EPPLER 328 AIRFOIL (e328-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 328 AIRFOIL (e328-il) Reynolds number: 50,000 Max Cl/Cd: 27.5 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e328-il-50000-n5.txt Download as CSV file: xf-e328-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 328 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.3840 0.12007 0.11316 -0.0195 1.0000 0.1061
-10.250 -0.3848 0.11670 0.10987 -0.0213 1.0000 0.1089
-10.000 -0.4166 0.11450 0.10786 -0.0281 1.0000 0.1127
-9.750 -0.4090 0.10990 0.10332 -0.0283 1.0000 0.1135
-9.500 -0.3970 0.10551 0.09897 -0.0276 1.0000 0.1146
-9.250 -0.4026 0.09494 0.08829 -0.0366 1.0000 0.0563
-9.000 -0.3901 0.09178 0.08519 -0.0346 1.0000 0.0533
-8.750 -0.3973 0.08707 0.08055 -0.0368 1.0000 0.0506
-8.500 -0.4338 0.08208 0.07550 -0.0392 1.0000 0.0462
-8.250 -0.4320 0.07898 0.07247 -0.0380 1.0000 0.0453
-8.000 -0.4383 0.07598 0.06951 -0.0365 1.0000 0.0445
-7.750 -0.4458 0.07294 0.06648 -0.0349 1.0000 0.0436
-7.500 -0.4543 0.06983 0.06335 -0.0328 1.0000 0.0427
-7.250 -0.4609 0.06702 0.06051 -0.0305 1.0000 0.0419
-7.000 -0.4688 0.06396 0.05737 -0.0278 1.0000 0.0409
-6.750 -0.4760 0.06110 0.05438 -0.0246 1.0000 0.0398
-6.500 -0.4847 0.05837 0.05145 -0.0208 1.0000 0.0388
-6.250 -0.4951 0.05619 0.04888 -0.0161 0.9997 0.0377
-6.000 -0.4664 0.05203 0.04430 -0.0189 0.9806 0.0377
-5.750 -0.4369 0.04880 0.04102 -0.0217 0.9614 0.0394
-5.500 -0.4083 0.04561 0.03746 -0.0233 0.9409 0.0403
-5.250 -0.3761 0.04246 0.03384 -0.0249 0.9233 0.0410
-5.000 -0.3412 0.03942 0.03030 -0.0265 0.9068 0.0415
-4.750 -0.3047 0.03654 0.02692 -0.0278 0.8903 0.0420
-4.500 -0.2658 0.03396 0.02387 -0.0292 0.8738 0.0429
-4.250 -0.2252 0.03188 0.02125 -0.0306 0.8571 0.0457
-4.000 -0.1846 0.03000 0.01922 -0.0324 0.8399 0.0501
-3.750 -0.1375 0.02831 0.01724 -0.0345 0.8231 0.0552
-3.500 -0.0940 0.02697 0.01573 -0.0363 0.8057 0.0644
-3.250 -0.0614 0.02589 0.01451 -0.0364 0.7884 0.0764
-3.000 -0.0367 0.02500 0.01350 -0.0353 0.7712 0.0945
-2.750 0.0188 0.02193 0.01384 -0.0365 0.7574 0.7279
-2.500 0.1968 0.02367 0.01415 -0.0562 0.7357 0.9849
-2.250 0.2309 0.02332 0.01342 -0.0579 0.7183 0.9908
-2.000 0.2631 0.02306 0.01282 -0.0592 0.7022 0.9964
-1.750 0.2917 0.02291 0.01236 -0.0599 0.6876 1.0000
-1.500 0.3128 0.02291 0.01211 -0.0590 0.6746 1.0000
-1.250 0.3338 0.02294 0.01195 -0.0582 0.6613 1.0000
-1.000 0.3551 0.02300 0.01183 -0.0573 0.6493 1.0000
-0.750 0.3763 0.02306 0.01172 -0.0565 0.6380 1.0000
-0.500 0.3977 0.02314 0.01162 -0.0556 0.6276 1.0000
-0.250 0.4189 0.02326 0.01163 -0.0548 0.6167 1.0000
0.000 0.4404 0.02338 0.01160 -0.0540 0.6075 1.0000
0.250 0.4619 0.02353 0.01165 -0.0532 0.5976 1.0000
0.500 0.4835 0.02371 0.01174 -0.0525 0.5885 1.0000
0.750 0.5054 0.02387 0.01179 -0.0516 0.5801 1.0000
1.000 0.5263 0.02411 0.01199 -0.0508 0.5712 1.0000
