EPPLER 485 AIRFOIL (e485-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 485 AIRFOIL (e485-il) Reynolds number: 1,000,000 Max Cl/Cd: 81.89 at α=7.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e485-il-1000000-n5.txt Download as CSV file: xf-e485-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 485 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-17.250 -0.8471 0.12269 0.12042 -0.0101 1.0000 0.0020
-17.000 -0.8917 0.10938 0.10699 -0.0169 1.0000 0.0018
-16.750 -0.9595 0.09185 0.08926 -0.0260 1.0000 0.0018
-16.500 -1.0043 0.07869 0.07592 -0.0332 1.0000 0.0017
-16.250 -1.0427 0.06671 0.06373 -0.0407 1.0000 0.0017
-16.000 -1.0719 0.05747 0.05429 -0.0467 1.0000 0.0017
-15.750 -1.0929 0.05071 0.04736 -0.0507 1.0000 0.0017
-15.500 -1.1086 0.04556 0.04204 -0.0529 1.0000 0.0017
-15.250 -1.1219 0.04131 0.03763 -0.0540 1.0000 0.0017
-15.000 -1.1284 0.03820 0.03439 -0.0541 1.0000 0.0017
-14.750 -1.1303 0.03580 0.03188 -0.0537 1.0000 0.0017
-14.500 -1.1414 0.03278 0.02868 -0.0525 1.0000 0.0018
-14.250 -1.1311 0.03172 0.02758 -0.0516 1.0000 0.0017
-14.000 -1.1388 0.02931 0.02499 -0.0495 1.0000 0.0018
-13.750 -1.1342 0.02795 0.02354 -0.0478 1.0000 0.0018
-13.500 -1.1354 0.02622 0.02167 -0.0454 1.0000 0.0019
-13.250 -1.1274 0.02522 0.02058 -0.0435 1.0000 0.0019
-13.000 -1.1237 0.02395 0.01920 -0.0409 1.0000 0.0020
-12.750 -1.1169 0.02294 0.01810 -0.0385 1.0000 0.0021
-12.500 -1.1077 0.02216 0.01725 -0.0361 1.0000 0.0021
-12.250 -1.0997 0.02140 0.01641 -0.0333 1.0000 0.0021
-12.000 -1.0915 0.02070 0.01564 -0.0303 1.0000 0.0022
-11.750 -1.0799 0.02006 0.01492 -0.0279 1.0000 0.0022
-11.500 -1.0662 0.01943 0.01424 -0.0258 1.0000 0.0023
-11.250 -1.0522 0.01882 0.01357 -0.0237 1.0000 0.0024
-11.000 -1.0373 0.01824 0.01294 -0.0216 1.0000 0.0026
-10.750 -1.0219 0.01770 0.01233 -0.0197 1.0000 0.0027
-10.500 -1.0060 0.01720 0.01179 -0.0177 1.0000 0.0028
-10.250 -0.9854 0.01664 0.01117 -0.0168 0.9992 0.0029
-10.000 -0.9557 0.01607 0.01053 -0.0177 0.9957 0.0030
-9.750 -0.9274 0.01552 0.00994 -0.0183 0.9907 0.0031
-9.500 -0.8983 0.01488 0.00925 -0.0191 0.9854 0.0036
-9.250 -0.8674 0.01436 0.00870 -0.0202 0.9799 0.0038
-9.000 -0.8361 0.01386 0.00816 -0.0213 0.9709 0.0042
-8.750 -0.8027 0.01340 0.00765 -0.0229 0.9591 0.0045
-8.500 -0.7683 0.01294 0.00714 -0.0246 0.9436 0.0050
-8.250 -0.7393 0.01255 0.00669 -0.0251 0.9233 0.0056
-8.000 -0.7150 0.01226 0.00631 -0.0245 0.9032 0.0063
-7.750 -0.6915 0.01201 0.00597 -0.0237 0.8867 0.0069
-7.500 -0.6682 0.01173 0.00563 -0.0229 0.8726 0.0078
-7.250 -0.6444 0.01147 0.00531 -0.0222 0.8604 0.0088
-7.000 -0.6201 0.01125 0.00503 -0.0216 0.8493 0.0097
