GOE 57 AIRFOIL (goe57-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 57 AIRFOIL (goe57-il) Reynolds number: 500,000 Max Cl/Cd: 86.46 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe57-il-500000-n5.txt Download as CSV file: xf-goe57-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 57 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.3313 0.10121 0.09897 -0.0249 1.0000 0.0089
-8.750 -0.3308 0.09751 0.09530 -0.0258 1.0000 0.0092
-8.500 -0.3333 0.09381 0.09163 -0.0264 1.0000 0.0097
-8.250 -0.3298 0.09211 0.08998 -0.0260 1.0000 0.0100
-8.000 -0.3285 0.09065 0.08855 -0.0250 1.0000 0.0103
-7.750 -0.3093 0.08728 0.08517 -0.0296 0.9950 0.0108
-7.500 -0.2895 0.08298 0.08087 -0.0355 0.9870 0.0113
-7.250 -0.2689 0.07804 0.07591 -0.0424 0.9775 0.0121
-7.000 -0.2458 0.07070 0.06854 -0.0530 0.9653 0.0135
-6.750 -0.2194 0.06859 0.06640 -0.0571 0.9542 0.0140
-6.500 -0.1913 0.06556 0.06333 -0.0625 0.9423 0.0148
-6.250 -0.1623 0.06140 0.05910 -0.0694 0.9297 0.0158
-6.000 -0.1239 0.05246 0.04998 -0.0834 0.9161 0.0186
-5.750 -0.0992 0.05081 0.04827 -0.0856 0.9062 0.0191
-5.500 -0.0740 0.04891 0.04629 -0.0880 0.8965 0.0197
-5.250 -0.0466 0.04640 0.04368 -0.0913 0.8868 0.0205
-5.000 -0.0171 0.04349 0.04064 -0.0951 0.8769 0.0221
-4.750 0.0171 0.03916 0.03611 -0.1005 0.8670 0.0234
-4.500 0.0549 0.03428 0.03096 -0.1056 0.8584 0.0250
-4.250 0.0840 0.03075 0.02720 -0.1085 0.8487 0.0263
-4.000 0.1106 0.02909 0.02538 -0.1095 0.8342 0.0268
-3.750 0.1377 0.02734 0.02344 -0.1104 0.8167 0.0273
-3.500 0.1660 0.02524 0.02110 -0.1114 0.7997 0.0277
-3.250 0.1954 0.02278 0.01838 -0.1124 0.7864 0.0280
-3.000 0.2239 0.02100 0.01637 -0.1131 0.7740 0.0286
-2.750 0.2538 0.01813 0.01312 -0.1138 0.7607 0.0287
-2.500 0.2831 0.01522 0.00974 -0.1143 0.7461 0.0291
-2.250 0.3109 0.01370 0.00786 -0.1143 0.7271 0.0300
-2.000 0.3377 0.01282 0.00665 -0.1141 0.6992 0.0309
-1.750 0.3639 0.01225 0.00578 -0.1136 0.6672 0.0317
-1.500 0.3903 0.01182 0.00509 -0.1133 0.6410 0.0322
-1.250 0.4168 0.01147 0.00453 -0.1130 0.6169 0.0326
-1.000 0.4434 0.01116 0.00404 -0.1127 0.5957 0.0329
-0.750 0.4702 0.01092 0.00365 -0.1124 0.5742 0.0332
-0.500 0.4967 0.01084 0.00343 -0.1121 0.5488 0.0337
-0.250 0.5228 0.01081 0.00323 -0.1117 0.5153 0.0341
0.000 0.5480 0.01081 0.00298 -0.1112 0.4683 0.0342
0.250 0.5736 0.01081 0.00277 -0.1108 0.4286 0.0343
0.500 0.5993 0.01085 0.00262 -0.1104 0.3942 0.0345
0.750 0.6253 0.01078 0.00238 -0.1101 0.3630 0.0353
1.000 0.6513 0.01084 0.00228 -0.1098 0.3313 0.0369
1.250 0.6772 0.01099 0.00230 -0.1095 0.3011 0.0391
1.500 0.7032 0.01117 0.00236 -0.1091 0.2717 0.0419
1.750 0.7287 0.01143 0.00245 -0.1087 0.2349 0.0449
2.000 0.7540 0.01171 0.00257 -0.1084 0.2022 0.0491
2.250 0.7802 0.01187 0.00269 -0.1081 0.1893 0.0564
2.500 0.8068 0.01199 0.00280 -0.1078 0.1837 0.0665
2.750 0.8333 0.01208 0.00296 -0.1076 0.1797 0.0972
3.000 0.8599 0.01208 0.00317 -0.1075 0.1764 0.1996
3.500 0.9088 0.01098 0.00359 -0.1064 0.1720 1.0000
3.750 0.9350 0.01118 0.00376 -0.1061 0.1673 1.0000
4.000 0.9606 0.01146 0.00396 -0.1058 0.1612 1.0000
