GOE 314 (HANSA-BRANDENBURG) AIRFOIL (goe314-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 314 (HANSA-BRANDENBURG) AIRFOIL (goe314-il) Reynolds number: 500,000 Max Cl/Cd: 98.32 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe314-il-500000.txt Download as CSV file: xf-goe314-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 314 (HANSA-BRANDENBURG) 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.750 -0.3154 0.08714 0.08495 -0.0223 1.0000 0.0248
-7.500 -0.3176 0.08523 0.08309 -0.0213 1.0000 0.0252
-7.250 -0.3244 0.08347 0.08137 -0.0198 1.0000 0.0254
-7.000 -0.2304 0.06506 0.06309 -0.0381 0.9880 0.0282
-6.750 -0.2090 0.05906 0.05702 -0.0480 0.9800 0.0283
-6.500 -0.1951 0.05377 0.05173 -0.0493 0.9732 0.0286
-6.250 -0.1765 0.05025 0.04822 -0.0503 0.9646 0.0290
-6.000 -0.1515 0.04632 0.04425 -0.0545 0.9568 0.0295
-5.750 -0.1255 0.04221 0.04009 -0.0596 0.9437 0.0302
-5.500 -0.0973 0.03798 0.03576 -0.0651 0.9283 0.0314
-5.250 -0.1225 0.05143 0.04903 -0.0656 0.9478 0.0312
-5.000 -0.0656 0.04658 0.04380 -0.0759 0.9348 0.0336
-4.750 -0.0356 0.04146 0.03854 -0.0802 0.9198 0.0341
-4.500 -0.0080 0.03891 0.03592 -0.0824 0.9015 0.0345
-4.250 0.0171 0.03690 0.03377 -0.0835 0.8813 0.0350
-4.000 0.0401 0.03505 0.03178 -0.0838 0.8628 0.0357
-3.750 0.0631 0.03321 0.02976 -0.0839 0.8457 0.0368
-3.250 0.1200 0.03008 0.02591 -0.0829 0.8148 0.0402
-3.000 0.1366 0.02632 0.02202 -0.0827 0.8004 0.0410
-2.750 0.1583 0.02497 0.02059 -0.0822 0.7852 0.0416
-2.500 0.1810 0.02380 0.01930 -0.0816 0.7689 0.0424
-2.250 0.2046 0.02263 0.01797 -0.0809 0.7520 0.0437
-2.000 0.2300 0.02153 0.01663 -0.0800 0.7336 0.0464
-1.750 0.2587 0.02171 0.01639 -0.0786 0.7124 0.0482
-1.500 0.2786 0.01856 0.01305 -0.0779 0.6902 0.0496
-1.250 0.3018 0.01776 0.01212 -0.0772 0.6620 0.0507
-1.000 0.3254 0.01716 0.01133 -0.0764 0.6317 0.0526
-0.750 0.3501 0.01673 0.01062 -0.0753 0.6001 0.0558
-0.500 0.3768 0.01754 0.01107 -0.0741 0.5696 0.0580
0.000 0.4230 0.01471 0.00791 -0.0728 0.5223 0.0638
0.250 0.4506 0.01315 0.00584 -0.0712 0.5040 0.0476
0.500 0.4763 0.01287 0.00536 -0.0705 0.4867 0.0485
1.000 0.5279 0.01196 0.00425 -0.0693 0.4607 0.0483
1.250 0.5528 0.01139 0.00360 -0.0686 0.4498 0.0490
1.500 0.5782 0.01103 0.00324 -0.0680 0.4397 0.0504
1.750 0.6037 0.01090 0.00309 -0.0674 0.4307 0.0520
2.000 0.6295 0.01085 0.00302 -0.0669 0.4219 0.0550
2.250 0.6553 0.01079 0.00294 -0.0664 0.4135 0.0571
2.500 0.6805 0.01069 0.00279 -0.0658 0.4041 0.0595
2.750 0.7063 0.01061 0.00272 -0.0653 0.3945 0.0639
3.000 0.7319 0.01067 0.00273 -0.0647 0.3859 0.0693
3.250 0.7580 0.01063 0.00274 -0.0643 0.3776 0.0793
3.500 0.7835 0.01064 0.00279 -0.0637 0.3694 0.1163
3.750 0.8394 0.00911 0.00304 -0.0704 0.3570 1.0000
