GOE 315 (HANSA-BRANDENBURG III.5) AIRFOIL (goe315-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 315 (HANSA-BRANDENBURG III.5) AIRFOIL (goe315-il) Reynolds number: 1,000,000 Max Cl/Cd: 87.02 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe315-il-1000000-n5.txt Download as CSV file: xf-goe315-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 315 (HANSA-BRANDENBURG III.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
------ -------- --------- --------- -------- -------- --------
-10.500 -0.4160 0.11067 0.10895 -0.0100 1.0000 0.0076
-10.250 -0.4119 0.10722 0.10551 -0.0113 1.0000 0.0079
-10.000 -0.4168 0.10136 0.09966 -0.0136 1.0000 0.0087
-9.750 -0.4115 0.09846 0.09678 -0.0148 1.0000 0.0088
-9.500 -0.4060 0.09568 0.09401 -0.0159 1.0000 0.0089
-9.250 -0.3987 0.09340 0.09174 -0.0168 1.0000 0.0091
-9.000 -0.3945 0.09048 0.08884 -0.0180 1.0000 0.0092
-8.500 -0.3395 0.07970 0.07799 -0.0361 0.9392 0.0101
-8.250 -0.3268 0.07238 0.07020 -0.0470 0.8186 0.0111
-8.000 -0.3232 0.07009 0.06777 -0.0482 0.7842 0.0112
-7.750 -0.3155 0.06761 0.06521 -0.0500 0.7647 0.0114
-7.500 -0.3069 0.06466 0.06220 -0.0523 0.7511 0.0115
-7.250 -0.2960 0.06171 0.05918 -0.0546 0.7400 0.0118
-7.000 -0.2841 0.05830 0.05569 -0.0571 0.7301 0.0121
-6.750 -0.2795 0.04943 0.04663 -0.0629 0.7229 0.0137
-6.500 -0.2612 0.04712 0.04423 -0.0640 0.7143 0.0139
-6.250 -0.2416 0.04511 0.04213 -0.0648 0.7068 0.0141
-6.000 -0.2213 0.04302 0.03995 -0.0655 0.6993 0.0143
-5.750 -0.2008 0.04067 0.03749 -0.0662 0.6922 0.0146
-5.500 -0.1799 0.03783 0.03450 -0.0669 0.6843 0.0152
-5.250 -0.1623 0.03017 0.02639 -0.0675 0.6782 0.0170
-5.000 -0.1391 0.02868 0.02480 -0.0675 0.6693 0.0172
-4.750 -0.1154 0.02736 0.02335 -0.0673 0.6603 0.0174
-4.500 -0.0915 0.02601 0.02187 -0.0671 0.6495 0.0177
-4.250 -0.0673 0.02447 0.02017 -0.0668 0.6377 0.0181
-3.750 -0.0250 0.01520 0.00981 -0.0642 0.6133 0.0207
-3.500 0.0005 0.01462 0.00907 -0.0638 0.5957 0.0210
-3.250 0.0261 0.01408 0.00837 -0.0634 0.5765 0.0212
-3.000 0.0520 0.01359 0.00773 -0.0630 0.5591 0.0214
-2.750 0.0779 0.01302 0.00699 -0.0626 0.5449 0.0217
-2.500 0.1042 0.01251 0.00634 -0.0622 0.5330 0.0219
-2.250 0.1304 0.01194 0.00563 -0.0618 0.5228 0.0222
-2.000 0.1571 0.01140 0.00498 -0.0615 0.5142 0.0224
-1.750 0.1836 0.01094 0.00440 -0.0611 0.5051 0.0227
-1.500 0.2103 0.01057 0.00395 -0.0607 0.4963 0.0230
-1.250 0.2371 0.01027 0.00358 -0.0604 0.4894 0.0234
-1.000 0.2640 0.00992 0.00317 -0.0601 0.4836 0.0237
-0.750 0.2907 0.00965 0.00286 -0.0597 0.4776 0.0240
-0.500 0.3177 0.00943 0.00261 -0.0594 0.4728 0.0244
-0.250 0.3447 0.00926 0.00241 -0.0591 0.4675 0.0246
0.000 0.3716 0.00917 0.00227 -0.0588 0.4585 0.0249
0.250 0.3986 0.00905 0.00213 -0.0586 0.4493 0.0250
0.500 0.4247 0.00877 0.00181 -0.0581 0.4400 0.0256
0.750 0.4512 0.00868 0.00166 -0.0578 0.4256 0.0260
1.000 0.4774 0.00868 0.00157 -0.0574 0.4003 0.0264
1.250 0.5030 0.00879 0.00153 -0.0570 0.3663 0.0267
1.500 0.5287 0.00893 0.00155 -0.0566 0.3350 0.0274
1.750 0.5543 0.00909 0.00159 -0.0561 0.3057 0.0282
2.000 0.5796 0.00929 0.00165 -0.0557 0.2727 0.0288
2.250 0.6054 0.00944 0.00170 -0.0553 0.2499 0.0295
2.500 0.6315 0.00958 0.00176 -0.0549 0.2332 0.0302
2.750 0.6578 0.00969 0.00183 -0.0546 0.2206 0.0308
