GOE 321 (HANSA-BRANDENBURG III.1) AIRFOIL (goe321-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| 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: 104.55 at α=8.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe321-il-1000000-n5.txt Download as CSV file: xf-goe321-il-1000000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.3664 0.10359 0.10083 -0.0101 0.6771 0.0137
-9.500 -0.3623 0.09986 0.09711 -0.0120 0.6731 0.0141
-9.250 -0.3733 0.09228 0.08952 -0.0163 0.6701 0.0152
-9.000 -0.3652 0.08969 0.08692 -0.0179 0.6649 0.0153
-8.750 -0.3568 0.08713 0.08435 -0.0196 0.6601 0.0154
-8.500 -0.3484 0.08452 0.08174 -0.0214 0.6547 0.0155
-8.250 -0.3409 0.08171 0.07892 -0.0236 0.6489 0.0157
-8.000 -0.3349 0.07852 0.07572 -0.0267 0.6437 0.0159
-7.750 -0.3242 0.07452 0.07170 -0.0316 0.6376 0.0162
-7.500 -0.3118 0.07009 0.06723 -0.0371 0.6310 0.0165
-7.250 -0.3063 0.05735 0.05433 -0.0511 0.6277 0.0181
-7.000 -0.2870 0.05399 0.05089 -0.0542 0.6194 0.0183
-6.750 -0.2663 0.05091 0.04770 -0.0568 0.6111 0.0184
-6.500 -0.2777 0.01890 0.01390 -0.0681 0.6135 0.0216
-6.250 -0.2511 0.01797 0.01282 -0.0681 0.6033 0.0218
-6.000 -0.2237 0.01742 0.01215 -0.0682 0.5931 0.0220
-5.500 -0.1689 0.01602 0.01045 -0.0683 0.5741 0.0224
-5.000 -0.1136 0.01456 0.00867 -0.0683 0.5592 0.0228
-4.750 -0.0857 0.01392 0.00787 -0.0684 0.5523 0.0231
-4.500 -0.0576 0.01333 0.00714 -0.0684 0.5469 0.0233
-4.250 -0.0292 0.01279 0.00649 -0.0684 0.5421 0.0236
-4.000 -0.0008 0.01233 0.00592 -0.0685 0.5377 0.0238
-3.500 0.0562 0.01155 0.00496 -0.0686 0.5279 0.0243
-3.250 0.0848 0.01124 0.00456 -0.0686 0.5215 0.0245
-2.750 0.1422 0.01071 0.00391 -0.0687 0.5125 0.0249
-2.500 0.1711 0.01051 0.00366 -0.0688 0.5080 0.0251
-2.250 0.1998 0.01030 0.00340 -0.0688 0.5031 0.0254
-2.000 0.2284 0.01002 0.00307 -0.0689 0.4985 0.0259
-1.750 0.2573 0.00983 0.00287 -0.0690 0.4947 0.0263
-1.500 0.2862 0.00968 0.00271 -0.0691 0.4897 0.0266
-1.250 0.3151 0.00957 0.00257 -0.0692 0.4850 0.0270
-1.000 0.3441 0.00947 0.00245 -0.0694 0.4810 0.0274
-0.750 0.3731 0.00935 0.00233 -0.0695 0.4774 0.0278
-0.500 0.4022 0.00925 0.00222 -0.0696 0.4730 0.0283
-0.250 0.4311 0.00918 0.00213 -0.0697 0.4678 0.0287
0.000 0.4601 0.00912 0.00205 -0.0699 0.4631 0.0292
0.250 0.4892 0.00906 0.00198 -0.0700 0.4585 0.0296
0.500 0.5182 0.00899 0.00190 -0.0702 0.4523 0.0303
0.750 0.5472 0.00895 0.00185 -0.0704 0.4459 0.0315
1.000 0.5761 0.00894 0.00183 -0.0705 0.4370 0.0328
1.250 0.6049 0.00896 0.00181 -0.0707 0.4243 0.0340
1.500 0.6333 0.00906 0.00182 -0.0708 0.4023 0.0350
1.750 0.6609 0.00927 0.00189 -0.0708 0.3669 0.0378
2.250 0.7163 0.00968 0.00212 -0.0710 0.3186 0.0498
2.500 0.7443 0.00982 0.00224 -0.0711 0.3043 0.0646
2.750 0.7722 0.00995 0.00236 -0.0712 0.2916 0.0845
3.000 0.8001 0.01000 0.00249 -0.0714 0.2791 0.1500
3.250 0.8234 0.00834 0.00276 -0.0709 0.2679 1.0000
3.500 0.8510 0.00857 0.00289 -0.0710 0.2544 1.0000
3.750 0.8783 0.00882 0.00304 -0.0710 0.2389 1.0000
4.000 0.9053 0.00911 0.00321 -0.0710 0.2211 1.0000
4.250 0.9320 0.00943 0.00341 -0.0710 0.2036 1.0000
4.500 0.9589 0.00971 0.00361 -0.0709 0.1910 1.0000
4.750 0.9861 0.00995 0.00378 -0.0709 0.1833 1.0000
