GOE 316 (HANSA-BRANDENBURG IV.5) AIRFOIL (goe316-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 316 (HANSA-BRANDENBURG IV.5) AIRFOIL (goe316-il) Reynolds number: 1,000,000 Max Cl/Cd: 118.64 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe316-il-1000000-n5.txt Download as CSV file: xf-goe316-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 316 (HANSA-BRANDENBURG IV.5) AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.4532 0.09155 0.08929 -0.0018 0.7528 0.0085
-8.500 -0.4503 0.08758 0.08529 -0.0045 0.7439 0.0089
-8.250 -0.4605 0.07875 0.07646 -0.0132 0.7374 0.0100
-8.000 -0.4468 0.07542 0.07309 -0.0173 0.7290 0.0101
-7.750 -0.4313 0.07214 0.06976 -0.0213 0.7200 0.0103
-7.500 -0.4148 0.06855 0.06611 -0.0256 0.7120 0.0106
-7.250 -0.3972 0.06447 0.06197 -0.0302 0.7043 0.0109
-7.000 -0.3827 0.05257 0.04984 -0.0415 0.7002 0.0128
-6.750 -0.3600 0.05035 0.04755 -0.0433 0.6925 0.0130
-6.500 -0.3369 0.04819 0.04529 -0.0450 0.6842 0.0132
-6.250 -0.3134 0.04563 0.04262 -0.0468 0.6743 0.0136
-6.000 -0.2911 0.03492 0.03141 -0.0517 0.6688 0.0161
-5.750 -0.2657 0.03375 0.03012 -0.0521 0.6564 0.0163
-5.500 -0.2401 0.03254 0.02881 -0.0526 0.6439 0.0166
-5.250 -0.2143 0.03092 0.02703 -0.0531 0.6300 0.0170
-5.000 -0.1882 0.02878 0.02468 -0.0536 0.6135 0.0176
-4.750 -0.1634 0.02000 0.01508 -0.0541 0.6019 0.0203
-4.500 -0.1362 0.01931 0.01421 -0.0543 0.5805 0.0206
-4.250 -0.1088 0.01881 0.01357 -0.0544 0.5627 0.0208
-4.000 -0.0812 0.01820 0.01281 -0.0545 0.5462 0.0212
-3.750 -0.0537 0.01675 0.01111 -0.0546 0.5317 0.0217
-3.500 -0.0260 0.01486 0.00889 -0.0546 0.5181 0.0224
-3.250 0.0018 0.01337 0.00710 -0.0546 0.5040 0.0233
-3.000 0.0299 0.01264 0.00618 -0.0546 0.4890 0.0239
-2.750 0.0581 0.01215 0.00553 -0.0547 0.4724 0.0243
-2.500 0.0864 0.01181 0.00505 -0.0547 0.4540 0.0245
-2.250 0.1146 0.01155 0.00465 -0.0548 0.4320 0.0246
-2.000 0.1426 0.01112 0.00404 -0.0549 0.4042 0.0249
-1.750 0.1704 0.01071 0.00347 -0.0550 0.3776 0.0253
-1.500 0.1986 0.01049 0.00315 -0.0550 0.3598 0.0257
-1.250 0.2269 0.01034 0.00292 -0.0551 0.3475 0.0260
-1.000 0.2553 0.01020 0.00273 -0.0552 0.3392 0.0263
-0.750 0.2838 0.01011 0.00260 -0.0553 0.3322 0.0267
-0.500 0.3124 0.01003 0.00250 -0.0554 0.3275 0.0273
-0.250 0.3409 0.00993 0.00237 -0.0555 0.3229 0.0279
0.250 0.3980 0.00976 0.00214 -0.0557 0.3155 0.0290
0.500 0.4267 0.00969 0.00206 -0.0558 0.3129 0.0296
0.750 0.4553 0.00965 0.00200 -0.0560 0.3100 0.0301
1.000 0.4839 0.00962 0.00195 -0.0561 0.3071 0.0305
1.250 0.5124 0.00962 0.00193 -0.0562 0.3041 0.0308
1.500 0.5410 0.00959 0.00188 -0.0563 0.3012 0.0315
1.750 0.5696 0.00954 0.00185 -0.0565 0.3000 0.0328
2.000 0.5982 0.00954 0.00187 -0.0566 0.2985 0.0345
2.250 0.6267 0.00955 0.00190 -0.0567 0.2969 0.0365
2.500 0.6553 0.00957 0.00193 -0.0568 0.2952 0.0383
2.750 0.6837 0.00959 0.00197 -0.0570 0.2935 0.0423
3.000 0.7121 0.00963 0.00203 -0.0571 0.2918 0.0476
3.250 0.7405 0.00968 0.00210 -0.0572 0.2897 0.0578
