EPPLER 325 AIRFOIL (e325-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 325 AIRFOIL (e325-il) Reynolds number: 50,000 Max Cl/Cd: 26.5 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e325-il-50000-n5.txt Download as CSV file: xf-e325-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 325 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
------ -------- --------- --------- -------- -------- --------
-11.250 -0.5615 0.11809 0.11125 0.0012 1.0000 0.0443
-11.000 -0.5574 0.11394 0.10714 0.0002 1.0000 0.0437
-10.750 -0.5578 0.10912 0.10237 -0.0021 1.0000 0.0433
-10.500 -0.5593 0.10404 0.09734 -0.0046 1.0000 0.0426
-10.250 -0.5644 0.09832 0.09166 -0.0082 1.0000 0.0420
-9.750 -0.6132 0.08455 0.07772 -0.0156 1.0000 0.0368
-9.500 -0.6232 0.08080 0.07393 -0.0153 1.0000 0.0366
-9.250 -0.6356 0.07729 0.07035 -0.0141 1.0000 0.0365
-9.000 -0.6450 0.07409 0.06710 -0.0122 1.0000 0.0362
-8.750 -0.6573 0.07091 0.06379 -0.0096 1.0000 0.0362
-8.500 -0.6642 0.06768 0.06041 -0.0072 1.0000 0.0361
-8.250 -0.6689 0.06444 0.05698 -0.0047 1.0000 0.0360
-8.000 -0.6714 0.06123 0.05354 -0.0021 1.0000 0.0360
-7.750 -0.6715 0.05801 0.05005 0.0007 1.0000 0.0360
-7.500 -0.6692 0.05489 0.04662 0.0036 1.0000 0.0361
-7.250 -0.6636 0.05183 0.04324 0.0063 1.0000 0.0361
-7.000 -0.6549 0.04896 0.04005 0.0088 1.0000 0.0360
-6.750 -0.6442 0.04603 0.03676 0.0113 1.0000 0.0360
-6.500 -0.6303 0.04321 0.03355 0.0136 1.0000 0.0361
-6.250 -0.6128 0.04056 0.03051 0.0155 1.0000 0.0364
-6.000 -0.5911 0.03795 0.02748 0.0170 1.0000 0.0368
-5.750 -0.5675 0.03577 0.02521 0.0176 1.0000 0.0383
-5.500 -0.5419 0.03395 0.02327 0.0180 1.0000 0.0411
-5.250 -0.5075 0.03194 0.02087 0.0176 1.0000 0.0445
-5.000 -0.4647 0.02990 0.01890 0.0154 1.0000 0.0487
-4.750 -0.4168 0.02826 0.01716 0.0125 1.0000 0.0574
-4.500 -0.3841 0.02699 0.01587 0.0119 1.0000 0.0677
-4.250 -0.3640 0.02594 0.01493 0.0131 1.0000 0.0830
-4.000 -0.3390 0.02457 0.01378 0.0129 0.9789 0.1188
-3.750 -0.3244 0.02098 0.01242 0.0133 0.9313 0.4072
-3.500 -0.1251 0.02752 0.01913 -0.0005 0.9750 0.9375
-3.250 -0.0645 0.02710 0.01816 -0.0077 0.8805 0.9462
-3.000 -0.0217 0.02673 0.01730 -0.0110 0.8304 0.9525
-2.750 0.0094 0.02649 0.01668 -0.0119 0.7943 0.9591
-2.500 0.0408 0.02617 0.01599 -0.0129 0.7651 0.9648
-2.250 0.0673 0.02602 0.01555 -0.0130 0.7403 0.9712
-2.000 0.0987 0.02564 0.01489 -0.0141 0.7183 0.9760
-1.750 0.1274 0.02541 0.01442 -0.0147 0.6981 0.9813
-1.500 0.1572 0.02512 0.01392 -0.0156 0.6794 0.9858
-1.250 0.1871 0.02485 0.01346 -0.0165 0.6624 0.9903
-1.000 0.2164 0.02464 0.01307 -0.0173 0.6466 0.9946
-0.750 0.2465 0.02438 0.01266 -0.0182 0.6313 0.9985
-0.500 0.2714 0.02431 0.01246 -0.0182 0.6177 1.0000
-0.250 0.2932 0.02431 0.01233 -0.0175 0.6057 1.0000
0.000 0.3151 0.02433 0.01227 -0.0168 0.5935 1.0000
0.250 0.3374 0.02438 0.01226 -0.0162 0.5814 1.0000
0.500 0.3595 0.02445 0.01226 -0.0156 0.5704 1.0000
