EPPLER 485 AIRFOIL (e485-il) Xfoil prediction polar at RE=200,000 Ncrit=5
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Airfoil: EPPLER 485 AIRFOIL (e485-il) Reynolds number: 200,000 Max Cl/Cd: 55.23 at α=7.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e485-il-200000-n5.txt Download as CSV file: xf-e485-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.250 -0.7016 0.08532 0.08143 -0.0302 1.0000 0.0094
-13.000 -0.7298 0.07416 0.07013 -0.0380 1.0000 0.0092
-12.750 -0.7561 0.06507 0.06084 -0.0446 1.0000 0.0092
-12.500 -0.7756 0.05877 0.05435 -0.0485 1.0000 0.0091
-12.250 -0.7948 0.05349 0.04889 -0.0506 1.0000 0.0088
-12.000 -0.8141 0.04889 0.04402 -0.0513 1.0000 0.0090
-11.750 -0.8279 0.04529 0.04020 -0.0507 1.0000 0.0089
-11.500 -0.8392 0.04223 0.03686 -0.0492 1.0000 0.0092
-11.250 -0.8487 0.03942 0.03374 -0.0470 1.0000 0.0094
-10.750 -0.8568 0.03517 0.02906 -0.0415 1.0000 0.0099
-10.500 -0.8554 0.03374 0.02752 -0.0385 1.0000 0.0102
-10.250 -0.8521 0.03233 0.02597 -0.0356 1.0000 0.0104
-10.000 -0.8451 0.03092 0.02441 -0.0331 1.0000 0.0107
-9.750 -0.8364 0.02951 0.02284 -0.0307 1.0000 0.0110
-9.500 -0.8265 0.02814 0.02131 -0.0283 1.0000 0.0115
-9.250 -0.8154 0.02686 0.01986 -0.0259 1.0000 0.0120
-9.000 -0.8036 0.02563 0.01841 -0.0235 1.0000 0.0127
-8.750 -0.7923 0.02451 0.01719 -0.0211 1.0000 0.0134
-8.500 -0.7798 0.02376 0.01643 -0.0189 1.0000 0.0144
-8.250 -0.7668 0.02302 0.01563 -0.0166 1.0000 0.0154
-8.000 -0.7546 0.02225 0.01474 -0.0141 1.0000 0.0168
-7.750 -0.7455 0.02136 0.01378 -0.0110 1.0000 0.0178
-7.500 -0.7142 0.02035 0.01272 -0.0125 0.9940 0.0196
-7.250 -0.6827 0.01954 0.01178 -0.0138 0.9872 0.0225
-7.000 -0.6515 0.01866 0.01089 -0.0152 0.9804 0.0260
-6.750 -0.6206 0.01792 0.01008 -0.0163 0.9726 0.0307
-6.500 -0.5899 0.01723 0.00936 -0.0173 0.9647 0.0362
-6.250 -0.5586 0.01651 0.00862 -0.0185 0.9570 0.0430
-6.000 -0.5288 0.01591 0.00800 -0.0192 0.9478 0.0522
-5.750 -0.4961 0.01532 0.00743 -0.0206 0.9408 0.0652
-5.500 -0.4667 0.01478 0.00692 -0.0212 0.9312 0.0815
-5.250 -0.4366 0.01425 0.00643 -0.0220 0.9225 0.1026
-5.000 -0.4075 0.01373 0.00600 -0.0225 0.9134 0.1307
-4.750 -0.3813 0.01322 0.00561 -0.0225 0.9030 0.1673
-4.500 -0.3555 0.01269 0.00525 -0.0224 0.8934 0.2138
-4.250 -0.3317 0.01216 0.00490 -0.0218 0.8832 0.2691
-4.000 -0.3099 0.01165 0.00462 -0.0209 0.8724 0.3324
-3.750 -0.2888 0.01113 0.00436 -0.0197 0.8624 0.4036
-3.500 -0.2681 0.01064 0.00415 -0.0183 0.8528 0.4801
-3.250 -0.2474 0.01026 0.00402 -0.0168 0.8424 0.5524
-3.000 -0.2246 0.01001 0.00397 -0.0155 0.8332 0.6170
-2.750 -0.2003 0.00989 0.00398 -0.0143 0.8239 0.6675
-2.500 -0.1753 0.00986 0.00399 -0.0134 0.8142 0.7049
-2.250 -0.1493 0.00987 0.00399 -0.0125 0.8052 0.7326
-2.000 -0.1234 0.00991 0.00401 -0.0117 0.7952 0.7545
-1.750 -0.0975 0.00996 0.00403 -0.0109 0.7852 0.7731
-1.500 -0.0713 0.01003 0.00402 -0.0102 0.7756 0.7890
-1.250 -0.0453 0.01009 0.00404 -0.0095 0.7650 0.8027
-1.000 -0.0193 0.01016 0.00407 -0.0088 0.7544 0.8152
-0.750 0.0066 0.01023 0.00407 -0.0080 0.7441 0.8268
-0.500 0.0322 0.01029 0.00406 -0.0073 0.7332 0.8374
-0.250 0.0588 0.01036 0.00410 -0.0067 0.7215 0.8452
0.000 0.0840 0.01040 0.00407 -0.0059 0.7095 0.8544
0.250 0.1110 0.01047 0.00410 -0.0054 0.6973 0.8609
