EPPLER 325 AIRFOIL (e325-il) Xfoil prediction polar at RE=100,000 Ncrit=5
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Airfoil: EPPLER 325 AIRFOIL (e325-il) Reynolds number: 100,000 Max Cl/Cd: 42.58 at α=9.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e325-il-100000-n5.txt Download as CSV file: xf-e325-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.5675 0.09727 0.09249 -0.0058 1.0000 0.0244
-10.250 -0.5728 0.09161 0.08686 -0.0093 1.0000 0.0238
-10.000 -0.5825 0.08601 0.08126 -0.0127 1.0000 0.0233
-9.750 -0.5981 0.08049 0.07569 -0.0150 1.0000 0.0228
-9.250 -0.6548 0.06831 0.06311 -0.0138 1.0000 0.0204
-9.000 -0.6642 0.06555 0.06028 -0.0113 1.0000 0.0202
-8.750 -0.6743 0.06270 0.05733 -0.0082 1.0000 0.0201
-8.500 -0.6799 0.05972 0.05420 -0.0055 1.0000 0.0198
-8.250 -0.6837 0.05658 0.05089 -0.0026 1.0000 0.0196
-8.000 -0.6854 0.05337 0.04747 0.0005 1.0000 0.0193
-7.750 -0.6852 0.05006 0.04390 0.0036 1.0000 0.0190
-7.500 -0.6823 0.04682 0.04036 0.0068 1.0000 0.0188
-7.250 -0.6771 0.04358 0.03678 0.0100 1.0000 0.0185
-7.000 -0.6686 0.04058 0.03342 0.0130 1.0000 0.0182
-6.750 -0.6575 0.03762 0.03005 0.0158 1.0000 0.0181
-6.500 -0.6428 0.03496 0.02702 0.0182 1.0000 0.0181
-6.250 -0.6248 0.03259 0.02430 0.0201 1.0000 0.0182
-6.000 -0.6035 0.03034 0.02173 0.0215 1.0000 0.0185
-5.750 -0.5795 0.02838 0.01952 0.0225 1.0000 0.0188
-5.500 -0.5534 0.02663 0.01753 0.0231 1.0000 0.0196
-5.250 -0.5177 0.02507 0.01585 0.0214 0.9763 0.0218
-5.000 -0.4696 0.02341 0.01401 0.0175 0.9249 0.0244
-4.750 -0.4247 0.02179 0.01229 0.0143 0.8813 0.0265
-4.500 -0.3939 0.02079 0.01111 0.0139 0.8412 0.0293
-4.250 -0.3709 0.02005 0.01024 0.0151 0.8080 0.0352
-4.000 -0.3503 0.01934 0.00940 0.0168 0.7805 0.0429
-3.750 -0.3301 0.01864 0.00867 0.0184 0.7562 0.0578
-3.500 -0.3103 0.01765 0.00798 0.0201 0.7354 0.1208
-3.250 -0.3084 0.01520 0.00739 0.0242 0.7183 0.4758
-3.000 -0.2211 0.01899 0.01201 0.0209 0.6952 0.8387
-2.750 -0.1677 0.02048 0.01312 0.0186 0.6750 0.8678
-2.500 -0.1120 0.02127 0.01356 0.0149 0.6556 0.8864
-2.250 -0.0916 0.02130 0.01337 0.0164 0.6404 0.8959
-2.000 -0.0573 0.02115 0.01298 0.0151 0.6246 0.8987
-1.750 -0.0261 0.02102 0.01262 0.0143 0.6096 0.9022
-1.500 0.0004 0.02092 0.01234 0.0144 0.5959 0.9067
-1.250 0.0199 0.02085 0.01213 0.0158 0.5837 0.9121
-1.000 0.0526 0.02071 0.01179 0.0147 0.5710 0.9145
-0.750 0.0825 0.02060 0.01151 0.0141 0.5595 0.9174
-0.500 0.1098 0.02050 0.01130 0.0140 0.5476 0.9210
-0.250 0.1319 0.02046 0.01114 0.0148 0.5372 0.9251
0.000 0.1565 0.02040 0.01094 0.0153 0.5276 0.9283
0.250 0.1871 0.02029 0.01074 0.0144 0.5165 0.9304
0.500 0.2159 0.02021 0.01057 0.0140 0.5070 0.9329
0.750 0.2425 0.02017 0.01043 0.0140 0.4977 0.9356
1.000 0.2671 0.02015 0.01037 0.0143 0.4887 0.9386
1.250 0.2877 0.02018 0.01031 0.0155 0.4810 0.9418
1.500 0.3157 0.02013 0.01024 0.0151 0.4719 0.9437
1.750 0.3448 0.02009 0.01011 0.0146 0.4644 0.9455
2.000 0.3727 0.02007 0.01011 0.0143 0.4554 0.9474
2.250 0.3993 0.02008 0.01004 0.0142 0.4486 0.9495
2.500 0.4250 0.02011 0.01011 0.0143 0.4403 0.9519
2.750 0.4486 0.02017 0.01011 0.0148 0.4338 0.9540
3.000 0.4708 0.02026 0.01026 0.0156 0.4263 0.9564
