GOE 318 (HANSA-BRANDENBURG VI.5) AIRFOIL (goe318-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 318 (HANSA-BRANDENBURG VI.5) AIRFOIL (goe318-il) Reynolds number: 500,000 Max Cl/Cd: 93.32 at α=8° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe318-il-500000.txt Download as CSV file: xf-goe318-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 318 (HANSA-BRANDENBURG VI.5) 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
------ -------- --------- --------- -------- -------- --------
-8.000 -0.4485 0.09606 0.09347 0.0138 0.7676 0.0222
-7.750 -0.4434 0.09256 0.08991 0.0115 0.7584 0.0229
-7.500 -0.4395 0.08832 0.08567 0.0060 0.7493 0.0242
-7.250 -0.4246 0.08191 0.07918 -0.0064 0.7423 0.0246
-7.000 -0.4077 0.07639 0.07359 -0.0133 0.7348 0.0247
-6.750 -0.3988 0.07008 0.06719 -0.0172 0.7290 0.0250
-6.500 -0.3861 0.06730 0.06439 -0.0176 0.7217 0.0253
-6.250 -0.3702 0.06487 0.06189 -0.0185 0.7153 0.0258
-6.000 -0.3513 0.06186 0.05882 -0.0208 0.7091 0.0267
-5.750 -0.3292 0.05804 0.05489 -0.0244 0.7031 0.0280
-5.500 -0.2879 0.05134 0.04779 -0.0325 0.6986 0.0306
-5.250 -0.2703 0.04403 0.04027 -0.0357 0.6939 0.0312
-5.000 -0.2501 0.04216 0.03836 -0.0362 0.6881 0.0318
-4.750 -0.2276 0.04042 0.03652 -0.0368 0.6830 0.0327
-4.500 -0.2022 0.03802 0.03399 -0.0378 0.6776 0.0341
-4.250 -0.1657 0.03540 0.03089 -0.0387 0.6721 0.0382
-4.000 -0.1437 0.02918 0.02428 -0.0403 0.6675 0.0395
-3.750 -0.1185 0.02785 0.02294 -0.0407 0.6610 0.0405
-3.500 -0.0923 0.02657 0.02155 -0.0410 0.6550 0.0420
-3.250 -0.0644 0.02497 0.01974 -0.0412 0.6496 0.0446
-3.000 -0.0321 0.02547 0.01986 -0.0406 0.6434 0.0482
-2.750 -0.0071 0.02084 0.01496 -0.0416 0.6387 0.0509
-2.500 0.0204 0.01993 0.01399 -0.0419 0.6336 0.0529
-2.250 0.0493 0.01917 0.01308 -0.0419 0.6275 0.0573
-2.000 0.0779 0.01773 0.01133 -0.0420 0.6222 0.0633
-1.750 0.1061 0.01692 0.01050 -0.0422 0.6162 0.0662
-1.500 0.1386 0.01400 0.00699 -0.0413 0.6103 0.0445
-1.250 0.1674 0.01323 0.00607 -0.0412 0.6037 0.0444
-1.000 0.1964 0.01244 0.00518 -0.0411 0.5964 0.0437
-0.750 0.2251 0.01189 0.00453 -0.0410 0.5905 0.0438
-0.500 0.2539 0.01142 0.00405 -0.0411 0.5844 0.0442
-0.250 0.2826 0.01105 0.00364 -0.0410 0.5782 0.0447
0.000 0.3113 0.01074 0.00330 -0.0411 0.5722 0.0454
0.250 0.3401 0.01050 0.00305 -0.0411 0.5652 0.0467
0.500 0.3688 0.01034 0.00284 -0.0412 0.5587 0.0479
0.750 0.3978 0.01005 0.00256 -0.0413 0.5511 0.0491
1.000 0.4267 0.00983 0.00229 -0.0414 0.5439 0.0520
1.250 0.4557 0.00969 0.00217 -0.0415 0.5353 0.0557
1.500 0.4846 0.00962 0.00206 -0.0416 0.5271 0.0611
1.750 0.5093 0.00719 0.00209 -0.0414 0.5182 1.0000
2.000 0.5381 0.00726 0.00206 -0.0414 0.5085 1.0000
2.250 0.5667 0.00735 0.00206 -0.0415 0.4980 1.0000
2.500 0.5953 0.00745 0.00207 -0.0416 0.4862 1.0000
2.750 0.6239 0.00755 0.00211 -0.0417 0.4736 1.0000
3.000 0.6524 0.00767 0.00216 -0.0419 0.4601 1.0000
3.250 0.6809 0.00782 0.00223 -0.0420 0.4452 1.0000
3.500 0.7092 0.00800 0.00232 -0.0421 0.4288 1.0000
3.750 0.7374 0.00821 0.00244 -0.0423 0.4110 1.0000
4.000 0.7656 0.00842 0.00257 -0.0424 0.3918 1.0000
4.250 0.7936 0.00867 0.00273 -0.0426 0.3702 1.0000
4.500 0.8214 0.00897 0.00293 -0.0428 0.3481 1.0000
