GOE 324 (HANSA-BRANDENBURG) AIRFOIL (goe324-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 324 (HANSA-BRANDENBURG) AIRFOIL (goe324-il) Reynolds number: 1,000,000 Max Cl/Cd: 123.97 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe324-il-1000000-n5.txt Download as CSV file: xf-goe324-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 324 (HANSA-BRANDENBURG) 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.2739 0.08884 0.08568 -0.0086 0.5549 0.0172
-7.750 -0.2672 0.08562 0.08246 -0.0109 0.5514 0.0173
-7.500 -0.2606 0.08231 0.07914 -0.0135 0.5478 0.0173
-7.250 -0.2540 0.07888 0.07572 -0.0170 0.5449 0.0174
-7.000 -0.2411 0.07543 0.07226 -0.0212 0.5415 0.0176
-6.750 -0.2263 0.07196 0.06877 -0.0255 0.5378 0.0179
-6.500 -0.2103 0.06792 0.06469 -0.0304 0.5340 0.0180
-6.250 -0.1924 0.06380 0.06051 -0.0352 0.5304 0.0181
-6.000 -0.1725 0.05967 0.05633 -0.0398 0.5272 0.0182
-5.750 -0.1511 0.05559 0.05217 -0.0440 0.5234 0.0183
-5.500 -0.1283 0.05154 0.04802 -0.0478 0.5191 0.0184
-5.250 -0.1045 0.04751 0.04387 -0.0511 0.5146 0.0185
-5.000 -0.0795 0.04327 0.03948 -0.0540 0.5106 0.0187
-4.750 -0.0527 0.03443 0.03023 -0.0579 0.5073 0.0194
-4.500 -0.0280 0.03156 0.02719 -0.0588 0.5019 0.0196
-4.000 0.0239 0.02734 0.02265 -0.0598 0.4920 0.0198
-3.750 0.0505 0.02523 0.02036 -0.0601 0.4869 0.0198
-3.500 0.0774 0.02307 0.01799 -0.0603 0.4818 0.0199
-3.250 0.1048 0.02165 0.01641 -0.0604 0.4773 0.0201
-3.000 0.1324 0.02025 0.01485 -0.0605 0.4725 0.0204
-2.750 0.1601 0.01797 0.01227 -0.0604 0.4676 0.0206
-2.500 0.1881 0.01606 0.01006 -0.0603 0.4626 0.0210
-2.250 0.2164 0.01430 0.00801 -0.0602 0.4582 0.0215
-2.000 0.2449 0.01310 0.00657 -0.0601 0.4534 0.0218
-1.750 0.2736 0.01235 0.00566 -0.0601 0.4488 0.0220
-1.500 0.3024 0.01186 0.00505 -0.0601 0.4449 0.0222
-1.250 0.3314 0.01150 0.00462 -0.0601 0.4413 0.0223
-1.000 0.3602 0.01109 0.00415 -0.0602 0.4372 0.0227
-0.750 0.3891 0.01088 0.00392 -0.0603 0.4328 0.0229
-0.500 0.4180 0.01070 0.00371 -0.0604 0.4287 0.0231
-0.250 0.4471 0.01051 0.00351 -0.0605 0.4258 0.0233
0.000 0.4761 0.01035 0.00332 -0.0606 0.4218 0.0236
0.250 0.5050 0.01021 0.00316 -0.0606 0.4171 0.0239
0.500 0.5339 0.01010 0.00301 -0.0607 0.4119 0.0243
0.750 0.5629 0.00998 0.00287 -0.0609 0.4076 0.0246
1.000 0.5919 0.00989 0.00276 -0.0610 0.4022 0.0250
1.250 0.6208 0.00985 0.00269 -0.0611 0.3971 0.0253
1.500 0.6499 0.00979 0.00262 -0.0613 0.3941 0.0256
1.750 0.6790 0.00971 0.00254 -0.0614 0.3910 0.0259
2.000 0.7080 0.00965 0.00248 -0.0616 0.3865 0.0265
2.250 0.7368 0.00967 0.00249 -0.0617 0.3810 0.0272
2.500 0.7658 0.00967 0.00250 -0.0619 0.3771 0.0280
2.750 0.7948 0.00966 0.00250 -0.0621 0.3737 0.0287
3.000 0.8238 0.00968 0.00251 -0.0623 0.3698 0.0293
3.250 0.8525 0.00972 0.00254 -0.0624 0.3651 0.0301
3.500 0.8813 0.00975 0.00258 -0.0626 0.3613 0.0312
3.750 0.9102 0.00978 0.00263 -0.0628 0.3575 0.0325