3.500 0.7638 0.00783 0.00235 -0.0569 0.2859 1.0000
3.750 0.7922 0.00791 0.00241 -0.0570 0.2834 1.0000
4.000 0.8206 0.00800 0.00248 -0.0571 0.2802 1.0000
4.250 0.8487 0.00811 0.00257 -0.0572 0.2762 1.0000
4.500 0.8768 0.00825 0.00267 -0.0573 0.2722 1.0000
4.750 0.9049 0.00836 0.00279 -0.0574 0.2699 1.0000
5.000 0.9330 0.00846 0.00289 -0.0576 0.2682 1.0000
5.250 0.9611 0.00857 0.00301 -0.0577 0.2657 1.0000
5.500 0.9891 0.00868 0.00313 -0.0578 0.2621 1.0000
5.750 1.0168 0.00884 0.00326 -0.0579 0.2573 1.0000
6.000 1.0446 0.00896 0.00340 -0.0580 0.2539 1.0000
6.250 1.0724 0.00910 0.00354 -0.0581 0.2476 1.0000
6.500 1.0998 0.00927 0.00369 -0.0581 0.2397 1.0000
6.750 1.1263 0.00959 0.00389 -0.0581 0.2151 1.0000
7.000 1.1483 0.01060 0.00452 -0.0578 0.1516 1.0000
7.250 1.1727 0.01122 0.00500 -0.0575 0.1251 1.0000
7.500 1.1967 0.01185 0.00549 -0.0573 0.0986 1.0000
8.000 1.2439 0.01317 0.00656 -0.0566 0.0535 1.0000
8.250 1.2689 0.01357 0.00696 -0.0564 0.0488 1.0000
8.500 1.2942 0.01390 0.00731 -0.0563 0.0457 1.0000
8.750 1.3191 0.01427 0.00770 -0.0561 0.0417 1.0000
9.000 1.3429 0.01476 0.00817 -0.0558 0.0356 1.0000
9.250 1.3648 0.01546 0.00876 -0.0553 0.0223 1.0000
9.500 1.3864 0.01615 0.00942 -0.0547 0.0150 1.0000
9.750 1.4091 0.01668 0.00998 -0.0542 0.0127 1.0000
10.000 1.4309 0.01726 0.01058 -0.0537 0.0111 1.0000
10.250 1.4527 0.01781 0.01117 -0.0531 0.0101 1.0000
10.500 1.4742 0.01834 0.01175 -0.0525 0.0094 1.0000
10.750 1.4946 0.01895 0.01241 -0.0518 0.0087 1.0000
11.000 1.5138 0.01964 0.01314 -0.0509 0.0080 1.0000
11.250 1.5319 0.02037 0.01392 -0.0500 0.0075 1.0000
11.500 1.5500 0.02102 0.01463 -0.0490 0.0072 1.0000
11.750 1.5668 0.02174 0.01541 -0.0479 0.0068 1.0000
12.000 1.5814 0.02253 0.01626 -0.0465 0.0064 1.0000
12.250 1.5914 0.02341 0.01719 -0.0445 0.0061 1.0000
12.500 1.5985 0.02449 0.01834 -0.0423 0.0058 1.0000
12.750 1.6038 0.02586 0.01979 -0.0405 0.0056 1.0000
13.000 1.6095 0.02739 0.02140 -0.0391 0.0054 1.0000
13.250 1.6159 0.02904 0.02315 -0.0382 0.0053 1.0000
13.500 1.6213 0.03098 0.02518 -0.0377 0.0052 1.0000
13.750 1.6252 0.03321 0.02750 -0.0375 0.0050 1.0000
14.000 1.6278 0.03571 0.03010 -0.0374 0.0049 1.0000
14.250 1.6286 0.03850 0.03300 -0.0375 0.0048 1.0000
14.500 1.6274 0.04159 0.03618 -0.0378 0.0047 1.0000
14.750 1.6245 0.04498 0.03968 -0.0382 0.0046 1.0000
15.000 1.6191 0.04876 0.04357 -0.0389 0.0045 1.0000
15.250 1.6119 0.05290 0.04782 -0.0397 0.0044 1.0000
15.500 1.6027 0.05739 0.05242 -0.0407 0.0044 1.0000
15.750 1.5915 0.06221 0.05736 -0.0418 0.0043 1.0000
16.000 1.5792 0.06727 0.06252 -0.0431 0.0043 1.0000
16.250 1.5661 0.07258 0.06794 -0.0445 0.0042 1.0000
16.500 1.5526 0.07809 0.07357 -0.0462 0.0042 1.0000
16.750 1.5389 0.08371 0.07929 -0.0479 0.0041 1.0000
17.000 1.5253 0.08939 0.08507 -0.0496 0.0041 1.0000
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Polar data table (+)
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