GOE 315 (HANSA-BRANDENBURG III.5) AIRFOIL (goe315-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 315 (HANSA-BRANDENBURG III.5) AIRFOIL (goe315-il) Reynolds number: 500,000 Max Cl/Cd: 82.84 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe315-il-500000-n5.txt Download as CSV file: xf-goe315-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.3667 0.08909 0.08681 -0.0194 1.0000 0.0128
-8.250 -0.3740 0.08423 0.08200 -0.0217 1.0000 0.0138
-8.000 -0.3740 0.08172 0.07952 -0.0221 1.0000 0.0138
-7.750 -0.3714 0.07998 0.07782 -0.0219 1.0000 0.0140
-7.500 -0.3557 0.07642 0.07427 -0.0265 0.9804 0.0143
-7.250 -0.3148 0.07052 0.06828 -0.0390 0.9401 0.0148
-7.000 -0.2680 0.06386 0.06138 -0.0533 0.8756 0.0154
-6.750 -0.2597 0.05657 0.05372 -0.0602 0.8219 0.0169
-6.500 -0.2454 0.05467 0.05168 -0.0606 0.7963 0.0170
-6.250 -0.2295 0.05276 0.04965 -0.0613 0.7781 0.0174
-6.000 -0.2124 0.05021 0.04697 -0.0625 0.7638 0.0178
-5.750 -0.1944 0.04713 0.04374 -0.0639 0.7517 0.0181
-5.500 -0.1751 0.04396 0.04039 -0.0651 0.7409 0.0186
-5.250 -0.1520 0.03716 0.03316 -0.0670 0.7323 0.0205
-5.000 -0.1321 0.03542 0.03130 -0.0672 0.7235 0.0208
-4.750 -0.1103 0.03385 0.02962 -0.0672 0.7143 0.0211
-4.500 -0.0878 0.03214 0.02777 -0.0672 0.7056 0.0215
-4.250 -0.0646 0.03014 0.02559 -0.0671 0.6962 0.0219
-4.000 -0.0404 0.02824 0.02351 -0.0669 0.6873 0.0230
-3.750 -0.0163 0.02573 0.02072 -0.0664 0.6786 0.0234
-3.500 0.0084 0.02321 0.01791 -0.0658 0.6689 0.0238
-3.250 0.0331 0.02071 0.01507 -0.0650 0.6590 0.0243
-3.000 0.0578 0.01822 0.01212 -0.0641 0.6482 0.0253
-2.750 0.0828 0.01685 0.01052 -0.0636 0.6359 0.0255
-2.500 0.1082 0.01591 0.00940 -0.0631 0.6217 0.0258
-2.250 0.1339 0.01511 0.00842 -0.0626 0.6049 0.0261
-2.000 0.1597 0.01444 0.00756 -0.0621 0.5879 0.0263
-1.500 0.2117 0.01335 0.00614 -0.0612 0.5574 0.0270
-1.250 0.2380 0.01294 0.00560 -0.0608 0.5438 0.0277
-1.000 0.2643 0.01244 0.00496 -0.0603 0.5317 0.0279
-0.750 0.2906 0.01200 0.00439 -0.0598 0.5218 0.0281
-0.500 0.3173 0.01159 0.00392 -0.0594 0.5145 0.0285
-0.250 0.3438 0.01128 0.00353 -0.0590 0.5080 0.0289
0.000 0.3704 0.01100 0.00322 -0.0587 0.5014 0.0293
0.250 0.3969 0.01077 0.00295 -0.0583 0.4946 0.0297
0.500 0.4235 0.01059 0.00275 -0.0579 0.4889 0.0302
0.750 0.4502 0.01042 0.00257 -0.0576 0.4828 0.0305
1.000 0.4769 0.01035 0.00247 -0.0572 0.4762 0.0309
1.250 0.5031 0.01009 0.00221 -0.0568 0.4681 0.0321
1.500 0.5294 0.01000 0.00209 -0.0565 0.4576 0.0328
1.750 0.5557 0.00995 0.00200 -0.0561 0.4400 0.0335
2.000 0.5815 0.00999 0.00194 -0.0556 0.4134 0.0344
2.250 0.6074 0.01007 0.00192 -0.0552 0.3872 0.0355
2.500 0.6329 0.01021 0.00194 -0.0548 0.3586 0.0367
2.750 0.6580 0.01043 0.00201 -0.0543 0.3269 0.0381
3.000 0.6829 0.01068 0.00211 -0.0538 0.2961 0.0403
3.250 0.7081 0.01088 0.00224 -0.0533 0.2742 0.0475