5.000 1.0132 0.01017 0.00397 -0.0709 0.1778 1.0000
5.250 1.0402 0.01040 0.00416 -0.0709 0.1727 1.0000
5.500 1.0675 0.01058 0.00433 -0.0710 0.1703 1.0000
5.750 1.0947 0.01078 0.00451 -0.0710 0.1681 1.0000
6.000 1.1216 0.01098 0.00470 -0.0710 0.1660 1.0000
6.250 1.1484 0.01119 0.00490 -0.0709 0.1640 1.0000
6.500 1.1750 0.01142 0.00512 -0.0709 0.1620 1.0000
6.750 1.2015 0.01165 0.00535 -0.0708 0.1600 1.0000
7.000 1.2277 0.01189 0.00559 -0.0708 0.1581 1.0000
7.250 1.2539 0.01212 0.00583 -0.0707 0.1569 1.0000
7.500 1.2803 0.01233 0.00606 -0.0706 0.1564 1.0000
7.750 1.3065 0.01253 0.00629 -0.0706 0.1557 1.0000
8.000 1.3325 0.01275 0.00653 -0.0705 0.1542 1.0000
8.250 1.3581 0.01299 0.00678 -0.0703 0.1525 1.0000
8.500 1.3833 0.01326 0.00706 -0.0701 0.1502 1.0000
8.750 1.4080 0.01355 0.00736 -0.0699 0.1480 1.0000
9.000 1.4324 0.01386 0.00767 -0.0696 0.1461 1.0000
9.250 1.4563 0.01419 0.00802 -0.0693 0.1438 1.0000
9.500 1.4802 0.01450 0.00836 -0.0689 0.1421 1.0000
9.750 1.5049 0.01473 0.00864 -0.0687 0.1410 1.0000
10.000 1.5291 0.01499 0.00892 -0.0684 0.1387 1.0000
10.250 1.5521 0.01531 0.00925 -0.0680 0.1349 1.0000
10.500 1.5735 0.01574 0.00967 -0.0673 0.1302 1.0000
10.750 1.5957 0.01609 0.01004 -0.0668 0.1266 1.0000
11.000 1.6148 0.01661 0.01050 -0.0659 0.1169 1.0000
11.250 1.6185 0.01803 0.01166 -0.0630 0.0832 1.0000
11.500 1.6131 0.01967 0.01320 -0.0587 0.0624 1.0000
11.750 1.6073 0.02168 0.01511 -0.0554 0.0428 1.0000
12.000 1.5974 0.02440 0.01772 -0.0526 0.0223 1.0000
12.250 1.6028 0.02618 0.01951 -0.0515 0.0176 1.0000
12.500 1.6110 0.02783 0.02121 -0.0508 0.0157 1.0000
12.750 1.6191 0.02955 0.02298 -0.0503 0.0145 1.0000
13.000 1.6263 0.03140 0.02488 -0.0498 0.0135 1.0000
13.250 1.6342 0.03318 0.02673 -0.0493 0.0129 1.0000
13.500 1.6406 0.03512 0.02873 -0.0489 0.0123 1.0000
13.750 1.6453 0.03724 0.03091 -0.0484 0.0117 1.0000
14.000 1.6482 0.03955 0.03328 -0.0480 0.0112 1.0000
14.250 1.6499 0.04201 0.03580 -0.0476 0.0107 1.0000
14.500 1.6530 0.04435 0.03822 -0.0472 0.0104 1.0000
14.750 1.6546 0.04686 0.04081 -0.0470 0.0101 1.0000
15.000 1.6550 0.04956 0.04359 -0.0467 0.0098 1.0000
15.250 1.6544 0.05244 0.04654 -0.0467 0.0095 1.0000
15.500 1.6529 0.05550 0.04968 -0.0467 0.0093 1.0000
15.750 1.6506 0.05877 0.05303 -0.0468 0.0090 1.0000
16.000 1.6472 0.06226 0.05659 -0.0471 0.0088 1.0000
16.250 1.6422 0.06599 0.06042 -0.0475 0.0086 1.0000
16.500 1.6359 0.06995 0.06446 -0.0480 0.0083 1.0000
16.750 1.6318 0.07368 0.06828 -0.0485 0.0082 1.0000
17.000 1.6263 0.07764 0.07234 -0.0492 0.0081 1.0000
17.250 1.6190 0.08188 0.07667 -0.0499 0.0080 1.0000
17.500 1.6107 0.08635 0.08124 -0.0508 0.0079 1.0000
17.750 1.6014 0.09106 0.08605 -0.0519 0.0078 1.0000
18.000 1.5910 0.09599 0.09109 -0.0531 0.0077 1.0000
18.250 1.5795 0.10115 0.09636 -0.0545 0.0075 1.0000
18.500 1.5670 0.10659 0.10191 -0.0561 0.0074 1.0000
18.750 1.5538 0.11225 0.10767 -0.0579 0.0073 1.0000
19.000 1.5390 0.11822 0.11375 -0.0600 0.0073 1.0000
19.250 1.5235 0.12441 0.12006 -0.0623 0.0072 1.0000
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Polar data table (+)
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