GOE 316 (HANSA-BRANDENBURG IV.5) AIRFOIL (goe316-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| 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: 123.41 at α=7.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe316-il-1000000.txt Download as CSV file: xf-goe316-il-1000000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.4221 0.09555 0.09408 -0.0017 1.0000 0.0162
-8.250 -0.4204 0.09127 0.08982 -0.0055 1.0000 0.0163
-8.000 -0.4159 0.08685 0.08541 -0.0101 0.9780 0.0163
-7.750 -0.4087 0.08235 0.08077 -0.0147 0.9038 0.0163
-7.500 -0.4059 0.07768 0.07588 -0.0169 0.8475 0.0166
-7.250 -0.3940 0.07537 0.07343 -0.0178 0.8168 0.0168
-7.000 -0.3794 0.07264 0.07060 -0.0203 0.7965 0.0171
-6.750 -0.3630 0.06942 0.06729 -0.0237 0.7814 0.0175
-6.500 -0.3447 0.06575 0.06353 -0.0277 0.7695 0.0183
-5.750 -0.2751 0.04773 0.04499 -0.0440 0.7411 0.0204
-5.500 -0.2543 0.04599 0.04319 -0.0447 0.7306 0.0208
-5.250 -0.2315 0.04387 0.04097 -0.0458 0.7211 0.0212
-5.000 -0.2069 0.04138 0.03835 -0.0471 0.7118 0.0221
-4.750 -0.1714 0.03697 0.03357 -0.0487 0.7046 0.0243
-4.500 -0.1495 0.03100 0.02729 -0.0501 0.6972 0.0249
-4.250 -0.1250 0.02950 0.02570 -0.0506 0.6884 0.0252
-4.000 -0.0996 0.02816 0.02425 -0.0509 0.6787 0.0256
-3.750 -0.0733 0.02676 0.02273 -0.0513 0.6686 0.0263
-3.500 -0.0456 0.02515 0.02095 -0.0514 0.6581 0.0280
-2.000 0.1221 0.00554 0.00018 -0.0497 0.5458 0.0361
-1.000 0.2379 0.01181 0.00532 -0.0514 0.4903 0.0331
-0.750 0.2663 0.01123 0.00458 -0.0514 0.4686 0.0333
-0.500 0.2946 0.01074 0.00394 -0.0514 0.4417 0.0335
-0.250 0.3227 0.01049 0.00351 -0.0514 0.4073 0.0339
0.000 0.3507 0.01033 0.00320 -0.0514 0.3794 0.0345
0.250 0.3789 0.01017 0.00295 -0.0515 0.3630 0.0349
0.500 0.4072 0.01002 0.00274 -0.0515 0.3529 0.0353
0.750 0.4355 0.00992 0.00258 -0.0516 0.3450 0.0358
1.000 0.4641 0.00990 0.00255 -0.0517 0.3398 0.0363
1.250 0.4925 0.00955 0.00216 -0.0519 0.3353 0.0383
1.500 0.5210 0.00952 0.00211 -0.0520 0.3307 0.0397
1.750 0.5495 0.00951 0.00209 -0.0521 0.3268 0.0412
2.000 0.5781 0.00948 0.00207 -0.0522 0.3243 0.0429
2.250 0.6066 0.00949 0.00208 -0.0523 0.3217 0.0445
2.500 0.6352 0.00946 0.00204 -0.0524 0.3191 0.0493
2.750 0.6636 0.00951 0.00208 -0.0525 0.3165 0.0546
3.000 0.6871 0.00753 0.00229 -0.0522 0.3138 1.0000
3.250 0.7154 0.00765 0.00237 -0.0523 0.3118 1.0000
3.500 0.7438 0.00774 0.00245 -0.0524 0.3104 1.0000
3.750 0.7722 0.00783 0.00253 -0.0525 0.3080 1.0000
4.000 0.8005 0.00793 0.00259 -0.0526 0.3034 1.0000
4.250 0.8283 0.00811 0.00272 -0.0527 0.2983 1.0000
4.500 0.8564 0.00823 0.00284 -0.0528 0.2962 1.0000