-6.750 -0.5961 0.01098 0.00473 -0.0209 0.8385 0.0116
-6.500 -0.5712 0.01076 0.00447 -0.0204 0.8289 0.0132
-6.250 -0.5467 0.01051 0.00419 -0.0198 0.8198 0.0163
-6.000 -0.5217 0.01028 0.00395 -0.0193 0.8105 0.0197
-5.750 -0.4966 0.01005 0.00371 -0.0189 0.8018 0.0245
-5.500 -0.4715 0.00983 0.00348 -0.0184 0.7931 0.0301
-5.250 -0.4461 0.00959 0.00327 -0.0180 0.7844 0.0380
-5.000 -0.4209 0.00938 0.00305 -0.0175 0.7760 0.0469
-4.750 -0.3951 0.00917 0.00287 -0.0172 0.7671 0.0561
-4.500 -0.3693 0.00899 0.00269 -0.0168 0.7588 0.0665
-4.250 -0.3436 0.00878 0.00251 -0.0164 0.7498 0.0822
-4.000 -0.3182 0.00854 0.00233 -0.0160 0.7409 0.1040
-3.750 -0.2925 0.00835 0.00218 -0.0157 0.7315 0.1236
-3.500 -0.2667 0.00814 0.00203 -0.0153 0.7214 0.1477
-3.250 -0.2414 0.00789 0.00188 -0.0149 0.7116 0.1826
-3.000 -0.2161 0.00767 0.00175 -0.0145 0.7017 0.2177
-2.750 -0.1905 0.00744 0.00162 -0.0142 0.6911 0.2554
-2.500 -0.1649 0.00722 0.00151 -0.0138 0.6808 0.2950
-2.250 -0.1399 0.00696 0.00139 -0.0134 0.6699 0.3469
-1.750 -0.0895 0.00650 0.00120 -0.0125 0.6451 0.4486
-1.500 -0.0648 0.00624 0.00111 -0.0120 0.6319 0.5110
-1.250 -0.0395 0.00605 0.00104 -0.0116 0.6184 0.5617
-1.000 -0.0140 0.00590 0.00100 -0.0111 0.6047 0.6090
-0.750 0.0120 0.00581 0.00098 -0.0108 0.5904 0.6475
-0.500 0.0382 0.00575 0.00097 -0.0104 0.5753 0.6801
-0.250 0.0650 0.00575 0.00098 -0.0102 0.5594 0.7048
0.000 0.0919 0.00576 0.00099 -0.0100 0.5435 0.7240
0.250 0.1189 0.00581 0.00101 -0.0098 0.5269 0.7404
0.500 0.1458 0.00587 0.00105 -0.0096 0.5095 0.7551
0.750 0.1730 0.00594 0.00108 -0.0094 0.4922 0.7682
1.000 0.2003 0.00602 0.00112 -0.0093 0.4745 0.7793
1.250 0.2273 0.00611 0.00118 -0.0091 0.4565 0.7885
1.500 0.2544 0.00622 0.00123 -0.0090 0.4376 0.7967
1.750 0.2815 0.00634 0.00130 -0.0088 0.4195 0.8048
2.000 0.3086 0.00646 0.00136 -0.0087 0.4015 0.8118
2.250 0.3354 0.00659 0.00144 -0.0086 0.3822 0.8188
2.500 0.3624 0.00673 0.00153 -0.0084 0.3639 0.8249
2.750 0.3890 0.00688 0.00162 -0.0082 0.3460 0.8305
3.000 0.4160 0.00702 0.00171 -0.0081 0.3292 0.8361
3.250 0.4427 0.00718 0.00182 -0.0080 0.3115 0.8408
3.500 0.4693 0.00733 0.00193 -0.0078 0.2956 0.8456
3.750 0.4959 0.00750 0.00204 -0.0076 0.2786 0.8504
4.000 0.5226 0.00767 0.00216 -0.0075 0.2646 0.8547
4.250 0.5488 0.00783 0.00229 -0.0072 0.2499 0.8588
4.500 0.5751 0.00801 0.00243 -0.0070 0.2355 0.8632
4.750 0.6013 0.00821 0.00258 -0.0068 0.2208 0.8675
5.000 0.6274 0.00839 0.00273 -0.0066 0.2083 0.8713
5.250 0.6531 0.00858 0.00289 -0.0063 0.1955 0.8753
5.500 0.6789 0.00879 0.00306 -0.0060 0.1829 0.8795
6.000 0.7297 0.00923 0.00344 -0.0054 0.1592 0.8873
