EPPLER 485 AIRFOIL (e485-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 485 AIRFOIL (e485-il) Reynolds number: 50,000 Max Cl/Cd: 30.9 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e485-il-50000-n5.txt Download as CSV file: xf-e485-il-50000-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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.5648 0.09574 0.08864 -0.0304 1.0000 0.0448
-11.000 -0.5819 0.08727 0.08021 -0.0359 1.0000 0.0443
-10.750 -0.6048 0.07949 0.07241 -0.0410 1.0000 0.0432
-10.500 -0.6309 0.07305 0.06589 -0.0444 1.0000 0.0424
-10.250 -0.6560 0.06797 0.06069 -0.0455 1.0000 0.0420
-10.000 -0.6784 0.06394 0.05650 -0.0446 1.0000 0.0417
-9.750 -0.6974 0.06061 0.05301 -0.0422 1.0000 0.0417
-9.500 -0.7101 0.05732 0.04950 -0.0397 1.0000 0.0422
-9.250 -0.7173 0.05430 0.04623 -0.0373 1.0000 0.0430
-9.000 -0.7220 0.05128 0.04289 -0.0346 1.0000 0.0445
-8.750 -0.7238 0.04826 0.03946 -0.0318 1.0000 0.0462
-8.500 -0.7227 0.04521 0.03585 -0.0288 1.0000 0.0480
-8.250 -0.7131 0.04262 0.03312 -0.0268 1.0000 0.0497
-8.000 -0.7013 0.04046 0.03079 -0.0249 1.0000 0.0522
-7.750 -0.6890 0.03851 0.02858 -0.0228 1.0000 0.0563
-7.500 -0.6739 0.03638 0.02608 -0.0207 1.0000 0.0606
-7.250 -0.6579 0.03471 0.02442 -0.0191 1.0000 0.0653
-7.000 -0.6400 0.03314 0.02252 -0.0173 1.0000 0.0726
-6.750 -0.6234 0.03169 0.02117 -0.0157 1.0000 0.0795
-6.500 -0.6062 0.03039 0.01979 -0.0139 1.0000 0.0892
-6.250 -0.5892 0.02922 0.01849 -0.0120 1.0000 0.1005
-6.000 -0.5747 0.02817 0.01746 -0.0099 1.0000 0.1143
-5.750 -0.5619 0.02715 0.01652 -0.0076 1.0000 0.1307
-5.500 -0.5504 0.02620 0.01564 -0.0051 1.0000 0.1518
-5.250 -0.5403 0.02525 0.01485 -0.0026 1.0000 0.1788
-5.000 -0.5309 0.02432 0.01410 0.0001 1.0000 0.2145
-4.750 -0.5231 0.02334 0.01346 0.0029 1.0000 0.2641
-4.500 -0.5158 0.02239 0.01289 0.0058 1.0000 0.3335
-4.250 -0.5091 0.02150 0.01255 0.0091 1.0000 0.4260
-4.000 -0.5006 0.02097 0.01263 0.0130 1.0000 0.5334
-3.750 -0.4750 0.02118 0.01323 0.0150 0.9956 0.6483
-3.500 -0.4392 0.02183 0.01386 0.0152 0.9875 0.7265
-3.250 -0.4036 0.02250 0.01429 0.0150 0.9790 0.7789
-3.000 -0.3614 0.02328 0.01484 0.0138 0.9717 0.8159
-2.750 -0.3178 0.02392 0.01520 0.0120 0.9643 0.8456
-2.500 -0.2686 0.02443 0.01545 0.0088 0.9578 0.8706
-2.250 -0.2124 0.02480 0.01556 0.0040 0.9518 0.8896
-2.000 -0.1539 0.02497 0.01546 -0.0017 0.9456 0.9054
-1.750 -0.0952 0.02497 0.01525 -0.0078 0.9393 0.9182
-1.500 -0.0426 0.02488 0.01498 -0.0130 0.9308 0.9300
-1.250 0.0130 0.02471 0.01466 -0.0187 0.9230 0.9400
-1.000 0.0692 0.02445 0.01426 -0.0247 0.9144 0.9479
-0.750 0.1160 0.02422 0.01395 -0.0289 0.9035 0.9569
-0.500 0.1699 0.02386 0.01351 -0.0343 0.8934 0.9634
-0.250 0.2171 0.02356 0.01315 -0.0384 0.8821 0.9707
0.000 0.2631 0.02320 0.01276 -0.0423 0.8685 0.9772
0.250 0.3046 0.02291 0.01244 -0.0452 0.8541 0.9840
0.500 0.3461 0.02257 0.01209 -0.0481 0.8390 0.9903
