EPPLER 485 AIRFOIL (e485-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 485 AIRFOIL (e485-il) Reynolds number: 200,000 Max Cl/Cd: 59.22 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e485-il-200000.txt Download as CSV file: xf-e485-il-200000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.4714 0.08703 0.08373 -0.0317 1.0000 0.0351
-11.000 -0.6414 0.06870 0.06489 -0.0482 1.0000 0.0289
-10.750 -0.6617 0.06372 0.05983 -0.0498 1.0000 0.0286
-10.500 -0.6837 0.05960 0.05556 -0.0499 1.0000 0.0285
-10.250 -0.7011 0.05585 0.05172 -0.0486 1.0000 0.0276
-10.000 -0.7219 0.05251 0.04823 -0.0457 1.0000 0.0269
-9.750 -0.7426 0.04917 0.04469 -0.0415 1.0000 0.0263
-9.500 -0.7602 0.04518 0.04037 -0.0374 1.0000 0.0258
-9.250 -0.7922 0.03862 0.03288 -0.0302 1.0000 0.0236
-9.000 -0.7910 0.03571 0.02965 -0.0268 1.0000 0.0236
-8.750 -0.7857 0.03316 0.02680 -0.0237 1.0000 0.0238
-8.500 -0.7770 0.03103 0.02447 -0.0210 1.0000 0.0243
-8.250 -0.7666 0.02927 0.02252 -0.0184 1.0000 0.0249
-8.000 -0.7554 0.02780 0.02090 -0.0157 1.0000 0.0261
-7.750 -0.7446 0.02653 0.01945 -0.0128 1.0000 0.0274
-7.500 -0.7360 0.02608 0.01877 -0.0095 1.0000 0.0294
-7.250 -0.7255 0.02384 0.01643 -0.0068 1.0000 0.0312
-7.000 -0.7156 0.02291 0.01547 -0.0040 1.0000 0.0331
-6.750 -0.7048 0.02206 0.01454 -0.0012 1.0000 0.0356
-6.500 -0.6932 0.02123 0.01357 0.0015 1.0000 0.0388
-6.250 -0.6589 0.02004 0.01242 -0.0005 0.9959 0.0452
-6.000 -0.6236 0.01884 0.01122 -0.0025 0.9908 0.0536
-5.750 -0.5878 0.01775 0.01011 -0.0045 0.9853 0.0643
-5.500 -0.5528 0.01688 0.00929 -0.0065 0.9795 0.0806
-5.250 -0.5185 0.01597 0.00849 -0.0083 0.9731 0.1045
-5.000 -0.4839 0.01510 0.00782 -0.0103 0.9673 0.1432
-4.750 -0.4532 0.01412 0.00721 -0.0116 0.9599 0.2098
-4.500 -0.4191 0.01303 0.00669 -0.0138 0.9552 0.3227
-4.250 -0.3948 0.01209 0.00632 -0.0136 0.9461 0.4451
-4.000 -0.3613 0.01131 0.00611 -0.0148 0.9418 0.5756
-3.750 -0.3349 0.01105 0.00614 -0.0140 0.9330 0.6586
-3.500 -0.2983 0.01098 0.00618 -0.0150 0.9280 0.7149
-3.250 -0.2691 0.01106 0.00625 -0.0146 0.9196 0.7504
-3.000 -0.2350 0.01116 0.00631 -0.0150 0.9134 0.7776
-2.750 -0.2066 0.01135 0.00647 -0.0142 0.9044 0.7977
-2.500 -0.1743 0.01154 0.00659 -0.0141 0.8976 0.8148
-2.250 -0.1484 0.01176 0.00675 -0.0128 0.8873 0.8293
-2.000 -0.1197 0.01196 0.00687 -0.0120 0.8790 0.8424
-1.750 -0.0934 0.01213 0.00697 -0.0108 0.8691 0.8551
-1.500 -0.0652 0.01235 0.00713 -0.0100 0.8590 0.8653
-1.250 -0.0332 0.01253 0.00722 -0.0098 0.8504 0.8740
-1.000 -0.0076 0.01264 0.00727 -0.0087 0.8395 0.8848
-0.750 0.0283 0.01283 0.00739 -0.0095 0.8293 0.8914
-0.500 0.0575 0.01288 0.00736 -0.0092 0.8191 0.9002
-0.250 0.0968 0.01297 0.00737 -0.0109 0.8084 0.9053
0.000 0.1231 0.01297 0.00732 -0.0103 0.7962 0.9141
0.250 0.1658 0.01300 0.00729 -0.0129 0.7844 0.9177
0.500 0.2027 0.01299 0.00722 -0.0144 0.7722 0.9233
0.750 0.2345 0.01294 0.00710 -0.0150 0.7597 0.9295
1.000 0.2762 0.01289 0.00698 -0.0176 0.7464 0.9331
1.250 0.3064 0.01285 0.00689 -0.0180 0.7324 0.9396
1.500 0.3404 0.01277 0.00676 -0.0192 0.7175 0.9444