6.250 0.7550 0.00943 0.00363 -0.0050 0.1493 0.8914
6.500 0.7802 0.00966 0.00384 -0.0046 0.1386 0.8957
6.750 0.8048 0.00991 0.00406 -0.0042 0.1278 0.8996
7.000 0.8288 0.01018 0.00430 -0.0036 0.1172 0.9037
7.250 0.8525 0.01047 0.00456 -0.0030 0.1052 0.9084
7.750 0.9000 0.01099 0.00508 -0.0019 0.0895 0.9176
8.000 0.9229 0.01129 0.00536 -0.0011 0.0812 0.9229
8.500 0.9675 0.01191 0.00597 0.0005 0.0666 0.9341
8.750 0.9894 0.01221 0.00629 0.0014 0.0601 0.9409
9.000 1.0104 0.01256 0.00664 0.0024 0.0534 0.9484
9.500 1.0555 0.01329 0.00738 0.0037 0.0427 0.9670
9.750 1.0819 0.01377 0.00785 0.0034 0.0368 0.9762
10.000 1.1104 0.01427 0.00834 0.0025 0.0311 0.9857
10.250 1.1380 0.01481 0.00887 0.0018 0.0264 1.0000
10.500 1.1552 0.01532 0.00936 0.0032 0.0223 1.0000
10.750 1.1729 0.01578 0.00983 0.0046 0.0196 1.0000
11.000 1.1880 0.01631 0.01036 0.0064 0.0168 1.0000
11.250 1.2023 0.01678 0.01085 0.0083 0.0154 1.0000
11.500 1.2162 0.01727 0.01139 0.0103 0.0140 1.0000
11.750 1.2280 0.01789 0.01202 0.0125 0.0121 1.0000
12.000 1.2410 0.01847 0.01263 0.0143 0.0110 1.0000
12.250 1.2528 0.01914 0.01333 0.0163 0.0096 1.0000
12.500 1.2633 0.01991 0.01413 0.0182 0.0083 1.0000
12.750 1.2735 0.02071 0.01498 0.0200 0.0072 1.0000
13.000 1.2825 0.02164 0.01594 0.0218 0.0063 1.0000
13.250 1.2919 0.02257 0.01693 0.0234 0.0056 1.0000
13.500 1.3009 0.02358 0.01799 0.0248 0.0051 1.0000
13.750 1.3081 0.02477 0.01925 0.0263 0.0046 1.0000
14.000 1.3145 0.02608 0.02061 0.0276 0.0041 1.0000
14.250 1.3210 0.02743 0.02203 0.0287 0.0036 1.0000
14.500 1.3259 0.02898 0.02365 0.0298 0.0033 1.0000
14.750 1.3304 0.03065 0.02539 0.0306 0.0031 1.0000
15.000 1.3326 0.03259 0.02740 0.0314 0.0027 1.0000
15.250 1.3357 0.03454 0.02944 0.0318 0.0026 1.0000
15.500 1.3378 0.03669 0.03167 0.0321 0.0025 1.0000
15.750 1.3377 0.03915 0.03421 0.0322 0.0023 1.0000
16.000 1.3367 0.04181 0.03697 0.0321 0.0022 1.0000
16.250 1.3344 0.04477 0.04003 0.0317 0.0021 1.0000
16.500 1.3295 0.04814 0.04350 0.0309 0.0020 1.0000
16.750 1.3244 0.05174 0.04721 0.0299 0.0019 1.0000
17.000 1.3160 0.05596 0.05153 0.0285 0.0018 1.0000
17.250 1.3066 0.06050 0.05619 0.0267 0.0017 1.0000
17.500 1.2962 0.06538 0.06119 0.0246 0.0017 1.0000
17.750 1.2820 0.07103 0.06696 0.0221 0.0017 1.0000
18.000 1.2672 0.07697 0.07303 0.0192 0.0017 1.0000
18.250 1.2523 0.08314 0.07933 0.0162 0.0015 1.0000
18.500 1.2343 0.08998 0.08630 0.0127 0.0016 1.0000
18.750 1.2166 0.09697 0.09341 0.0090 0.0016 1.0000
19.000 1.1950 0.10486 0.10144 0.0048 0.0016 1.0000
19.250 1.1717 0.11330 0.11001 0.0002 0.0016 1.0000
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