GOE 324 (HANSA-BRANDENBURG) AIRFOIL (goe324-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 324 (HANSA-BRANDENBURG) AIRFOIL (goe324-il) Reynolds number: 500,000 Max Cl/Cd: 104.3 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe324-il-500000-n5.txt Download as CSV file: xf-goe324-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.750 -0.2523 0.08859 0.08484 -0.0112 0.5811 0.0229
-7.500 -0.2437 0.08579 0.08205 -0.0130 0.5779 0.0231
-7.250 -0.2355 0.08290 0.07917 -0.0152 0.5745 0.0234
-7.000 -0.2272 0.07990 0.07617 -0.0182 0.5711 0.0239
-6.750 -0.2147 0.07641 0.07265 -0.0224 0.5677 0.0244
-6.500 -0.1997 0.07239 0.06858 -0.0278 0.5645 0.0251
-6.250 -0.1791 0.06651 0.06262 -0.0371 0.5615 0.0256
-6.000 -0.1577 0.06160 0.05762 -0.0429 0.5579 0.0257
-5.750 -0.1358 0.05719 0.05310 -0.0472 0.5539 0.0257
-5.500 -0.1131 0.05306 0.04882 -0.0505 0.5500 0.0257
-5.250 -0.0927 0.04951 0.04516 -0.0525 0.5464 0.0259
-5.000 -0.0728 0.04747 0.04311 -0.0533 0.5423 0.0260
-4.750 -0.0509 0.04545 0.04103 -0.0543 0.5377 0.0263
-4.500 -0.0272 0.04319 0.03867 -0.0556 0.5333 0.0265
-4.250 -0.0023 0.04072 0.03607 -0.0569 0.5292 0.0268
-4.000 0.0236 0.03823 0.03346 -0.0581 0.5247 0.0273
-3.500 0.0805 0.03012 0.02471 -0.0603 0.5155 0.0255
-3.250 0.1067 0.02824 0.02266 -0.0607 0.5109 0.0253
-3.000 0.1348 0.02534 0.01946 -0.0608 0.5062 0.0255
-2.750 0.1621 0.02350 0.01740 -0.0610 0.5013 0.0253
-2.500 0.1897 0.02173 0.01538 -0.0610 0.4967 0.0252
-2.250 0.2179 0.01994 0.01333 -0.0610 0.4923 0.0252
-2.000 0.2465 0.01826 0.01136 -0.0609 0.4875 0.0253
-1.750 0.2751 0.01699 0.00981 -0.0608 0.4826 0.0255
-1.500 0.3038 0.01602 0.00859 -0.0607 0.4779 0.0256
-1.250 0.3326 0.01520 0.00761 -0.0607 0.4730 0.0259
-1.000 0.3611 0.01470 0.00705 -0.0608 0.4681 0.0262
-0.750 0.3896 0.01438 0.00668 -0.0609 0.4638 0.0266
-0.500 0.4185 0.01399 0.00622 -0.0609 0.4600 0.0270
-0.250 0.4473 0.01352 0.00568 -0.0609 0.4558 0.0271
0.000 0.4760 0.01313 0.00521 -0.0609 0.4513 0.0274
0.250 0.5046 0.01282 0.00483 -0.0609 0.4471 0.0277
0.500 0.5333 0.01253 0.00450 -0.0610 0.4437 0.0281
0.750 0.5620 0.01228 0.00423 -0.0610 0.4400 0.0285
1.000 0.5906 0.01209 0.00401 -0.0610 0.4354 0.0289
1.250 0.6190 0.01198 0.00384 -0.0610 0.4304 0.0293
1.500 0.6476 0.01181 0.00367 -0.0611 0.4254 0.0298
1.750 0.6761 0.01170 0.00359 -0.0612 0.4197 0.0307
2.000 0.7045 0.01167 0.00353 -0.0613 0.4145 0.0317
2.250 0.7331 0.01162 0.00348 -0.0614 0.4109 0.0324
2.500 0.7619 0.01156 0.00344 -0.0615 0.4077 0.0331
2.750 0.7905 0.01155 0.00343 -0.0617 0.4039 0.0338
3.000 0.8190 0.01153 0.00342 -0.0618 0.3998 0.0349
3.250 0.8473 0.01160 0.00346 -0.0619 0.3954 0.0364
3.750 0.9044 0.01165 0.00355 -0.0622 0.3865 0.0418
4.000 0.9327 0.01173 0.00362 -0.0623 0.3820 0.0471
4.500 0.9869 0.01007 0.00399 -0.0624 0.3741 1.0000
4.750 1.0148 0.01022 0.00411 -0.0625 0.3693 1.0000