0.750 0.3814 0.02452 0.01225 -0.0148 0.5604 1.0000
1.000 0.4036 0.02464 0.01237 -0.0143 0.5493 1.0000
1.250 0.4254 0.02477 0.01246 -0.0135 0.5399 1.0000
1.500 0.4471 0.02491 0.01259 -0.0128 0.5303 1.0000
1.750 0.4691 0.02511 0.01280 -0.0122 0.5206 1.0000
2.000 0.4912 0.02527 0.01291 -0.0114 0.5126 1.0000
2.250 0.5136 0.02552 0.01323 -0.0109 0.5028 1.0000
2.500 0.5353 0.02571 0.01337 -0.0101 0.4953 1.0000
2.750 0.5572 0.02603 0.01382 -0.0095 0.4859 1.0000
3.000 0.5787 0.02626 0.01403 -0.0087 0.4787 1.0000
3.250 0.6002 0.02662 0.01450 -0.0080 0.4696 1.0000
3.500 0.6216 0.02690 0.01481 -0.0071 0.4628 1.0000
3.750 0.6427 0.02732 0.01537 -0.0065 0.4540 1.0000
4.000 0.6639 0.02760 0.01566 -0.0055 0.4473 1.0000
4.250 0.6844 0.02811 0.01634 -0.0048 0.4386 1.0000
4.500 0.7055 0.02838 0.01663 -0.0038 0.4323 1.0000
4.750 0.7250 0.02899 0.01746 -0.0031 0.4233 1.0000
5.000 0.7461 0.02926 0.01774 -0.0020 0.4174 1.0000
5.250 0.7645 0.03000 0.01874 -0.0012 0.4083 1.0000
5.500 0.7853 0.03027 0.01904 0.0000 0.4021 1.0000
5.750 0.8025 0.03110 0.02012 0.0010 0.3932 1.0000
6.000 0.8228 0.03136 0.02044 0.0023 0.3867 1.0000
6.250 0.8385 0.03228 0.02163 0.0034 0.3777 1.0000
6.500 0.8586 0.03251 0.02190 0.0048 0.3711 1.0000
6.750 0.8724 0.03353 0.02321 0.0061 0.3618 1.0000
7.000 0.8926 0.03368 0.02340 0.0076 0.3553 1.0000
7.250 0.9038 0.03485 0.02488 0.0091 0.3456 1.0000
7.500 0.9230 0.03504 0.02513 0.0107 0.3387 1.0000
7.750 0.9327 0.03616 0.02654 0.0126 0.3290 1.0000
8.000 0.9471 0.03673 0.02727 0.0144 0.3210 1.0000
8.250 0.9592 0.03740 0.02813 0.0164 0.3120 1.0000
8.500 0.9672 0.03841 0.02935 0.0187 0.3029 1.0000
8.750 0.9850 0.03836 0.02935 0.0206 0.2946 1.0000
9.000 0.9839 0.03989 0.03117 0.0235 0.2847 1.0000
9.250 0.9941 0.04030 0.03172 0.0260 0.2759 1.0000
9.500 0.9993 0.04096 0.03253 0.0289 0.2666 1.0000
9.750 0.9937 0.04237 0.03412 0.0324 0.2578 1.0000
10.000 1.0058 0.04223 0.03401 0.0351 0.2487 1.0000
10.250 0.9840 0.04448 0.03645 0.0398 0.2413 1.0000
10.500 0.9870 0.04478 0.03678 0.0431 0.2329 1.0000
10.750 0.9501 0.04751 0.03959 0.0488 0.2287 1.0000
11.000 0.9598 0.04714 0.03919 0.0518 0.2199 1.0000
11.250 0.9097 0.05182 0.04391 0.0553 0.2172 1.0000
11.500 0.8498 0.05977 0.05183 0.0548 0.2127 1.0000
11.750 0.8694 0.05886 0.05099 0.0571 0.2037 1.0000
12.000 0.7926 0.07176 0.06374 0.0524 0.1971 1.0000
12.250 0.8093 0.07128 0.06336 0.0541 0.1892 1.0000
12.500 0.7809 0.07823 0.07028 0.0519 0.1810 1.0000
12.750 0.7484 0.08653 0.07850 0.0488 0.1729 1.0000
13.000 0.7818 0.08307 0.07522 0.0518 0.1656 1.0000
13.250 0.7229 0.09705 0.08901 0.0456 0.1577 1.0000
13.500 0.7976 0.08545 0.07774 0.0528 0.1504 1.0000
13.750 0.7058 0.10664 0.09862 0.0426 0.1439 1.0000
14.000 0.7555 0.09924 0.09149 0.0474 0.1374 1.0000
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Polar data table (+)
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