3.250 0.4971 0.02029 0.01028 0.0156 0.4194 0.9581
3.500 0.5249 0.02034 0.01036 0.0152 0.4123 0.9595
3.750 0.5518 0.02040 0.01043 0.0151 0.4051 0.9610
4.000 0.5788 0.02048 0.01056 0.0149 0.3985 0.9627
4.250 0.6045 0.02059 0.01073 0.0149 0.3914 0.9646
4.500 0.6289 0.02070 0.01082 0.0153 0.3856 0.9662
4.750 0.6525 0.02085 0.01112 0.0157 0.3780 0.9679
5.000 0.6756 0.02101 0.01129 0.0163 0.3721 0.9699
5.250 0.7001 0.02118 0.01157 0.0165 0.3650 0.9715
5.500 0.7265 0.02130 0.01177 0.0164 0.3579 0.9727
5.750 0.7521 0.02147 0.01203 0.0164 0.3509 0.9740
6.000 0.7775 0.02163 0.01230 0.0164 0.3434 0.9754
6.250 0.8029 0.02182 0.01259 0.0165 0.3364 0.9772
6.500 0.8272 0.02203 0.01293 0.0167 0.3285 0.9790
6.750 0.8503 0.02225 0.01324 0.0172 0.3214 0.9806
7.000 0.8723 0.02250 0.01364 0.0178 0.3133 0.9822
7.250 0.8951 0.02274 0.01399 0.0183 0.3056 0.9836
7.500 0.9203 0.02295 0.01434 0.0182 0.2966 0.9850
7.750 0.9453 0.02321 0.01479 0.0181 0.2870 0.9868
8.000 0.9696 0.02343 0.01509 0.0182 0.2779 0.9888
8.250 0.9922 0.02374 0.01559 0.0185 0.2669 0.9907
8.500 1.0136 0.02408 0.01610 0.0190 0.2556 0.9924
8.750 1.0349 0.02444 0.01661 0.0195 0.2442 0.9942
9.000 1.0570 0.02483 0.01713 0.0197 0.2319 0.9960
9.250 1.0782 0.02532 0.01774 0.0199 0.2187 0.9981
9.500 1.0978 0.02590 0.01847 0.0204 0.2045 1.0000
9.750 1.1070 0.02656 0.01921 0.0227 0.1921 1.0000
10.000 1.1140 0.02731 0.02007 0.0253 0.1790 1.0000
10.250 1.1179 0.02816 0.02100 0.0283 0.1666 1.0000
10.500 1.1181 0.02909 0.02201 0.0317 0.1550 1.0000
10.750 1.1137 0.03009 0.02307 0.0358 0.1453 1.0000
11.000 1.1025 0.03116 0.02415 0.0406 0.1377 1.0000
11.250 1.0852 0.03210 0.02517 0.0465 0.1320 1.0000
11.500 1.0612 0.03315 0.02625 0.0527 0.1284 1.0000
11.750 1.0389 0.03466 0.02776 0.0575 0.1250 1.0000
12.000 1.0227 0.03661 0.02978 0.0604 0.1201 1.0000
12.250 1.0081 0.03908 0.03229 0.0621 0.1144 1.0000
12.500 0.9943 0.04198 0.03518 0.0629 0.1093 1.0000
12.750 0.9833 0.04506 0.03836 0.0631 0.1035 1.0000
13.000 0.9706 0.04856 0.04184 0.0628 0.0988 1.0000
13.250 0.9612 0.05197 0.04535 0.0624 0.0935 1.0000
13.500 0.9502 0.05571 0.04913 0.0616 0.0889 1.0000
13.750 0.9397 0.05949 0.05290 0.0607 0.0846 1.0000
14.000 0.9312 0.06323 0.05675 0.0597 0.0800 1.0000
14.250 0.9213 0.06719 0.06072 0.0585 0.0761 1.0000
14.500 0.9136 0.07102 0.06460 0.0573 0.0721 1.0000
14.750 0.9062 0.07506 0.06873 0.0559 0.0680 1.0000
15.000 0.8994 0.07900 0.07266 0.0545 0.0647 1.0000
15.250 0.8931 0.08310 0.07684 0.0530 0.0610 1.0000
15.500 0.8866 0.08736 0.08119 0.0514 0.0576 1.0000
15.750 0.8818 0.09132 0.08515 0.0498 0.0548 1.0000
16.000 0.8764 0.09554 0.08946 0.0481 0.0519 1.0000
16.250 0.8702 0.10012 0.09414 0.0462 0.0491 1.0000
16.500 0.8662 0.10425 0.09833 0.0444 0.0467 1.0000
16.750 0.8634 0.10815 0.10224 0.0428 0.0445 1.0000
17.000 0.8547 0.11357 0.10783 0.0403 0.0426 1.0000
17.250 0.8471 0.11880 0.11317 0.0379 0.0407 1.0000
17.500 0.8434 0.12327 0.11769 0.0357 0.0389 1.0000
17.750 0.8433 0.12689 0.12129 0.0341 0.0371 1.0000
18.000 0.8285 0.13418 0.12877 0.0305 0.0363 1.0000
18.250 0.8082 0.14306 0.13782 0.0260 0.0356 1.0000
18.500 0.7708 0.15699 0.15184 0.0192 0.0356 1.0000
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