1.250 0.5480 0.02429 0.01207 -0.0500 0.5637 1.0000
1.500 0.5684 0.02459 0.01236 -0.0491 0.5552 1.0000
1.750 0.5898 0.02481 0.01250 -0.0482 0.5482 1.0000
2.000 0.6098 0.02515 0.01286 -0.0472 0.5403 1.0000
2.250 0.6305 0.02541 0.01308 -0.0462 0.5332 1.0000
2.500 0.6503 0.02578 0.01344 -0.0452 0.5263 1.0000
2.750 0.6699 0.02614 0.01382 -0.0441 0.5192 1.0000
3.000 0.6906 0.02643 0.01408 -0.0430 0.5133 1.0000
3.250 0.7079 0.02696 0.01470 -0.0417 0.5057 1.0000
3.500 0.7284 0.02727 0.01497 -0.0406 0.5001 1.0000
3.750 0.7449 0.02785 0.01565 -0.0392 0.4930 1.0000
4.000 0.7632 0.02829 0.01611 -0.0379 0.4867 1.0000
4.250 0.7825 0.02869 0.01655 -0.0366 0.4815 1.0000
4.500 0.7963 0.02942 0.01742 -0.0348 0.4743 1.0000
4.750 0.8155 0.02978 0.01778 -0.0335 0.4690 1.0000
5.000 0.8289 0.03053 0.01865 -0.0317 0.4625 1.0000
5.250 0.8435 0.03116 0.01940 -0.0299 0.4563 1.0000
5.500 0.8643 0.03143 0.01964 -0.0286 0.4517 1.0000
5.750 0.8699 0.03256 0.02098 -0.0259 0.4443 1.0000
6.000 0.8856 0.03307 0.02156 -0.0242 0.4389 1.0000
6.250 0.8988 0.03373 0.02232 -0.0221 0.4334 1.0000
6.500 0.9035 0.03478 0.02354 -0.0192 0.4266 1.0000
6.750 0.9218 0.03510 0.02389 -0.0176 0.4218 1.0000
7.000 0.9211 0.03638 0.02534 -0.0140 0.4151 1.0000
7.250 0.9285 0.03718 0.02624 -0.0113 0.4091 1.0000
7.500 0.9528 0.03718 0.02628 -0.0102 0.4048 1.0000
7.750 0.9311 0.03932 0.02863 -0.0046 0.3969 1.0000
8.000 0.9473 0.03966 0.02903 -0.0027 0.3917 1.0000
8.250 0.9401 0.04117 0.03065 0.0013 0.3853 1.0000
8.500 0.9358 0.04260 0.03218 0.0048 0.3786 1.0000
8.750 0.9723 0.04200 0.03165 0.0047 0.3741 1.0000
9.000 0.9216 0.04621 0.03597 0.0111 0.3649 1.0000
9.250 0.9583 0.04550 0.03537 0.0112 0.3600 1.0000
9.500 0.8885 0.05166 0.04152 0.0167 0.3496 1.0000
9.750 0.9282 0.05042 0.04042 0.0172 0.3453 1.0000
10.000 0.8633 0.05864 0.04861 0.0179 0.3324 1.0000
10.250 0.9097 0.05607 0.04620 0.0195 0.3294 1.0000
10.500 0.8573 0.06467 0.05478 0.0179 0.3159 1.0000
11.000 0.8610 0.06976 0.06004 0.0180 0.3000 1.0000
11.500 0.8182 0.08167 0.07199 0.0148 0.2778 1.0000
11.750 0.8379 0.08189 0.07236 0.0156 0.2721 1.0000
12.250 0.8456 0.08689 0.07755 0.0151 0.2569 1.0000
12.750 0.8541 0.09183 0.08269 0.0145 0.2420 1.0000
13.250 0.8230 0.10345 0.09437 0.0105 0.2226 1.0000
13.500 0.8344 0.10494 0.09599 0.0105 0.2160 1.0000
14.000 0.8404 0.11075 0.10200 0.0091 0.2014 1.0000
14.250 0.8221 0.11765 0.10892 0.0062 0.1922 1.0000
14.500 0.8450 0.11695 0.10839 0.0072 0.1872 1.0000
14.750 0.8228 0.12500 0.11643 0.0036 0.1782 1.0000
15.000 0.8467 0.12403 0.11563 0.0048 0.1734 1.0000
15.250 0.8239 0.13245 0.12403 0.0007 0.1645 1.0000
15.500 0.8468 0.13160 0.12336 0.0018 0.1599 1.0000
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Polar data table (+)
Polar graphs
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