4.000 0.9389 0.00984 0.00269 -0.0630 0.3530 0.0345
4.250 0.9674 0.00994 0.00278 -0.0632 0.3477 0.0382
4.500 0.9958 0.00960 0.00296 -0.0636 0.3427 0.3295
5.000 1.0489 0.00853 0.00330 -0.0635 0.3268 1.0000
5.500 1.1046 0.00891 0.00358 -0.0637 0.3099 1.0000
5.750 1.1321 0.00915 0.00376 -0.0638 0.3005 1.0000
6.000 1.1595 0.00939 0.00394 -0.0639 0.2901 1.0000
6.250 1.1866 0.00966 0.00415 -0.0640 0.2796 1.0000
6.500 1.2132 0.00997 0.00440 -0.0641 0.2688 1.0000
6.750 1.2397 0.01029 0.00466 -0.0641 0.2579 1.0000
7.000 1.2663 0.01058 0.00490 -0.0642 0.2490 1.0000
7.250 1.2924 0.01092 0.00519 -0.0642 0.2403 1.0000
7.500 1.3186 0.01122 0.00546 -0.0642 0.2325 1.0000
7.750 1.3443 0.01156 0.00577 -0.0642 0.2253 1.0000
8.000 1.3703 0.01186 0.00605 -0.0642 0.2191 1.0000
8.250 1.3955 0.01223 0.00638 -0.0642 0.2129 1.0000
8.500 1.4214 0.01250 0.00666 -0.0642 0.2090 1.0000
8.750 1.4469 0.01280 0.00696 -0.0642 0.2046 1.0000
9.000 1.4716 0.01316 0.00730 -0.0641 0.2000 1.0000
9.250 1.4964 0.01350 0.00765 -0.0640 0.1961 1.0000
9.500 1.5209 0.01384 0.00799 -0.0639 0.1913 1.0000
9.750 1.5446 0.01423 0.00838 -0.0637 0.1867 1.0000
10.000 1.5677 0.01466 0.00880 -0.0635 0.1825 1.0000
10.250 1.5910 0.01503 0.00919 -0.0632 0.1782 1.0000
10.500 1.6111 0.01564 0.00976 -0.0627 0.1699 1.0000
10.750 1.6294 0.01635 0.01042 -0.0621 0.1583 1.0000
11.000 1.6427 0.01736 0.01134 -0.0610 0.1434 1.0000
11.250 1.6437 0.01895 0.01282 -0.0587 0.1220 1.0000
11.500 1.6333 0.02207 0.01583 -0.0575 0.0975 1.0000
12.000 1.6445 0.02632 0.02010 -0.0574 0.0865 1.0000
12.250 1.6511 0.02832 0.02214 -0.0572 0.0842 1.0000
12.500 1.6568 0.03038 0.02425 -0.0570 0.0824 1.0000
12.750 1.6614 0.03254 0.02645 -0.0567 0.0805 1.0000
13.000 1.6656 0.03471 0.02867 -0.0564 0.0788 1.0000
13.250 1.6715 0.03669 0.03072 -0.0561 0.0782 1.0000
13.500 1.6761 0.03880 0.03289 -0.0558 0.0775 1.0000
13.750 1.6788 0.04110 0.03526 -0.0554 0.0767 1.0000
14.000 1.6803 0.04354 0.03776 -0.0551 0.0757 1.0000
14.250 1.6804 0.04610 0.04038 -0.0548 0.0746 1.0000
14.500 1.6792 0.04886 0.04320 -0.0545 0.0734 1.0000
14.750 1.6767 0.05188 0.04628 -0.0543 0.0720 1.0000
15.000 1.6747 0.05492 0.04937 -0.0543 0.0706 1.0000
15.250 1.6736 0.05791 0.05242 -0.0543 0.0694 1.0000
15.500 1.6750 0.06064 0.05523 -0.0543 0.0688 1.0000
15.750 1.6766 0.06336 0.05803 -0.0544 0.0680 1.0000
16.000 1.6773 0.06622 0.06095 -0.0545 0.0668 1.0000
16.250 1.6754 0.06945 0.06424 -0.0548 0.0650 1.0000
16.500 1.6718 0.07286 0.06770 -0.0550 0.0628 1.0000
16.750 1.6661 0.07660 0.07148 -0.0554 0.0607 1.0000
17.000 1.6640 0.07993 0.07487 -0.0557 0.0584 1.0000
17.250 1.6550 0.08414 0.07909 -0.0563 0.0521 1.0000
17.500 1.6339 0.09001 0.08491 -0.0572 0.0416 1.0000
17.750 1.6139 0.09590 0.09081 -0.0582 0.0351 1.0000
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Polar data table (+)
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