GOE 316 (HANSA-BRANDENBURG IV.5) AIRFOIL (goe316-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 316 (HANSA-BRANDENBURG IV.5) AIRFOIL (goe316-il) Reynolds number: 500,000 Max Cl/Cd: 98.8 at α=7.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe316-il-500000-n5.txt Download as CSV file: xf-goe316-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.4107 0.09259 0.09048 -0.0059 0.9439 0.0114
-8.250 -0.4119 0.08912 0.08685 -0.0067 0.8673 0.0120
-8.000 -0.4185 0.08320 0.08078 -0.0109 0.8293 0.0126
-7.750 -0.4107 0.07880 0.07626 -0.0157 0.8062 0.0129
-7.500 -0.3975 0.07590 0.07327 -0.0189 0.7877 0.0130
-7.250 -0.3828 0.07263 0.06991 -0.0226 0.7731 0.0133
-7.000 -0.3667 0.06890 0.06608 -0.0269 0.7610 0.0137
-6.750 -0.3490 0.06469 0.06178 -0.0315 0.7506 0.0142
-6.500 -0.3285 0.05448 0.05133 -0.0417 0.7440 0.0161
-6.250 -0.3073 0.05230 0.04905 -0.0434 0.7344 0.0163
-6.000 -0.2850 0.05004 0.04669 -0.0451 0.7250 0.0167
-5.750 -0.2617 0.04721 0.04371 -0.0471 0.7160 0.0172
-5.500 -0.2369 0.04374 0.04007 -0.0493 0.7073 0.0183
-5.250 -0.2092 0.03584 0.03168 -0.0526 0.7008 0.0202
-5.000 -0.1844 0.03447 0.03019 -0.0532 0.6899 0.0205
-4.750 -0.1592 0.03322 0.02881 -0.0536 0.6778 0.0210
-4.500 -0.1332 0.03149 0.02690 -0.0541 0.6656 0.0219
-4.250 -0.1059 0.02859 0.02370 -0.0546 0.6535 0.0229
-4.000 -0.0760 0.02374 0.01826 -0.0546 0.6430 0.0247
-3.750 -0.0500 0.02167 0.01592 -0.0550 0.6306 0.0253
-3.500 -0.0229 0.02051 0.01456 -0.0552 0.6162 0.0257
-3.250 0.0046 0.01948 0.01332 -0.0553 0.6000 0.0260
-3.000 0.0323 0.01837 0.01198 -0.0553 0.5830 0.0264
-2.750 0.0603 0.01732 0.01069 -0.0554 0.5659 0.0269
-2.500 0.0883 0.01649 0.00963 -0.0554 0.5492 0.0277
-2.250 0.1166 0.01540 0.00827 -0.0553 0.5332 0.0282
-2.000 0.1449 0.01452 0.00714 -0.0553 0.5170 0.0288
-1.750 0.1731 0.01384 0.00626 -0.0553 0.5005 0.0293
-1.500 0.2012 0.01330 0.00555 -0.0553 0.4829 0.0297
-1.250 0.2294 0.01288 0.00497 -0.0553 0.4638 0.0301
-1.000 0.2574 0.01257 0.00451 -0.0553 0.4425 0.0304
-0.750 0.2855 0.01247 0.00427 -0.0553 0.4182 0.0308
-0.500 0.3130 0.01198 0.00364 -0.0553 0.3945 0.0316
-0.250 0.3409 0.01174 0.00331 -0.0553 0.3765 0.0321
0.000 0.3688 0.01160 0.00310 -0.0554 0.3635 0.0327
0.250 0.3970 0.01148 0.00293 -0.0555 0.3542 0.0334
0.500 0.4251 0.01140 0.00280 -0.0555 0.3470 0.0342
0.750 0.4533 0.01131 0.00269 -0.0556 0.3413 0.0350
1.000 0.4815 0.01126 0.00260 -0.0557 0.3362 0.0359
1.250 0.5098 0.01123 0.00254 -0.0558 0.3321 0.0368
1.500 0.5381 0.01120 0.00251 -0.0559 0.3288 0.0380
1.750 0.5664 0.01118 0.00249 -0.0560 0.3253 0.0394
2.000 0.5946 0.01116 0.00246 -0.0561 0.3220 0.0416
2.250 0.6227 0.01120 0.00249 -0.0561 0.3189 0.0441
2.500 0.6508 0.01125 0.00253 -0.0562 0.3164 0.0473
2.750 0.6791 0.01127 0.00257 -0.0563 0.3145 0.0533
