GOE 670 AIRFOIL (goe670-il) Xfoil prediction polar at RE=50,000 Ncrit=9
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Airfoil: GOE 670 AIRFOIL (goe670-il) Reynolds number: 50,000 Max Cl/Cd: 35.66 at α=6.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe670-il-50000.txt Download as CSV file: xf-goe670-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 670 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.3926 0.11006 0.10291 -0.0275 1.0000 0.2060
-8.500 -0.3740 0.10500 0.09785 -0.0258 1.0000 0.2140
-8.250 -0.3894 0.10419 0.09717 -0.0251 1.0000 0.2208
-8.000 -0.3867 0.10078 0.09382 -0.0239 1.0000 0.2259
-7.750 -0.3895 0.09869 0.09179 -0.0222 1.0000 0.2348
-7.500 -0.4247 0.09922 0.09254 -0.0200 1.0000 0.2376
-7.250 -0.3997 0.09412 0.08740 -0.0183 1.0000 0.2486
-7.000 -0.4347 0.09428 0.08776 -0.0163 1.0000 0.2530
-6.750 -0.4185 0.09015 0.08363 -0.0134 1.0000 0.2631
-6.500 -0.4565 0.09030 0.08394 -0.0139 1.0000 0.2693
-6.250 -0.4443 0.08655 0.08022 -0.0102 1.0000 0.2834
-6.000 -0.4412 0.08364 0.07737 -0.0074 1.0000 0.2968
-5.750 -0.4443 0.08118 0.07496 -0.0049 1.0000 0.3115
-5.500 -0.4489 0.07885 0.07270 -0.0027 1.0000 0.3276
-5.250 -0.4614 0.07718 0.07107 -0.0016 1.0000 0.3462
-5.000 -0.4559 0.07394 0.06791 0.0024 1.0000 0.3650
-4.750 -0.4533 0.07151 0.06553 0.0063 1.0000 0.3886
-4.500 0.0291 0.04716 0.03978 -0.0342 1.0000 1.0000
-4.250 0.0337 0.04568 0.03837 -0.0335 1.0000 1.0000
-4.000 -0.1692 0.05555 0.04898 0.0102 1.0000 0.8526
-3.750 -0.0980 0.05052 0.04378 -0.0006 1.0000 0.9215
-3.500 -0.1686 0.05198 0.04554 0.0135 1.0000 0.8667
-3.250 -0.2491 0.05319 0.04706 0.0268 1.0000 0.8057
-3.000 -0.3227 0.05356 0.04771 0.0381 1.0000 0.7642
-2.750 -0.2970 0.04203 0.03344 -0.0254 1.0000 0.2052
-2.500 -0.2701 0.03932 0.03003 -0.0262 1.0000 0.1910
-2.250 -0.2485 0.03747 0.02782 -0.0258 1.0000 0.1911
-2.000 -0.2269 0.03575 0.02577 -0.0253 1.0000 0.1909
-1.750 -0.2050 0.03417 0.02385 -0.0247 1.0000 0.1905
-1.500 -0.1833 0.03279 0.02218 -0.0241 1.0000 0.1922
-1.250 -0.1638 0.03181 0.02117 -0.0233 1.0000 0.1994
-1.000 -0.1418 0.03101 0.01999 -0.0226 1.0000 0.2075
-0.750 -0.1201 0.03016 0.01908 -0.0221 1.0000 0.2150
-0.500 -0.0995 0.02957 0.01838 -0.0213 1.0000 0.2288
-0.250 -0.0778 0.02911 0.01781 -0.0206 1.0000 0.2446
0.000 -0.0525 0.02880 0.01739 -0.0206 1.0000 0.2670
0.250 -0.0273 0.02847 0.01710 -0.0207 1.0000 0.2939
0.500 -0.0032 0.02818 0.01695 -0.0206 1.0000 0.3332
0.750 0.0213 0.02764 0.01692 -0.0206 1.0000 0.4019
1.000 0.0624 0.02616 0.01668 -0.0230 1.0000 1.0000
1.250 0.0805 0.02682 0.01699 -0.0223 1.0000 1.0000
1.500 0.0980 0.02752 0.01746 -0.0217 1.0000 1.0000
1.750 0.1152 0.02826 0.01802 -0.0211 1.0000 1.0000
