202
-3.000 0.2467 0.01501 0.00632 -0.1169 0.7263 0.1280
-2.750 0.2676 0.01490 0.00620 -0.1155 0.7203 0.1365
-2.500 0.2921 0.01468 0.00602 -0.1148 0.7151 0.1475
-2.250 0.3166 0.01451 0.00586 -0.1142 0.7098 0.1606
-2.000 0.3355 0.01438 0.00580 -0.1124 0.7028 0.1762
-1.750 0.3599 0.01420 0.00565 -0.1117 0.6973 0.1982
-1.500 0.3829 0.01404 0.00556 -0.1108 0.6916 0.2254
-1.250 0.4018 0.01390 0.00553 -0.1091 0.6845 0.2571
-1.000 0.4259 0.01369 0.00540 -0.1084 0.6786 0.2974
-0.750 0.4435 0.01348 0.00539 -0.1064 0.6713 0.3475
-0.500 0.4612 0.01317 0.00538 -0.1045 0.6642 0.4388
-0.250 0.4817 0.01291 0.00531 -0.1030 0.6582 0.5143
0.000 0.4925 0.01255 0.00544 -0.0994 0.6504 0.6335
0.250 0.5141 0.01233 0.00550 -0.0977 0.6439 0.7470
0.500 0.5435 0.01236 0.00576 -0.0975 0.6362 0.8345
0.750 0.5838 0.01252 0.00592 -0.0996 0.6291 0.8925
1.000 0.6229 0.01271 0.00606 -0.1018 0.6220 0.9286
1.250 0.6670 0.01293 0.00622 -0.1050 0.6141 0.9547
1.500 0.7195 0.01316 0.00634 -0.1100 0.6073 0.9688
1.750 0.7659 0.01337 0.00648 -0.1140 0.5995 0.9785
2.000 0.8111 0.01352 0.00651 -0.1178 0.5926 0.9861
2.250 0.8555 0.01370 0.00664 -0.1215 0.5852 0.9950
2.500 0.8928 0.01385 0.00670 -0.1238 0.5783 1.0000
2.750 0.9048 0.01396 0.00675 -0.1209 0.5722 1.0000
3.000 0.9149 0.01408 0.00684 -0.1176 0.5659 1.0000
3.250 0.9277 0.01421 0.00689 -0.1148 0.5600 1.0000
3.500 0.9384 0.01435 0.00699 -0.1115 0.5542 1.0000
3.750 0.9456 0.01448 0.00709 -0.1076 0.5479 1.0000
4.000 0.9582 0.01463 0.00715 -0.1047 0.5417 1.0000
4.250 0.9662 0.01478 0.00729 -0.1010 0.5351 1.0000
4.500 0.9769 0.01496 0.00743 -0.0977 0.5283 1.0000
4.750 0.9947 0.01516 0.00754 -0.0959 0.5229 1.0000
5.000 1.0055 0.01537 0.00777 -0.0928 0.5173 1.0000
5.250 1.0199 0.01560 0.00798 -0.0905 0.5119 1.0000
5.500 1.0377 0.01583 0.00816 -0.0887 0.5067 1.0000
5.750 1.0533 0.01608 0.00841 -0.0867 0.5016 1.0000
6.000 1.0671 0.01635 0.00871 -0.0843 0.4960 1.0000
6.250 1.0841 0.01662 0.00896 -0.0825 0.4909 1.0000
6.500 1.1033 0.01689 0.00919 -0.0812 0.4861 1.0000
6.750 1.1151 0.01721 0.00958 -0.0786 0.4801 1.0000
7.000 1.1296 0.01754 0.00991 -0.0765 0.4736 1.0000
7.250 1.1452 0.01787 0.01022 -0.0746 0.4673 1.0000
7.500 1.1562 0.01828 0.01068 -0.0721 0.4599 1.0000
7.750 1.1701 0.01866 0.01102 -0.0700 0.4527 1.0000
8.000 1.1807 0.01913 0.01154 -0.0675 0.4447 1.0000
8.250 1.1924 0.01960 0.01201 -0.0652 0.4365 1.0000