4.750 0.8491 0.00928 0.00314 -0.0429 0.3272 1.0000
5.000 0.8768 0.00960 0.00337 -0.0431 0.3114 1.0000
5.250 0.9044 0.00989 0.00362 -0.0433 0.3001 1.0000
5.500 0.9319 0.01021 0.00388 -0.0434 0.2917 1.0000
5.750 0.9596 0.01044 0.00412 -0.0435 0.2852 1.0000
6.000 0.9868 0.01076 0.00441 -0.0436 0.2792 1.0000
6.250 1.0144 0.01100 0.00467 -0.0437 0.2737 1.0000
6.500 1.0416 0.01128 0.00494 -0.0438 0.2670 1.0000
6.750 1.0687 0.01156 0.00522 -0.0439 0.2600 1.0000
7.000 1.0958 0.01181 0.00550 -0.0440 0.2535 1.0000
7.250 1.1224 0.01214 0.00582 -0.0441 0.2471 1.0000
7.500 1.1496 0.01234 0.00607 -0.0441 0.2408 1.0000
7.750 1.1758 0.01271 0.00643 -0.0442 0.2332 1.0000
8.000 1.2029 0.01289 0.00669 -0.0443 0.2261 1.0000
8.250 1.2290 0.01324 0.00704 -0.0443 0.2179 1.0000
8.500 1.2551 0.01356 0.00736 -0.0443 0.2051 1.0000
8.750 1.2813 0.01387 0.00767 -0.0444 0.1816 1.0000
9.000 1.2911 0.01666 0.00960 -0.0436 0.0574 1.0000
9.250 1.3081 0.01819 0.01097 -0.0429 0.0308 1.0000
9.500 1.3282 0.01918 0.01199 -0.0424 0.0253 1.0000
9.750 1.3465 0.02030 0.01314 -0.0418 0.0222 1.0000
10.000 1.3653 0.02125 0.01419 -0.0411 0.0206 1.0000
10.250 1.3827 0.02227 0.01529 -0.0405 0.0193 1.0000
10.500 1.3970 0.02350 0.01661 -0.0396 0.0182 1.0000
10.750 1.4034 0.02533 0.01854 -0.0382 0.0173 1.0000
11.000 1.4020 0.02750 0.02085 -0.0367 0.0168 1.0000
11.250 1.4077 0.02952 0.02299 -0.0365 0.0165 1.0000
11.500 1.4122 0.03183 0.02542 -0.0365 0.0160 1.0000
11.750 1.4153 0.03437 0.02806 -0.0366 0.0156 1.0000
12.000 1.4172 0.03708 0.03087 -0.0368 0.0151 1.0000
12.250 1.4178 0.03997 0.03385 -0.0370 0.0147 1.0000
12.500 1.4169 0.04303 0.03699 -0.0372 0.0143 1.0000
12.750 1.4136 0.04637 0.04041 -0.0374 0.0140 1.0000
13.000 1.4081 0.04997 0.04410 -0.0377 0.0138 1.0000
13.250 1.4006 0.05377 0.04798 -0.0378 0.0135 1.0000
13.500 1.3914 0.05770 0.05199 -0.0378 0.0133 1.0000
13.750 1.3830 0.06138 0.05576 -0.0373 0.0131 1.0000
14.000 1.3826 0.06451 0.05900 -0.0377 0.0129 1.0000
14.250 1.3823 0.06773 0.06232 -0.0380 0.0128 1.0000
14.500 1.3817 0.07100 0.06570 -0.0384 0.0126 1.0000
14.750 1.3812 0.07430 0.06910 -0.0388 0.0124 1.0000
15.000 1.3806 0.07765 0.07254 -0.0391 0.0122 1.0000
15.250 1.3798 0.08102 0.07602 -0.0395 0.0120 1.0000
15.500 1.3790 0.08445 0.07955 -0.0400 0.0119 1.0000
15.750 1.3777 0.08802 0.08322 -0.0406 0.0117 1.0000
16.000 1.3763 0.09167 0.08697 -0.0414 0.0115 1.0000
16.250 1.3744 0.09546 0.09086 -0.0424 0.0113 1.0000
16.500 1.3719 0.09943 0.09493 -0.0435 0.0111 1.0000
16.750 1.3690 0.10353 0.09912 -0.0448 0.0109 1.0000
17.000 1.3662 0.10763 0.10331 -0.0462 0.0107 1.0000
17.250 1.3632 0.11173 0.10748 -0.0476 0.0105 1.0000
17.500 1.3605 0.11566 0.11148 -0.0488 0.0104 1.0000
17.750 1.3560 0.11989 0.11581 -0.0500 0.0102 1.0000
18.000 1.3487 0.12471 0.12077 -0.0514 0.0101 1.0000
18.250 1.3386 0.13035 0.12656 -0.0538 0.0101 1.0000
18.500 1.3265 0.13666 0.13304 -0.0568 0.0100 1.0000
18.750 1.3145 0.14331 0.13986 -0.0605 0.0100 1.0000
19.000 1.3031 0.15014 0.14684 -0.0646 0.0100 1.0000
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Polar data table (+)
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