2.000 0.1487 0.02952 0.01911 -0.0238 0.9931 1.0000
2.250 0.2023 0.03119 0.02063 -0.0302 0.9738 1.0000
2.500 0.2610 0.03263 0.02197 -0.0369 0.9477 1.0000
2.750 0.3196 0.03365 0.02294 -0.0429 0.9197 1.0000
3.000 0.3776 0.03437 0.02365 -0.0483 0.8944 1.0000
3.250 0.4196 0.03483 0.02413 -0.0509 0.8717 1.0000
3.500 0.4755 0.03512 0.02448 -0.0552 0.8513 1.0000
3.750 0.5081 0.03532 0.02476 -0.0558 0.8275 1.0000
4.000 0.5666 0.03492 0.02450 -0.0596 0.8064 1.0000
4.250 0.6031 0.03465 0.02437 -0.0599 0.7806 1.0000
4.500 0.6550 0.03364 0.02353 -0.0617 0.7559 1.0000
4.750 0.7254 0.03145 0.02162 -0.0651 0.7321 1.0000
5.000 0.7850 0.02935 0.01973 -0.0666 0.7026 1.0000
5.250 0.8402 0.02750 0.01804 -0.0674 0.6661 1.0000
5.500 0.8975 0.02610 0.01660 -0.0689 0.6243 1.0000
5.750 0.9264 0.02641 0.01683 -0.0676 0.5841 1.0000
6.000 0.9540 0.02690 0.01729 -0.0665 0.5516 1.0000
6.250 0.9777 0.02760 0.01798 -0.0651 0.5250 1.0000
6.500 1.0060 0.02821 0.01854 -0.0644 0.5031 1.0000
6.750 1.0263 0.02911 0.01951 -0.0628 0.4824 1.0000
7.000 1.0495 0.02984 0.02029 -0.0615 0.4620 1.0000
7.250 1.0759 0.03053 0.02091 -0.0606 0.4417 1.0000
7.500 1.0943 0.03164 0.02215 -0.0588 0.4232 1.0000
7.750 1.1145 0.03285 0.02348 -0.0573 0.4058 1.0000
8.000 1.1360 0.03379 0.02447 -0.0558 0.3846 1.0000
8.250 1.1503 0.03453 0.02522 -0.0531 0.3584 1.0000
8.500 1.1620 0.03480 0.02536 -0.0498 0.3269 1.0000
8.750 1.1708 0.03525 0.02573 -0.0463 0.2965 1.0000
9.000 1.1774 0.03597 0.02636 -0.0426 0.2640 1.0000
9.250 1.1755 0.03715 0.02744 -0.0377 0.2248 1.0000
9.500 1.1702 0.03864 0.02858 -0.0324 0.1842 1.0000
9.750 1.1705 0.04028 0.03005 -0.0282 0.1568 1.0000
10.000 1.1743 0.04223 0.03213 -0.0247 0.1386 1.0000
10.250 1.1847 0.04427 0.03418 -0.0223 0.1254 1.0000
10.500 1.2049 0.04680 0.03663 -0.0213 0.1157 1.0000
10.750 1.2130 0.04968 0.03990 -0.0189 0.1093 1.0000
11.000 1.2288 0.05245 0.04267 -0.0178 0.1030 1.0000
11.250 1.2246 0.05577 0.04648 -0.0144 0.1004 1.0000
11.500 1.2188 0.05926 0.05034 -0.0112 0.0989 1.0000
11.750 1.2076 0.06293 0.05435 -0.0080 0.0981 1.0000
12.000 1.1902 0.06687 0.05860 -0.0051 0.0979 1.0000
12.250 1.1666 0.07126 0.06329 -0.0028 0.0982 1.0000
12.500 1.1374 0.07636 0.06866 -0.0015 0.0989 1.0000
12.750 1.1053 0.08233 0.07484 -0.0019 0.1001 1.0000
13.000 1.0719 0.08938 0.08203 -0.0039 0.1014 1.0000
13.250 1.0406 0.09740 0.09015 -0.0073 0.1027 1.0000
13.500 1.0152 0.10584 0.09864 -0.0112 0.1038 1.0000
13.750 0.8954 0.14069 0.13323 -0.0355 0.1279 1.0000
14.000 0.8886 0.14826 0.14079 -0.0389 0.1310 1.0000
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Polar data table (+)
Polar graphs
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