5.000 1.0425 0.01040 0.00424 -0.0626 0.3649 1.0000
5.250 1.0703 0.01057 0.00438 -0.0627 0.3606 1.0000
5.500 1.0980 0.01072 0.00452 -0.0628 0.3547 1.0000
5.750 1.1252 0.01094 0.00469 -0.0628 0.3482 1.0000
6.000 1.1527 0.01112 0.00486 -0.0629 0.3420 1.0000
6.250 1.1797 0.01134 0.00505 -0.0629 0.3342 1.0000
6.500 1.2067 0.01157 0.00526 -0.0630 0.3267 1.0000
6.750 1.2332 0.01183 0.00548 -0.0630 0.3183 1.0000
7.000 1.2598 0.01209 0.00572 -0.0630 0.3105 1.0000
7.500 1.3114 0.01271 0.00628 -0.0630 0.2922 1.0000
7.750 1.3365 0.01308 0.00661 -0.0629 0.2829 1.0000
8.000 1.3611 0.01348 0.00698 -0.0628 0.2733 1.0000
8.250 1.3856 0.01387 0.00735 -0.0626 0.2648 1.0000
8.500 1.4091 0.01434 0.00778 -0.0624 0.2565 1.0000
8.750 1.4329 0.01475 0.00819 -0.0622 0.2489 1.0000
9.000 1.4553 0.01527 0.00869 -0.0619 0.2416 1.0000
9.250 1.4783 0.01570 0.00913 -0.0616 0.2354 1.0000
9.500 1.4997 0.01625 0.00967 -0.0612 0.2292 1.0000
9.750 1.5210 0.01677 0.01020 -0.0608 0.2237 1.0000
10.000 1.5419 0.01729 0.01074 -0.0604 0.2189 1.0000
10.250 1.5610 0.01791 0.01138 -0.0598 0.2145 1.0000
10.500 1.5793 0.01855 0.01205 -0.0591 0.2108 1.0000
10.750 1.5966 0.01915 0.01270 -0.0583 0.2074 1.0000
11.000 1.6104 0.01996 0.01356 -0.0573 0.2038 1.0000
11.250 1.6216 0.02110 0.01474 -0.0565 0.1999 1.0000
11.500 1.6331 0.02242 0.01611 -0.0562 0.1956 1.0000
11.750 1.6445 0.02386 0.01758 -0.0560 0.1894 1.0000
12.000 1.6502 0.02589 0.01962 -0.0558 0.1826 1.0000
12.250 1.6597 0.02756 0.02133 -0.0557 0.1759 1.0000
12.500 1.6620 0.02993 0.02371 -0.0554 0.1685 1.0000
12.750 1.6666 0.03204 0.02585 -0.0551 0.1608 1.0000
13.000 1.6662 0.03464 0.02846 -0.0547 0.1530 1.0000
13.250 1.6620 0.03761 0.03144 -0.0543 0.1436 1.0000
13.500 1.6565 0.04072 0.03455 -0.0539 0.1334 1.0000
13.750 1.6458 0.04439 0.03820 -0.0534 0.1219 1.0000
14.000 1.6314 0.04848 0.04228 -0.0530 0.1103 1.0000
14.250 1.6182 0.05260 0.04640 -0.0527 0.1015 1.0000
14.500 1.6103 0.05633 0.05016 -0.0527 0.0967 1.0000
14.750 1.6040 0.05996 0.05383 -0.0528 0.0933 1.0000
15.000 1.5975 0.06367 0.05759 -0.0529 0.0903 1.0000
15.250 1.5934 0.06715 0.06114 -0.0531 0.0881 1.0000
15.500 1.5896 0.07066 0.06472 -0.0534 0.0863 1.0000
15.750 1.5851 0.07427 0.06840 -0.0537 0.0845 1.0000
16.000 1.5803 0.07796 0.07215 -0.0541 0.0828 1.0000
16.250 1.5743 0.08188 0.07614 -0.0546 0.0814 1.0000
16.500 1.5686 0.08576 0.08008 -0.0551 0.0799 1.0000
16.750 1.5649 0.08938 0.08378 -0.0557 0.0786 1.0000
17.000 1.5643 0.09265 0.08714 -0.0562 0.0776 1.0000
17.250 1.5632 0.09598 0.09055 -0.0568 0.0762 1.0000
17.500 1.5601 0.09962 0.09427 -0.0575 0.0748 1.0000
17.750 1.5559 0.10340 0.09812 -0.0582 0.0730 1.0000
18.000 1.5496 0.10755 0.10233 -0.0592 0.0713 1.0000
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Polar data table (+)
Polar graphs
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