0.500 0.1359 0.01051 0.00407 -0.0047 0.6845 0.8692
0.750 0.1631 0.01058 0.00409 -0.0042 0.6712 0.8747
1.000 0.1880 0.01062 0.00407 -0.0035 0.6574 0.8821
1.250 0.2150 0.01068 0.00408 -0.0031 0.6429 0.8871
1.500 0.2412 0.01075 0.00410 -0.0026 0.6277 0.8928
1.750 0.2660 0.01080 0.00409 -0.0019 0.6119 0.8992
2.000 0.2936 0.01088 0.00412 -0.0018 0.5950 0.9034
2.250 0.3193 0.01095 0.00415 -0.0012 0.5775 0.9090
2.500 0.3446 0.01104 0.00418 -0.0007 0.5595 0.9145
2.750 0.3724 0.01116 0.00423 -0.0006 0.5404 0.9185
3.000 0.3980 0.01127 0.00429 -0.0002 0.5212 0.9239
3.250 0.4236 0.01139 0.00436 0.0003 0.5010 0.9291
3.750 0.4786 0.01172 0.00456 0.0002 0.4589 0.9379
4.000 0.5037 0.01190 0.00469 0.0006 0.4375 0.9432
4.250 0.5337 0.01212 0.00484 0.0000 0.4149 0.9466
4.500 0.5615 0.01235 0.00501 -0.0002 0.3930 0.9510
4.750 0.5865 0.01257 0.00519 0.0001 0.3723 0.9567
5.000 0.6178 0.01285 0.00541 -0.0009 0.3503 0.9596
5.250 0.6475 0.01314 0.00565 -0.0016 0.3295 0.9634
5.500 0.6748 0.01342 0.00589 -0.0019 0.3097 0.9683
5.750 0.7044 0.01375 0.00618 -0.0027 0.2899 0.9720
6.000 0.7358 0.01409 0.00649 -0.0039 0.2706 0.9752
6.250 0.7656 0.01444 0.00682 -0.0048 0.2521 0.9792
6.500 0.7943 0.01481 0.00718 -0.0054 0.2346 0.9836
6.750 0.8254 0.01521 0.00756 -0.0067 0.2178 0.9869
7.000 0.8548 0.01564 0.00796 -0.0076 0.2016 0.9912
7.250 0.8840 0.01608 0.00839 -0.0086 0.1864 0.9957
7.500 0.9130 0.01653 0.00887 -0.0095 0.1715 1.0000
7.750 0.9236 0.01688 0.00923 -0.0066 0.1609 1.0000
8.000 0.9342 0.01723 0.00960 -0.0038 0.1510 1.0000
8.250 0.9449 0.01764 0.01000 -0.0010 0.1413 1.0000
8.750 0.9706 0.01856 0.01092 0.0037 0.1215 1.0000
9.000 0.9852 0.01908 0.01147 0.0056 0.1122 1.0000
9.250 0.9992 0.01967 0.01205 0.0075 0.1034 1.0000
9.500 1.0144 0.02024 0.01266 0.0092 0.0949 1.0000
9.750 1.0282 0.02087 0.01332 0.0110 0.0877 1.0000
10.000 1.0399 0.02154 0.01400 0.0132 0.0805 1.0000
10.250 1.0517 0.02222 0.01474 0.0153 0.0746 1.0000
10.500 1.0621 0.02301 0.01557 0.0174 0.0684 1.0000
10.750 1.0730 0.02382 0.01646 0.0193 0.0633 1.0000
11.000 1.0830 0.02473 0.01741 0.0211 0.0580 1.0000
11.250 1.0915 0.02577 0.01850 0.0229 0.0535 1.0000
11.500 1.1014 0.02678 0.01960 0.0244 0.0490 1.0000
11.750 1.1070 0.02810 0.02095 0.0260 0.0454 1.0000
12.000 1.1152 0.02933 0.02229 0.0274 0.0421 1.0000
12.250 1.1220 0.03070 0.02376 0.0286 0.0391 1.0000
12.500 1.1251 0.03242 0.02554 0.0297 0.0361 1.0000
12.750 1.1295 0.03413 0.02736 0.0307 0.0338 1.0000
13.000 1.1346 0.03586 0.02922 0.0314 0.0313 1.0000
13.250 1.1363 0.03796 0.03140 0.0319 0.0291 1.0000
13.500 1.1335 0.04059 0.03408 0.0322 0.0275 1.0000
13.750 1.1358 0.04287 0.03653 0.0324 0.0257 1.0000
14.000 1.1372 0.04534 0.03912 0.0322 0.0237 1.0000
14.250 1.1339 0.04843 0.04232 0.0318 0.0227 1.0000
14.500 1.1278 0.05200 0.04598 0.0309 0.0215 1.0000
14.750 1.1215 0.05579 0.04989 0.0298 0.0205 1.0000
15.000 1.1171 0.05950 0.05377 0.0285 0.0194 1.0000
15.250 1.1101 0.06376 0.05817 0.0269 0.0185 1.0000
15.500 1.1020 0.06838 0.06293 0.0249 0.0178 1.0000
15.750 1.0926 0.07339 0.06807 0.0225 0.0173 1.0000
16.000 1.0815 0.07887 0.07368 0.0198 0.0168 1.0000
16.250 1.0678 0.08501 0.07992 0.0166 0.0163 1.0000
16.500 1.0536 0.09135 0.08638 0.0134 0.0160 1.0000
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