4.250 0.8277 0.01003 0.00309 -0.0562 0.2078 1.0000
4.500 0.8521 0.01030 0.00328 -0.0556 0.1942 1.0000
4.750 0.8764 0.01058 0.00348 -0.0550 0.1785 1.0000
5.000 0.8999 0.01095 0.00373 -0.0543 0.1556 1.0000
5.250 0.9178 0.01192 0.00430 -0.0529 0.0852 1.0000
5.500 0.9409 0.01233 0.00465 -0.0521 0.0699 1.0000
5.750 0.9625 0.01291 0.00509 -0.0511 0.0403 1.0000
6.000 0.9860 0.01326 0.00543 -0.0504 0.0371 1.0000
6.250 1.0098 0.01359 0.00576 -0.0497 0.0351 1.0000
6.500 1.0335 0.01391 0.00610 -0.0491 0.0339 1.0000
6.750 1.0570 0.01424 0.00648 -0.0484 0.0330 1.0000
7.000 1.0803 0.01460 0.00687 -0.0477 0.0322 1.0000
7.250 1.1031 0.01499 0.00730 -0.0469 0.0315 1.0000
7.500 1.1255 0.01540 0.00778 -0.0461 0.0309 1.0000
7.750 1.1474 0.01586 0.00828 -0.0453 0.0303 1.0000
8.000 1.1684 0.01639 0.00885 -0.0443 0.0295 1.0000
8.250 1.1881 0.01701 0.00952 -0.0431 0.0286 1.0000
8.500 1.2062 0.01774 0.01032 -0.0418 0.0278 1.0000
8.750 1.2258 0.01830 0.01094 -0.0407 0.0274 1.0000
9.000 1.2456 0.01880 0.01150 -0.0396 0.0269 1.0000
9.250 1.2644 0.01936 0.01213 -0.0384 0.0263 1.0000
9.500 1.2820 0.01998 0.01281 -0.0371 0.0257 1.0000
9.750 1.2986 0.02062 0.01352 -0.0356 0.0249 1.0000
10.000 1.3138 0.02132 0.01427 -0.0340 0.0242 1.0000
10.250 1.3270 0.02205 0.01506 -0.0321 0.0235 1.0000
10.500 1.3349 0.02292 0.01597 -0.0294 0.0228 1.0000
10.750 1.3371 0.02411 0.01723 -0.0262 0.0223 1.0000
11.000 1.3465 0.02497 0.01818 -0.0241 0.0219 1.0000
11.250 1.3579 0.02577 0.01907 -0.0225 0.0214 1.0000
11.500 1.3670 0.02677 0.02017 -0.0208 0.0208 1.0000
11.750 1.3752 0.02792 0.02140 -0.0194 0.0202 1.0000
12.000 1.3834 0.02918 0.02275 -0.0182 0.0195 1.0000
12.250 1.3925 0.03046 0.02410 -0.0173 0.0189 1.0000
12.500 1.4006 0.03193 0.02564 -0.0167 0.0183 1.0000
12.750 1.4059 0.03374 0.02752 -0.0161 0.0179 1.0000
13.000 1.4085 0.03593 0.02979 -0.0156 0.0175 1.0000
13.250 1.4152 0.03778 0.03175 -0.0154 0.0169 1.0000
13.500 1.4186 0.04004 0.03413 -0.0152 0.0164 1.0000
13.750 1.4229 0.04228 0.03647 -0.0152 0.0158 1.0000
14.000 1.4297 0.04429 0.03857 -0.0154 0.0151 1.0000
14.250 1.4327 0.04681 0.04118 -0.0156 0.0147 1.0000
14.500 1.4366 0.04930 0.04373 -0.0160 0.0143 1.0000
14.750 1.4363 0.05236 0.04687 -0.0166 0.0139 1.0000
15.000 1.4332 0.05584 0.05045 -0.0174 0.0136 1.0000
15.250 1.4286 0.05955 0.05428 -0.0182 0.0133 1.0000
15.500 1.4242 0.06332 0.05817 -0.0192 0.0130 1.0000
15.750 1.4199 0.06721 0.06218 -0.0203 0.0126 1.0000
16.000 1.4143 0.07139 0.06646 -0.0216 0.0124 1.0000
16.250 1.4105 0.07545 0.07063 -0.0230 0.0120 1.0000
16.500 1.4061 0.07970 0.07498 -0.0246 0.0117 1.0000
16.750 1.3999 0.08430 0.07967 -0.0264 0.0115 1.0000
17.000 1.3939 0.08900 0.08447 -0.0283 0.0113 1.0000
17.250 1.3864 0.09406 0.08962 -0.0304 0.0110 1.0000
17.500 1.3780 0.09938 0.09502 -0.0327 0.0108 1.0000
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