8.500 1.2036 0.02013 0.01257 -0.0630 0.4283 1.0000
8.750 1.2145 0.02069 0.01313 -0.0608 0.4198 1.0000
9.000 1.2251 0.02130 0.01377 -0.0586 0.4108 1.0000
9.250 1.2348 0.02196 0.01441 -0.0564 0.4014 1.0000
9.500 1.2450 0.02267 0.01515 -0.0543 0.3917 1.0000
9.750 1.2546 0.02342 0.01589 -0.0522 0.3828 1.0000
10.000 1.2639 0.02423 0.01672 -0.0502 0.3727 1.0000
10.250 1.2726 0.02511 0.01760 -0.0482 0.3628 1.0000
10.500 1.2797 0.02610 0.01857 -0.0461 0.3525 1.0000
10.750 1.2880 0.02709 0.01957 -0.0442 0.3421 1.0000
11.000 1.2949 0.02818 0.02065 -0.0422 0.3323 1.0000
11.250 1.3019 0.02933 0.02180 -0.0404 0.3224 1.0000
11.500 1.3095 0.03049 0.02297 -0.0387 0.3131 1.0000
11.750 1.3151 0.03180 0.02426 -0.0369 0.3040 1.0000
12.000 1.3227 0.03304 0.02553 -0.0354 0.2951 1.0000
12.250 1.3276 0.03448 0.02695 -0.0337 0.2869 1.0000
12.500 1.3350 0.03583 0.02836 -0.0324 0.2783 1.0000
12.750 1.3394 0.03739 0.02990 -0.0308 0.2706 1.0000
13.000 1.3460 0.03887 0.03143 -0.0296 0.2624 1.0000
13.250 1.3496 0.04059 0.03314 -0.0282 0.2546 1.0000
13.500 1.3555 0.04221 0.03482 -0.0270 0.2471 1.0000
13.750 1.3579 0.04413 0.03672 -0.0258 0.2390 1.0000
14.000 1.3623 0.04594 0.03859 -0.0247 0.2313 1.0000
14.250 1.3641 0.04801 0.04066 -0.0236 0.2235 1.0000
14.500 1.3668 0.05008 0.04277 -0.0227 0.2152 1.0000
14.750 1.3674 0.05237 0.04507 -0.0218 0.2075 1.0000
15.000 1.3706 0.05448 0.04723 -0.0211 0.2007 1.0000
15.250 1.3729 0.05672 0.04951 -0.0204 0.1939 1.0000
15.500 1.3741 0.05910 0.05193 -0.0198 0.1874 1.0000
15.750 1.3759 0.06149 0.05436 -0.0193 0.1804 1.0000
16.000 1.3754 0.06412 0.05701 -0.0188 0.1743 1.0000
16.250 1.3770 0.06663 0.05959 -0.0185 0.1673 1.0000
16.500 1.3756 0.06945 0.06242 -0.0182 0.1619 1.0000
16.750 1.3779 0.07191 0.06496 -0.0180 0.1562 1.0000
17.000 1.3763 0.07486 0.06793 -0.0179 0.1505 1.0000
17.250 1.3761 0.07765 0.07076 -0.0178 0.1457 1.0000
17.500 1.3767 0.08042 0.07359 -0.0178 0.1407 1.0000
17.750 1.3743 0.08353 0.07673 -0.0179 0.1361 1.0000
18.000 1.3746 0.08636 0.07962 -0.0181 0.1319 1.0000
18.250 1.3752 0.08916 0.08249 -0.0183 0.1279 1.0000
18.500 1.3738 0.09224 0.08561 -0.0186 0.1242 1.0000
18.750 1.3721 0.09538 0.08878 -0.0190 0.1205 1.0000
19.000 1.3733 0.09822 0.09173 -0.0195 0.1168 1.0000
19.250 1.3714 0.10145 0.09503 -0.0201 0.1129 1.0000
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