GOE 321 (HANSA-BRANDENBURG III.1) AIRFOIL (goe321-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 321 (HANSA-BRANDENBURG III.1) AIRFOIL (goe321-il) Reynolds number: 1,000,000 Max Cl/Cd: 120.94 at α=3.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe321-il-1000000.txt Download as CSV file: xf-goe321-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 321 (HANSA-BRANDENBURG III.1) 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
------ -------- --------- --------- -------- -------- --------
-9.500 -0.2359 0.09658 0.09412 -0.0194 0.7114 0.0201
-9.250 -0.2315 0.09331 0.09084 -0.0204 0.7073 0.0207
-9.000 -0.3343 0.09980 0.09729 -0.0116 0.7207 0.0198
-8.750 -0.3272 0.09686 0.09433 -0.0131 0.7154 0.0203
-8.500 -0.3205 0.09377 0.09121 -0.0149 0.7104 0.0210
-8.250 -0.3247 0.08779 0.08524 -0.0223 0.7066 0.0222
-8.000 -0.3225 0.08339 0.08085 -0.0268 0.7020 0.0222
-7.750 -0.3125 0.07857 0.07600 -0.0327 0.6972 0.0223
-7.500 -0.3063 0.07386 0.07124 -0.0358 0.6924 0.0225
-7.250 -0.2923 0.07120 0.06859 -0.0374 0.6876 0.0227
-7.000 -0.2769 0.06844 0.06579 -0.0397 0.6820 0.0228
-6.750 -0.2603 0.06564 0.06293 -0.0424 0.6763 0.0231
-6.500 -0.2421 0.06262 0.05988 -0.0454 0.6708 0.0235
-6.250 -0.2226 0.05924 0.05644 -0.0488 0.6645 0.0242
-5.750 -0.1530 0.03098 0.02796 -0.0597 0.6395 0.0265
-5.500 -0.1341 0.02863 0.02553 -0.0604 0.6303 0.0267
-5.250 -0.1136 0.02671 0.02354 -0.0610 0.6215 0.0270
-5.000 -0.0922 0.02459 0.02132 -0.0618 0.6119 0.0274
-4.750 -0.0698 0.02229 0.01891 -0.0627 0.6033 0.0280
-4.500 -0.0463 0.01961 0.01605 -0.0637 0.5953 0.0291
-4.250 -0.0225 0.01306 0.00893 -0.0650 0.5911 0.0311
-4.000 0.0017 0.01194 0.00771 -0.0653 0.5835 0.0314
-3.750 0.0265 0.01102 0.00669 -0.0654 0.5761 0.0317
-3.500 0.0519 0.01016 0.00572 -0.0656 0.5684 0.0323
-3.250 0.0779 0.00930 0.00471 -0.0657 0.5615 0.0335
-2.750 0.1339 0.01410 0.00807 -0.0671 0.5571 0.0302
-2.500 0.1624 0.01328 0.00707 -0.0671 0.5513 0.0304
-2.250 0.1907 0.01231 0.00587 -0.0671 0.5457 0.0309
-2.000 0.2192 0.01143 0.00490 -0.0671 0.5407 0.0312
-1.750 0.2476 0.01095 0.00436 -0.0672 0.5347 0.0316
-1.500 0.2762 0.01066 0.00401 -0.0672 0.5295 0.0320
-1.250 0.3051 0.01035 0.00369 -0.0673 0.5260 0.0324
-1.000 0.3339 0.01008 0.00341 -0.0673 0.5221 0.0329
-0.750 0.3627 0.00986 0.00316 -0.0674 0.5182 0.0334
-0.500 0.3913 0.00968 0.00294 -0.0675 0.5141 0.0340
-0.250 0.4203 0.00951 0.00276 -0.0676 0.5107 0.0348
0.000 0.4494 0.00940 0.00265 -0.0677 0.5069 0.0356
0.250 0.4782 0.00916 0.00238 -0.0678 0.5031 0.0365
0.500 0.5070 0.00903 0.00224 -0.0679 0.4987 0.0377
0.750 0.5360 0.00895 0.00216 -0.0681 0.4944 0.0390
1.000 0.5652 0.00887 0.00209 -0.0682 0.4897 0.0404
1.250 0.5942 0.00884 0.00204 -0.0684 0.4841 0.0418
1.500 0.6231 0.00877 0.00196 -0.0685 0.4792 0.0455
1.750 0.6523 0.00871 0.00193 -0.0687 0.4748 0.0503
2.000 0.6813 0.00865 0.00192 -0.0689 0.4693 0.0636
2.250 0.7101 0.00861 0.00194 -0.0691 0.4634 0.0975
2.500 0.7351 0.00659 0.00211 -0.0690 0.4578 1.0000
2.750 0.7637 0.00668 0.00213 -0.0691 0.4498 1.0000
3.000 0.7923 0.00676 0.00216 -0.0692 0.4411 1.0000
3.250 0.8208 0.00687 0.00220 -0.0693 0.4294 1.0000
3.500 0.8490 0.00702 0.00226 -0.0694 0.4123 1.0000
