GOE 507 AIRFOIL (goe507-il) Xfoil prediction polar at RE=100,000 Ncrit=9
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Airfoil: GOE 507 AIRFOIL (goe507-il) Reynolds number: 100,000 Max Cl/Cd: 55.45 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe507-il-100000.txt Download as CSV file: xf-goe507-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 507 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.4164 0.10796 0.10256 -0.0251 1.0000 0.1081
-9.500 -0.4365 0.10665 0.10136 -0.0300 1.0000 0.1119
-9.250 -0.4603 0.10515 0.10001 -0.0349 1.0000 0.1125
-9.000 -0.4114 0.09840 0.09312 -0.0277 1.0000 0.1175
-8.750 -0.4106 0.09575 0.09052 -0.0285 1.0000 0.1228
-8.500 -0.4389 0.09444 0.08938 -0.0329 1.0000 0.1260
-8.250 -0.4170 0.08969 0.08460 -0.0300 1.0000 0.1300
-8.000 -0.4130 0.08726 0.08220 -0.0292 1.0000 0.1363
-7.750 -0.4392 0.08564 0.08075 -0.0311 1.0000 0.1397
-7.500 -0.4770 0.08393 0.07908 -0.0381 1.0000 0.1410
-7.250 -0.4362 0.07936 0.07457 -0.0282 1.0000 0.1460
-7.000 -0.4416 0.07710 0.07237 -0.0274 1.0000 0.1511
-6.750 -0.4777 0.07502 0.07024 -0.0329 1.0000 0.1562
-6.500 -0.4637 0.07165 0.06700 -0.0270 1.0000 0.1587
-6.250 -0.4609 0.06966 0.06504 -0.0240 1.0000 0.1639
-6.000 -0.4739 0.06649 0.06174 -0.0273 1.0000 0.1722
-5.750 -0.4660 0.06427 0.05963 -0.0226 1.0000 0.1763
-5.500 -0.4675 0.06125 0.05640 -0.0253 1.0000 0.1876
-5.250 -0.4601 0.05861 0.05385 -0.0220 1.0000 0.1907
-5.000 -0.4535 0.05575 0.05077 -0.0238 1.0000 0.2031
-4.750 -0.4445 0.05327 0.04836 -0.0209 1.0000 0.2075
-4.500 -0.4143 0.03793 0.03127 -0.0312 1.0000 0.1278
-4.250 -0.3960 0.03495 0.02805 -0.0304 1.0000 0.1237
-4.000 -0.3765 0.03215 0.02481 -0.0299 1.0000 0.1232
-3.750 -0.3553 0.02959 0.02185 -0.0293 1.0000 0.1216
-3.500 -0.3335 0.02764 0.01949 -0.0285 1.0000 0.1221
-3.250 -0.3116 0.02618 0.01762 -0.0277 1.0000 0.1242
-3.000 -0.2894 0.02486 0.01595 -0.0269 1.0000 0.1250
-2.750 -0.2673 0.02381 0.01458 -0.0260 1.0000 0.1259
-2.500 -0.2460 0.02288 0.01357 -0.0252 1.0000 0.1289
-2.250 -0.2227 0.02236 0.01302 -0.0248 0.9993 0.1327
-2.000 -0.1816 0.02183 0.01232 -0.0276 0.9933 0.1367
-1.750 -0.1418 0.02138 0.01169 -0.0300 0.9865 0.1411
-1.500 -0.1029 0.02100 0.01146 -0.0325 0.9798 0.1482
-1.250 -0.0628 0.02077 0.01125 -0.0351 0.9724 0.1592
-1.000 -0.0263 0.02050 0.01108 -0.0369 0.9644 0.1736
-0.750 0.0150 0.02009 0.01094 -0.0396 0.9571 0.2099
-0.500 0.0880 0.01719 0.01086 -0.0483 0.9571 1.0000
-0.250 0.1250 0.01745 0.01082 -0.0502 0.9468 1.0000
0.000 0.1702 0.01775 0.01090 -0.0537 0.9382 1.0000
0.250 0.2112 0.01795 0.01095 -0.0563 0.9280 1.0000