4.750 0.8847 0.00832 0.00294 -0.0529 0.2946 1.0000
5.000 0.9129 0.00842 0.00305 -0.0530 0.2926 1.0000
5.250 0.9410 0.00852 0.00316 -0.0531 0.2900 1.0000
5.500 0.9689 0.00865 0.00328 -0.0532 0.2870 1.0000
5.750 0.9965 0.00883 0.00345 -0.0533 0.2832 1.0000
6.000 1.0245 0.00894 0.00358 -0.0534 0.2806 1.0000
6.250 1.0526 0.00901 0.00370 -0.0535 0.2776 1.0000
6.500 1.0805 0.00911 0.00379 -0.0536 0.2721 1.0000
6.750 1.1080 0.00927 0.00394 -0.0537 0.2660 1.0000
7.000 1.1360 0.00935 0.00406 -0.0538 0.2607 1.0000
7.250 1.1633 0.00952 0.00421 -0.0539 0.2540 1.0000
7.500 1.1909 0.00965 0.00435 -0.0540 0.2438 1.0000
7.750 1.2174 0.00992 0.00454 -0.0540 0.2246 1.0000
8.000 1.2396 0.01085 0.00512 -0.0536 0.1638 1.0000
8.250 1.2620 0.01171 0.00577 -0.0532 0.1296 1.0000
8.500 1.2835 0.01266 0.00648 -0.0527 0.0901 1.0000
8.750 1.3044 0.01365 0.00726 -0.0521 0.0578 1.0000
9.000 1.3284 0.01416 0.00777 -0.0518 0.0517 1.0000
9.250 1.3527 0.01460 0.00823 -0.0515 0.0465 1.0000
9.500 1.3758 0.01516 0.00877 -0.0511 0.0391 1.0000
9.750 1.3975 0.01586 0.00939 -0.0506 0.0263 1.0000
10.000 1.4180 0.01666 0.01014 -0.0499 0.0186 1.0000
10.250 1.4387 0.01739 0.01087 -0.0492 0.0162 1.0000
10.500 1.4593 0.01808 0.01162 -0.0485 0.0148 1.0000
10.750 1.4797 0.01873 0.01233 -0.0477 0.0140 1.0000
11.000 1.4985 0.01949 0.01315 -0.0468 0.0131 1.0000
11.250 1.5140 0.02051 0.01424 -0.0455 0.0122 1.0000
11.500 1.5287 0.02149 0.01531 -0.0442 0.0117 1.0000
11.750 1.5450 0.02225 0.01614 -0.0430 0.0113 1.0000
12.000 1.5583 0.02313 0.01709 -0.0415 0.0108 1.0000
12.250 1.5661 0.02413 0.01816 -0.0392 0.0104 1.0000
12.500 1.5719 0.02536 0.01948 -0.0372 0.0101 1.0000
12.750 1.5757 0.02694 0.02115 -0.0355 0.0098 1.0000
13.000 1.5761 0.02910 0.02340 -0.0343 0.0095 1.0000
13.250 1.5711 0.03217 0.02660 -0.0338 0.0093 1.0000
13.500 1.5594 0.03635 0.03094 -0.0339 0.0090 1.0000
13.750 1.5617 0.03906 0.03374 -0.0342 0.0089 1.0000
14.000 1.5612 0.04217 0.03696 -0.0346 0.0088 1.0000
14.250 1.5585 0.04564 0.04054 -0.0352 0.0087 1.0000
14.500 1.5535 0.04950 0.04451 -0.0360 0.0086 1.0000
14.750 1.5461 0.05375 0.04888 -0.0369 0.0085 1.0000
15.000 1.5372 0.05829 0.05354 -0.0380 0.0084 1.0000
15.250 1.5269 0.06304 0.05839 -0.0392 0.0083 1.0000
15.500 1.5153 0.06804 0.06350 -0.0405 0.0082 1.0000
15.750 1.5038 0.07314 0.06870 -0.0419 0.0081 1.0000
16.000 1.4926 0.07833 0.07400 -0.0434 0.0081 1.0000
16.250 1.4819 0.08352 0.07928 -0.0450 0.0080 1.0000
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Polar data table (+)
Polar graphs
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