3.000 0.6840 0.00982 0.00190 -0.0543 0.2079 0.0316
3.250 0.7102 0.00995 0.00198 -0.0539 0.1956 0.0333
3.500 0.7361 0.01012 0.00209 -0.0536 0.1799 0.0355
4.000 0.7698 0.00952 0.00280 -0.0501 0.0903 0.8182
4.750 0.8736 0.01034 0.00366 -0.0551 0.0326 1.0000
5.000 0.8984 0.01055 0.00386 -0.0545 0.0314 1.0000
5.250 0.9231 0.01077 0.00407 -0.0539 0.0304 1.0000
5.500 0.9477 0.01100 0.00430 -0.0533 0.0295 1.0000
5.750 0.9723 0.01124 0.00455 -0.0527 0.0288 1.0000
6.000 0.9966 0.01151 0.00482 -0.0521 0.0280 1.0000
6.250 1.0210 0.01177 0.00508 -0.0515 0.0275 1.0000
6.500 1.0453 0.01202 0.00535 -0.0509 0.0272 1.0000
6.750 1.0695 0.01229 0.00564 -0.0503 0.0269 1.0000
7.000 1.0934 0.01258 0.00595 -0.0497 0.0265 1.0000
7.250 1.1171 0.01288 0.00628 -0.0491 0.0261 1.0000
7.500 1.1406 0.01320 0.00662 -0.0484 0.0257 1.0000
7.750 1.1638 0.01353 0.00698 -0.0477 0.0251 1.0000
8.000 1.1868 0.01388 0.00735 -0.0470 0.0247 1.0000
8.250 1.2094 0.01426 0.00775 -0.0462 0.0241 1.0000
8.500 1.2314 0.01466 0.00819 -0.0454 0.0235 1.0000
8.750 1.2525 0.01515 0.00870 -0.0445 0.0229 1.0000
9.000 1.2717 0.01578 0.00939 -0.0432 0.0221 1.0000
9.250 1.2942 0.01609 0.00972 -0.0425 0.0219 1.0000
9.500 1.3163 0.01641 0.01008 -0.0418 0.0215 1.0000
9.750 1.3377 0.01677 0.01048 -0.0409 0.0210 1.0000
10.000 1.3584 0.01717 0.01092 -0.0400 0.0204 1.0000
10.250 1.3789 0.01757 0.01135 -0.0390 0.0198 1.0000
10.500 1.3993 0.01795 0.01176 -0.0381 0.0191 1.0000
10.750 1.4189 0.01836 0.01218 -0.0370 0.0185 1.0000
11.000 1.4364 0.01888 0.01273 -0.0357 0.0178 1.0000
11.250 1.4534 0.01939 0.01329 -0.0343 0.0173 1.0000
11.500 1.4704 0.01983 0.01378 -0.0329 0.0168 1.0000
11.750 1.4848 0.02028 0.01427 -0.0310 0.0161 1.0000
12.000 1.4983 0.02077 0.01479 -0.0290 0.0153 1.0000
12.250 1.5117 0.02127 0.01531 -0.0272 0.0145 1.0000
12.500 1.5233 0.02192 0.01598 -0.0252 0.0138 1.0000
12.750 1.5330 0.02270 0.01684 -0.0232 0.0134 1.0000
13.000 1.5424 0.02356 0.01775 -0.0214 0.0127 1.0000
13.250 1.5513 0.02452 0.01876 -0.0197 0.0120 1.0000
13.500 1.5593 0.02563 0.01991 -0.0183 0.0114 1.0000
13.750 1.5660 0.02695 0.02128 -0.0170 0.0106 1.0000
14.000 1.5713 0.02851 0.02292 -0.0160 0.0104 1.0000
14.250 1.5762 0.03024 0.02474 -0.0152 0.0097 1.0000
14.500 1.5800 0.03219 0.02676 -0.0146 0.0093 1.0000
14.750 1.5827 0.03434 0.02899 -0.0142 0.0090 1.0000
15.000 1.5838 0.03676 0.03148 -0.0140 0.0086 1.0000
15.250 1.5829 0.03947 0.03427 -0.0140 0.0082 1.0000
15.500 1.5815 0.04233 0.03723 -0.0141 0.0080 1.0000
15.750 1.5794 0.04539 0.04039 -0.0144 0.0078 1.0000
16.000 1.5757 0.04874 0.04385 -0.0149 0.0077 1.0000
16.250 1.5701 0.05240 0.04761 -0.0157 0.0075 1.0000
16.500 1.5639 0.05624 0.05155 -0.0165 0.0072 1.0000
16.750 1.5562 0.06035 0.05576 -0.0176 0.0071 1.0000
17.000 1.5477 0.06471 0.06023 -0.0188 0.0070 1.0000
17.250 1.5374 0.06944 0.06506 -0.0203 0.0069 1.0000
17.500 1.5268 0.07435 0.07007 -0.0219 0.0067 1.0000
17.750 1.5148 0.07962 0.07544 -0.0238 0.0065 1.0000
18.000 1.5028 0.08501 0.08095 -0.0259 0.0066 1.0000
18.250 1.4891 0.09087 0.08691 -0.0282 0.0064 1.0000
18.500 1.4759 0.09679 0.09294 -0.0308 0.0063 1.0000
18.750 1.4628 0.10281 0.09905 -0.0334 0.0062 1.0000
19.000 1.4493 0.10905 0.10540 -0.0363 0.0061 1.0000
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