4.250 0.9866 0.01168 0.00417 -0.1054 0.1577 1.0000
4.500 1.0129 0.01185 0.00433 -0.1052 0.1533 1.0000
4.750 1.0386 0.01208 0.00454 -0.1048 0.1482 1.0000
5.000 1.0643 0.01231 0.00472 -0.1045 0.1398 1.0000
5.500 1.1058 0.01403 0.00581 -0.1025 0.0227 1.0000
5.750 1.1301 0.01443 0.00621 -0.1018 0.0157 1.0000
6.000 1.1545 0.01480 0.00664 -0.1013 0.0137 1.0000
6.250 1.1784 0.01524 0.00715 -0.1006 0.0122 1.0000
6.500 1.2013 0.01580 0.00782 -0.0997 0.0107 1.0000
6.750 1.2249 0.01622 0.00828 -0.0991 0.0100 1.0000
7.000 1.2479 0.01670 0.00883 -0.0983 0.0092 1.0000
7.250 1.2703 0.01727 0.00945 -0.0974 0.0085 1.0000
7.500 1.2918 0.01790 0.01017 -0.0965 0.0080 1.0000
7.750 1.3119 0.01868 0.01102 -0.0953 0.0076 1.0000
8.000 1.3287 0.01979 0.01223 -0.0937 0.0071 1.0000
8.250 1.3490 0.02042 0.01293 -0.0925 0.0068 1.0000
8.500 1.3684 0.02112 0.01370 -0.0913 0.0064 1.0000
8.750 1.3860 0.02194 0.01459 -0.0898 0.0060 1.0000
9.000 1.4018 0.02287 0.01563 -0.0881 0.0057 1.0000
9.250 1.4165 0.02383 0.01666 -0.0863 0.0055 1.0000
9.500 1.4294 0.02485 0.01777 -0.0842 0.0053 1.0000
9.750 1.4389 0.02593 0.01892 -0.0816 0.0051 1.0000
10.000 1.4440 0.02723 0.02030 -0.0785 0.0050 1.0000
10.250 1.4440 0.02894 0.02212 -0.0749 0.0049 1.0000
10.500 1.4467 0.03057 0.02385 -0.0720 0.0048 1.0000
10.750 1.4505 0.03219 0.02559 -0.0695 0.0047 1.0000
11.000 1.4531 0.03404 0.02755 -0.0671 0.0046 1.0000
11.250 1.4547 0.03608 0.02972 -0.0648 0.0045 1.0000
11.500 1.4560 0.03827 0.03206 -0.0628 0.0044 1.0000
11.750 1.4572 0.04057 0.03449 -0.0611 0.0043 1.0000
12.000 1.4584 0.04295 0.03700 -0.0596 0.0041 1.0000
12.250 1.4593 0.04545 0.03962 -0.0583 0.0040 1.0000
12.500 1.4595 0.04807 0.04238 -0.0573 0.0039 1.0000
12.750 1.4590 0.05089 0.04531 -0.0565 0.0038 1.0000
13.000 1.4579 0.05387 0.04842 -0.0560 0.0037 1.0000
13.250 1.4551 0.05715 0.05184 -0.0557 0.0036 1.0000
13.500 1.4516 0.06067 0.05548 -0.0556 0.0035 1.0000
13.750 1.4467 0.06448 0.05943 -0.0557 0.0035 1.0000
14.000 1.4411 0.06848 0.06357 -0.0562 0.0035 1.0000
14.250 1.4348 0.07276 0.06799 -0.0570 0.0034 1.0000
14.500 1.4279 0.07730 0.07266 -0.0580 0.0034 1.0000
14.750 1.4202 0.08210 0.07760 -0.0594 0.0034 1.0000
15.000 1.4117 0.08718 0.08282 -0.0610 0.0033 1.0000
15.250 1.4025 0.09254 0.08832 -0.0629 0.0033 1.0000
15.500 1.3930 0.09814 0.09406 -0.0651 0.0033 1.0000
15.750 1.3825 0.10401 0.10007 -0.0675 0.0033 1.0000
16.000 1.3726 0.10997 0.10616 -0.0703 0.0033 1.0000
16.250 1.3618 0.11624 0.11257 -0.0732 0.0033 1.0000
16.500 1.3510 0.12268 0.11915 -0.0764 0.0032 1.0000
16.750 1.3400 0.12930 0.12590 -0.0798 0.0032 1.0000
17.000 1.3288 0.13614 0.13290 -0.0835 0.0032 1.0000
17.250 1.3179 0.14314 0.14004 -0.0874 0.0032 1.0000
17.500 1.3070 0.15040 0.14743 -0.0917 0.0032 1.0000
17.750 1.2960 0.15795 0.15512 -0.0963 0.0032 1.0000
18.000 1.2848 0.16584 0.16311 -0.1012 0.0032 1.0000
18.250 1.2739 0.17396 0.17135 -0.1064 0.0032 1.0000
18.500 1.2618 0.18289 0.18042 -0.1121 0.0032 1.0000
18.750 1.2490 0.19264 0.19031 -0.1184 0.0032 1.0000
19.000 1.2293 0.20595 0.20379 -0.1268 0.0033 1.0000
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