0.500 0.2489 0.01814 0.01103 -0.0583 0.9169 1.0000
0.750 0.3037 0.01820 0.01101 -0.0633 0.9099 1.0000
1.000 0.3390 0.01827 0.01103 -0.0646 0.8972 1.0000
1.250 0.3791 0.01827 0.01101 -0.0667 0.8854 1.0000
1.500 0.4398 0.01790 0.01065 -0.0722 0.8788 1.0000
1.750 0.4764 0.01770 0.01045 -0.0731 0.8649 1.0000
2.000 0.5127 0.01741 0.01018 -0.0738 0.8507 1.0000
2.250 0.5467 0.01712 0.00992 -0.0739 0.8364 1.0000
2.500 0.5783 0.01686 0.00970 -0.0735 0.8219 1.0000
2.750 0.6082 0.01663 0.00950 -0.0729 0.8071 1.0000
3.000 0.6372 0.01637 0.00929 -0.0720 0.7913 1.0000
3.250 0.6665 0.01594 0.00887 -0.0707 0.7733 1.0000
3.500 0.6922 0.01557 0.00850 -0.0689 0.7517 1.0000
3.750 0.7173 0.01525 0.00817 -0.0670 0.7280 1.0000
4.000 0.7411 0.01508 0.00802 -0.0652 0.7030 1.0000
4.250 0.7657 0.01494 0.00785 -0.0635 0.6771 1.0000
4.500 0.7888 0.01490 0.00777 -0.0617 0.6479 1.0000
4.750 0.8102 0.01495 0.00778 -0.0596 0.6129 1.0000
5.000 0.8320 0.01510 0.00784 -0.0577 0.5786 1.0000
5.250 0.8528 0.01538 0.00796 -0.0557 0.5409 1.0000
5.500 0.8717 0.01577 0.00822 -0.0536 0.4995 1.0000
5.750 0.8894 0.01621 0.00857 -0.0513 0.4551 1.0000
6.000 0.9045 0.01674 0.00893 -0.0487 0.3964 1.0000
6.250 0.9120 0.01782 0.00943 -0.0450 0.2900 1.0000
6.500 0.9156 0.01976 0.01050 -0.0412 0.1824 1.0000
6.750 0.9279 0.02117 0.01155 -0.0387 0.1490 1.0000
7.000 0.9429 0.02236 0.01264 -0.0366 0.1320 1.0000
7.250 0.9587 0.02363 0.01379 -0.0346 0.1202 1.0000
7.500 0.9760 0.02511 0.01509 -0.0330 0.1105 1.0000
7.750 0.9973 0.02639 0.01644 -0.0318 0.1021 1.0000
8.000 1.0218 0.02830 0.01825 -0.0313 0.0949 1.0000
8.250 1.0460 0.02990 0.01997 -0.0306 0.0887 1.0000
8.500 1.0743 0.03255 0.02252 -0.0309 0.0829 1.0000
8.750 1.0968 0.03448 0.02478 -0.0297 0.0797 1.0000
9.000 1.1183 0.03654 0.02705 -0.0287 0.0756 1.0000
9.250 1.1405 0.03955 0.03008 -0.0284 0.0719 1.0000
9.500 1.1564 0.04338 0.03427 -0.0270 0.0705 1.0000
9.750 1.1657 0.04582 0.03721 -0.0244 0.0696 1.0000
10.000 1.1713 0.04851 0.04038 -0.0216 0.0685 1.0000
10.250 1.1730 0.05144 0.04376 -0.0187 0.0672 1.0000
10.500 1.1716 0.05488 0.04759 -0.0158 0.0669 1.0000
10.750 1.1660 0.05870 0.05178 -0.0129 0.0674 1.0000
11.000 1.1563 0.06271 0.05612 -0.0100 0.0681 1.0000
11.250 1.1448 0.06682 0.06046 -0.0073 0.0690 1.0000
11.500 1.1359 0.07171 0.06550 -0.0054 0.0701 1.0000
11.750 1.0460 0.07026 0.06451 0.0013 0.0712 1.0000
12.000 1.0099 0.07321 0.06770 0.0032 0.0720 1.0000
12.250 0.8727 0.08867 0.08374 -0.0048 0.0787 1.0000
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Polar data table (+)
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