4.000 0.8640 0.00923 0.00313 -0.0696 0.3480 1.0000
4.250 0.8878 0.00942 0.00323 -0.0688 0.3387 1.0000
4.500 0.9121 0.00956 0.00334 -0.0680 0.3286 1.0000
4.750 0.9363 0.00973 0.00347 -0.0672 0.3196 1.0000
5.000 0.9600 0.00993 0.00362 -0.0664 0.3100 1.0000
5.250 0.9844 0.01009 0.00376 -0.0657 0.3003 1.0000
5.500 1.0083 0.01030 0.00393 -0.0649 0.2903 1.0000
5.750 1.0318 0.01053 0.00412 -0.0640 0.2795 1.0000
6.000 1.0559 0.01074 0.00430 -0.0633 0.2687 1.0000
6.250 1.0795 0.01098 0.00451 -0.0625 0.2579 1.0000
6.500 1.1027 0.01125 0.00474 -0.0617 0.2471 1.0000
6.750 1.1259 0.01153 0.00499 -0.0609 0.2359 1.0000
7.000 1.1492 0.01181 0.00524 -0.0601 0.2248 1.0000
7.250 1.1720 0.01212 0.00552 -0.0592 0.2132 1.0000
7.500 1.1944 0.01247 0.00582 -0.0583 0.2008 1.0000
7.750 1.2165 0.01284 0.00614 -0.0574 0.1885 1.0000
8.000 1.2384 0.01322 0.00647 -0.0565 0.1776 1.0000
8.250 1.2608 0.01356 0.00681 -0.0556 0.1675 1.0000
8.500 1.2821 0.01398 0.00720 -0.0546 0.1540 1.0000
8.750 1.3020 0.01451 0.00764 -0.0534 0.1354 1.0000
9.000 1.3118 0.01588 0.00860 -0.0510 0.0745 1.0000
9.250 1.3289 0.01660 0.00930 -0.0494 0.0662 1.0000
9.500 1.3475 0.01716 0.00991 -0.0480 0.0623 1.0000
9.750 1.3641 0.01784 0.01063 -0.0464 0.0586 1.0000
10.000 1.3788 0.01861 0.01145 -0.0445 0.0546 1.0000
10.250 1.3974 0.01906 0.01198 -0.0431 0.0524 1.0000
10.500 1.4137 0.01963 0.01262 -0.0415 0.0489 1.0000
10.750 1.4223 0.02052 0.01356 -0.0387 0.0446 1.0000
11.000 1.4403 0.02083 0.01392 -0.0373 0.0393 1.0000
11.250 1.4518 0.02151 0.01456 -0.0349 0.0318 1.0000
11.500 1.4603 0.02236 0.01537 -0.0323 0.0259 1.0000
11.750 1.4664 0.02338 0.01640 -0.0296 0.0229 1.0000
12.000 1.4722 0.02445 0.01754 -0.0270 0.0212 1.0000
12.250 1.4745 0.02580 0.01894 -0.0244 0.0199 1.0000
12.500 1.4745 0.02741 0.02065 -0.0219 0.0190 1.0000
12.750 1.4765 0.02902 0.02238 -0.0200 0.0184 1.0000
13.000 1.4770 0.03089 0.02436 -0.0183 0.0179 1.0000
13.250 1.4748 0.03317 0.02676 -0.0170 0.0173 1.0000
13.500 1.4723 0.03567 0.02937 -0.0161 0.0170 1.0000
13.750 1.4673 0.03865 0.03247 -0.0155 0.0167 1.0000
14.000 1.4591 0.04224 0.03617 -0.0155 0.0163 1.0000
14.250 1.4462 0.04671 0.04076 -0.0162 0.0159 1.0000
14.500 1.4356 0.05120 0.04539 -0.0172 0.0158 1.0000
14.750 1.4191 0.05671 0.05102 -0.0187 0.0155 1.0000
15.000 1.4059 0.06186 0.05629 -0.0203 0.0154 1.0000
15.250 1.3952 0.06678 0.06133 -0.0218 0.0152 1.0000
15.500 1.3845 0.07174 0.06640 -0.0233 0.0152 1.0000
15.750 1.3762 0.07645 0.07122 -0.0249 0.0150 1.0000
16.000 1.3690 0.08111 0.07599 -0.0265 0.0148 1.0000
16.250 1.3600 0.08605 0.08103 -0.0282 0.0146 1.0000
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Polar data table (+)
Polar graphs
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