0.750 0.3850 0.02227 0.01179 -0.0504 0.8233 0.9966
1.000 0.4154 0.02208 0.01158 -0.0511 0.8070 1.0000
1.250 0.4339 0.02207 0.01157 -0.0495 0.7889 1.0000
1.500 0.4524 0.02206 0.01158 -0.0479 0.7709 1.0000
1.750 0.4710 0.02204 0.01156 -0.0462 0.7531 1.0000
2.000 0.4898 0.02201 0.01153 -0.0444 0.7356 1.0000
2.250 0.5091 0.02197 0.01149 -0.0427 0.7182 1.0000
2.500 0.5270 0.02199 0.01154 -0.0408 0.6995 1.0000
2.750 0.5447 0.02203 0.01160 -0.0389 0.6803 1.0000
3.000 0.5631 0.02204 0.01162 -0.0370 0.6617 1.0000
3.250 0.5820 0.02203 0.01161 -0.0351 0.6432 1.0000
3.500 0.5985 0.02214 0.01177 -0.0330 0.6226 1.0000
3.750 0.6161 0.02222 0.01186 -0.0310 0.6025 1.0000
4.000 0.6342 0.02230 0.01192 -0.0290 0.5828 1.0000
4.250 0.6502 0.02248 0.01214 -0.0268 0.5611 1.0000
4.500 0.6676 0.02263 0.01228 -0.0247 0.5405 1.0000
4.750 0.6833 0.02287 0.01253 -0.0224 0.5189 1.0000
5.000 0.6994 0.02311 0.01277 -0.0202 0.4978 1.0000
5.250 0.7149 0.02341 0.01305 -0.0179 0.4766 1.0000
5.500 0.7296 0.02376 0.01342 -0.0156 0.4554 1.0000
5.750 0.7450 0.02411 0.01372 -0.0133 0.4355 1.0000
6.000 0.7585 0.02457 0.01421 -0.0109 0.4146 1.0000
6.250 0.7727 0.02504 0.01466 -0.0086 0.3950 1.0000
6.500 0.7871 0.02552 0.01510 -0.0063 0.3763 1.0000
6.750 0.8002 0.02610 0.01574 -0.0039 0.3573 1.0000
7.000 0.8135 0.02670 0.01635 -0.0016 0.3390 1.0000
7.250 0.8272 0.02733 0.01698 0.0006 0.3216 1.0000
7.500 0.8412 0.02800 0.01765 0.0027 0.3048 1.0000
7.750 0.8553 0.02871 0.01835 0.0047 0.2886 1.0000
8.000 0.8691 0.02949 0.01919 0.0067 0.2727 1.0000
8.250 0.8825 0.03032 0.02007 0.0087 0.2570 1.0000
8.500 0.8961 0.03120 0.02100 0.0105 0.2423 1.0000
8.750 0.9091 0.03213 0.02197 0.0124 0.2279 1.0000
9.000 0.9222 0.03310 0.02297 0.0142 0.2146 1.0000
9.250 0.9344 0.03413 0.02408 0.0160 0.2017 1.0000
9.500 0.9451 0.03527 0.02537 0.0179 0.1891 1.0000
9.750 0.9557 0.03651 0.02674 0.0197 0.1776 1.0000
10.000 0.9650 0.03777 0.02809 0.0215 0.1668 1.0000
10.250 0.9744 0.03899 0.02931 0.0234 0.1573 1.0000
10.500 0.9799 0.04045 0.03094 0.0255 0.1480 1.0000
10.750 0.9853 0.04203 0.03265 0.0274 0.1396 1.0000
11.000 0.9917 0.04342 0.03402 0.0291 0.1317 1.0000
11.250 0.9929 0.04553 0.03640 0.0309 0.1244 1.0000
11.500 1.0002 0.04702 0.03788 0.0321 0.1178 1.0000
11.750 0.9954 0.04968 0.04087 0.0335 0.1117 1.0000
12.000 0.9983 0.05170 0.04294 0.0345 0.1062 1.0000
12.250 0.9964 0.05446 0.04588 0.0352 0.1016 1.0000
12.500 0.9876 0.05784 0.04953 0.0355 0.0973 1.0000
12.750 0.9890 0.06014 0.05184 0.0358 0.0927 1.0000
13.000 0.9813 0.06387 0.05574 0.0355 0.0897 1.0000
13.250 0.9618 0.06923 0.06140 0.0340 0.0878 1.0000
13.500 0.9390 0.07549 0.06790 0.0316 0.0867 1.0000
13.750 0.9085 0.08359 0.07621 0.0275 0.0863 1.0000
14.000 0.8642 0.09532 0.08811 0.0207 0.0872 1.0000
14.250 0.8042 0.11263 0.10537 0.0106 0.0885 1.0000
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