3.000 0.7073 0.01129 0.00265 -0.0564 0.3125 0.0696
3.500 0.7589 0.00952 0.00295 -0.0560 0.3087 1.0000
3.750 0.7867 0.00967 0.00308 -0.0560 0.3068 1.0000
4.000 0.8145 0.00984 0.00321 -0.0561 0.3046 1.0000
4.250 0.8419 0.01005 0.00337 -0.0561 0.3012 1.0000
4.500 0.8699 0.01014 0.00349 -0.0561 0.2980 1.0000
4.750 0.8977 0.01027 0.00362 -0.0562 0.2941 1.0000
5.000 0.9253 0.01043 0.00376 -0.0562 0.2897 1.0000
5.250 0.9525 0.01064 0.00395 -0.0562 0.2857 1.0000
5.500 0.9803 0.01076 0.00411 -0.0563 0.2832 1.0000
5.750 1.0079 0.01090 0.00428 -0.0563 0.2805 1.0000
6.000 1.0353 0.01105 0.00447 -0.0564 0.2772 1.0000
6.250 1.0625 0.01123 0.00466 -0.0564 0.2738 1.0000
6.500 1.0895 0.01142 0.00486 -0.0564 0.2698 1.0000
6.750 1.1170 0.01155 0.00506 -0.0564 0.2655 1.0000
7.000 1.1440 0.01172 0.00526 -0.0564 0.2597 1.0000
7.250 1.1710 0.01190 0.00546 -0.0564 0.2513 1.0000
7.500 1.1975 0.01212 0.00566 -0.0564 0.2369 1.0000
7.750 1.2225 0.01255 0.00593 -0.0563 0.2009 1.0000
8.000 1.2422 0.01369 0.00672 -0.0557 0.1464 1.0000
8.250 1.2644 0.01447 0.00738 -0.0552 0.1209 1.0000
8.500 1.2858 0.01532 0.00809 -0.0547 0.0927 1.0000
8.750 1.3047 0.01642 0.00900 -0.0539 0.0606 1.0000
9.000 1.3274 0.01700 0.00960 -0.0535 0.0536 1.0000
9.250 1.3491 0.01766 0.01027 -0.0529 0.0474 1.0000
9.500 1.3718 0.01817 0.01083 -0.0525 0.0427 1.0000
9.750 1.3924 0.01887 0.01154 -0.0518 0.0353 1.0000
10.000 1.4101 0.01981 0.01240 -0.0509 0.0219 1.0000
10.250 1.4274 0.02073 0.01331 -0.0498 0.0167 1.0000
10.500 1.4440 0.02165 0.01427 -0.0487 0.0144 1.0000
10.750 1.4608 0.02247 0.01518 -0.0476 0.0131 1.0000
11.000 1.4758 0.02337 0.01617 -0.0463 0.0121 1.0000
11.250 1.4876 0.02441 0.01729 -0.0447 0.0112 1.0000
11.500 1.4929 0.02565 0.01862 -0.0422 0.0104 1.0000
11.750 1.5003 0.02686 0.01993 -0.0404 0.0100 1.0000
12.000 1.5067 0.02829 0.02147 -0.0389 0.0097 1.0000
12.250 1.5118 0.03002 0.02331 -0.0378 0.0093 1.0000
12.500 1.5157 0.03206 0.02547 -0.0371 0.0090 1.0000
12.750 1.5183 0.03444 0.02796 -0.0368 0.0087 1.0000
13.000 1.5191 0.03716 0.03080 -0.0368 0.0084 1.0000
13.250 1.5175 0.04029 0.03404 -0.0370 0.0082 1.0000
13.500 1.5131 0.04386 0.03773 -0.0374 0.0079 1.0000
13.750 1.5051 0.04803 0.04202 -0.0382 0.0078 1.0000
14.000 1.4946 0.05268 0.04680 -0.0392 0.0076 1.0000
14.250 1.4880 0.05690 0.05115 -0.0402 0.0075 1.0000
14.500 1.4797 0.06140 0.05578 -0.0413 0.0074 1.0000
14.750 1.4706 0.06608 0.06058 -0.0425 0.0073 1.0000
15.000 1.4598 0.07103 0.06565 -0.0438 0.0072 1.0000
15.250 1.4494 0.07608 0.07083 -0.0452 0.0071 1.0000
15.500 1.4392 0.08122 0.07607 -0.0467 0.0070 1.0000
15.750 1.4291 0.08637 0.08133 -0.0483 0.0068 1.0000
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Polar data table (+)
Polar graphs
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