3.750 0.8765 0.00727 0.00236 -0.0694 0.3847 1.0000
4.000 0.9033 0.00762 0.00254 -0.0694 0.3528 1.0000
4.250 0.9301 0.00797 0.00274 -0.0694 0.3280 1.0000
4.500 0.9570 0.00830 0.00295 -0.0694 0.3090 1.0000
4.750 0.9840 0.00858 0.00314 -0.0694 0.2926 1.0000
5.000 1.0110 0.00887 0.00334 -0.0694 0.2760 1.0000
5.250 1.0377 0.00918 0.00356 -0.0694 0.2574 1.0000
5.500 1.0638 0.00956 0.00380 -0.0693 0.2352 1.0000
5.750 1.0895 0.00996 0.00409 -0.0692 0.2144 1.0000
6.000 1.1154 0.01032 0.00435 -0.0690 0.2002 1.0000
6.250 1.1416 0.01062 0.00460 -0.0690 0.1922 1.0000
6.500 1.1678 0.01092 0.00487 -0.0689 0.1860 1.0000
6.750 1.1944 0.01116 0.00510 -0.0688 0.1827 1.0000
7.000 1.2205 0.01143 0.00535 -0.0687 0.1797 1.0000
7.250 1.2463 0.01172 0.00564 -0.0686 0.1767 1.0000
7.500 1.2716 0.01205 0.00596 -0.0684 0.1736 1.0000
7.750 1.2976 0.01230 0.00623 -0.0683 0.1717 1.0000
8.000 1.3237 0.01251 0.00647 -0.0682 0.1700 1.0000
8.250 1.3493 0.01276 0.00674 -0.0681 0.1683 1.0000
8.500 1.3745 0.01304 0.00703 -0.0679 0.1661 1.0000
8.750 1.3991 0.01335 0.00736 -0.0676 0.1641 1.0000
9.000 1.4230 0.01372 0.00773 -0.0673 0.1618 1.0000
9.250 1.4458 0.01415 0.00817 -0.0668 0.1591 1.0000
9.500 1.4700 0.01444 0.00850 -0.0665 0.1577 1.0000
9.750 1.4951 0.01465 0.00875 -0.0663 0.1563 1.0000
10.000 1.5196 0.01489 0.00903 -0.0660 0.1543 1.0000
10.250 1.5433 0.01517 0.00934 -0.0657 0.1517 1.0000
10.500 1.5653 0.01557 0.00973 -0.0651 0.1480 1.0000
10.750 1.5850 0.01609 0.01027 -0.0643 0.1441 1.0000
11.000 1.6103 0.01621 0.01044 -0.0641 0.1416 1.0000
11.250 1.6327 0.01651 0.01074 -0.0636 0.1365 1.0000
11.500 1.6519 0.01700 0.01122 -0.0627 0.1303 1.0000
11.750 1.6710 0.01745 0.01163 -0.0618 0.1206 1.0000
12.000 1.6686 0.01892 0.01284 -0.0580 0.0875 1.0000
12.250 1.6537 0.02141 0.01517 -0.0535 0.0603 1.0000
12.500 1.6397 0.02442 0.01804 -0.0504 0.0371 1.0000
12.750 1.6336 0.02725 0.02083 -0.0489 0.0244 1.0000
13.000 1.6361 0.02950 0.02311 -0.0481 0.0205 1.0000
13.250 1.6410 0.03158 0.02524 -0.0475 0.0188 1.0000
13.500 1.6431 0.03395 0.02767 -0.0469 0.0174 1.0000
13.750 1.6481 0.03605 0.02984 -0.0465 0.0167 1.0000
14.000 1.6513 0.03833 0.03219 -0.0460 0.0160 1.0000
14.250 1.6522 0.04086 0.03480 -0.0456 0.0154 1.0000
14.500 1.6505 0.04371 0.03772 -0.0452 0.0148 1.0000
14.750 1.6452 0.04700 0.04111 -0.0448 0.0143 1.0000
15.000 1.6438 0.04993 0.04412 -0.0446 0.0140 1.0000
15.250 1.6426 0.05292 0.04720 -0.0446 0.0137 1.0000
15.500 1.6399 0.05615 0.05052 -0.0447 0.0134 1.0000
15.750 1.6365 0.05959 0.05406 -0.0449 0.0132 1.0000
16.000 1.6320 0.06326 0.05782 -0.0453 0.0129 1.0000
16.250 1.6260 0.06717 0.06182 -0.0457 0.0127 1.0000
16.500 1.6182 0.07138 0.06613 -0.0463 0.0124 1.0000
16.750 1.6085 0.07594 0.07079 -0.0471 0.0122 1.0000
17.000 1.5967 0.08087 0.07583 -0.0481 0.0120 1.0000
17.250 1.5826 0.08622 0.08128 -0.0492 0.0119 1.0000
17.500 1.5663 0.09205 0.08723 -0.0506 0.0117 1.0000
17.750 1.5477 0.09838 0.09369 -0.0524 0.0116 1.0000
18.000 1.5275 0.10509 0.10053 -0.0544 0.0115 1.0000
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Polar data table (+)
Polar graphs
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