1.750 0.3779 0.01271 0.00665 -0.0211 0.7015 0.9486
2.000 0.4042 0.01267 0.00659 -0.0209 0.6849 0.9554
2.250 0.4408 0.01259 0.00647 -0.0227 0.6665 0.9591
2.500 0.4762 0.01253 0.00638 -0.0243 0.6475 0.9635
2.750 0.5034 0.01253 0.00631 -0.0242 0.6289 0.9695
3.000 0.5398 0.01246 0.00620 -0.0262 0.6065 0.9731
3.250 0.5736 0.01245 0.00611 -0.0276 0.5840 0.9774
3.500 0.6020 0.01250 0.00612 -0.0279 0.5599 0.9828
3.750 0.6380 0.01248 0.00603 -0.0298 0.5336 0.9862
4.000 0.6709 0.01254 0.00601 -0.0312 0.5070 0.9905
4.250 0.7026 0.01265 0.00602 -0.0323 0.4796 0.9946
4.500 0.7363 0.01275 0.00604 -0.0340 0.4510 0.9985
4.750 0.7605 0.01293 0.00616 -0.0337 0.4251 1.0000
5.000 0.7781 0.01317 0.00634 -0.0321 0.4020 1.0000
5.250 0.7952 0.01343 0.00653 -0.0304 0.3796 1.0000
5.500 0.8119 0.01371 0.00675 -0.0287 0.3583 1.0000
5.750 0.8283 0.01400 0.00699 -0.0269 0.3377 1.0000
6.000 0.8438 0.01433 0.00726 -0.0249 0.3187 1.0000
6.250 0.8591 0.01465 0.00755 -0.0229 0.3005 1.0000
6.500 0.8737 0.01498 0.00786 -0.0208 0.2827 1.0000
6.750 0.8873 0.01534 0.00820 -0.0185 0.2664 1.0000
7.000 0.9000 0.01572 0.00856 -0.0160 0.2510 1.0000
7.250 0.9117 0.01611 0.00894 -0.0133 0.2363 1.0000
7.500 0.9225 0.01651 0.00933 -0.0105 0.2224 1.0000
7.750 0.9323 0.01692 0.00973 -0.0075 0.2093 1.0000
8.000 0.9415 0.01736 0.01014 -0.0044 0.1969 1.0000
8.250 0.9509 0.01783 0.01058 -0.0013 0.1847 1.0000
8.500 0.9610 0.01836 0.01106 0.0015 0.1728 1.0000
8.750 0.9738 0.01885 0.01157 0.0038 0.1604 1.0000
9.000 0.9876 0.01941 0.01216 0.0059 0.1484 1.0000
9.250 1.0013 0.02004 0.01282 0.0079 0.1371 1.0000
9.500 1.0143 0.02077 0.01353 0.0099 0.1268 1.0000
9.750 1.0257 0.02162 0.01431 0.0121 0.1173 1.0000
10.000 1.0381 0.02223 0.01502 0.0142 0.1080 1.0000
10.250 1.0478 0.02311 0.01592 0.0166 0.1001 1.0000
10.500 1.0563 0.02403 0.01684 0.0189 0.0926 1.0000
10.750 1.0666 0.02495 0.01787 0.0209 0.0854 1.0000
11.000 1.0731 0.02623 0.01906 0.0231 0.0789 1.0000
11.250 1.0831 0.02716 0.02017 0.0249 0.0730 1.0000
11.500 1.0890 0.02848 0.02145 0.0267 0.0677 1.0000
11.750 1.0970 0.02982 0.02294 0.0283 0.0629 1.0000
12.000 1.1034 0.03110 0.02430 0.0297 0.0585 1.0000
12.250 1.1081 0.03301 0.02619 0.0312 0.0545 1.0000
12.500 1.1133 0.03448 0.02786 0.0324 0.0507 1.0000
12.750 1.1172 0.03617 0.02963 0.0333 0.0475 1.0000
13.000 1.1193 0.03844 0.03190 0.0344 0.0442 1.0000
13.250 1.1211 0.04043 0.03412 0.0350 0.0415 1.0000
13.500 1.1226 0.04256 0.03635 0.0355 0.0389 1.0000
13.750 1.1220 0.04505 0.03883 0.0358 0.0365 1.0000
14.000 1.1196 0.04796 0.04189 0.0359 0.0343 1.0000
14.250 1.1176 0.05087 0.04501 0.0358 0.0327 1.0000
14.500 1.1146 0.05392 0.04819 0.0353 0.0308 1.0000
14.750 1.1118 0.05699 0.05129 0.0344 0.0292 1.0000
15.000 1.1054 0.06092 0.05525 0.0342 0.0274 1.0000
15.250 1.0970 0.06509 0.05967 0.0326 0.0266 1.0000
15.500 1.0883 0.06956 0.06434 0.0307 0.0257 1.0000
15.750 1.0791 0.07433 0.06929 0.0284 0.0247 1.0000
16.000 1.0702 0.07924 0.07436 0.0260 0.0239 1.0000
16.250 1.0627 0.08406 0.07926 0.0234 0.0229 1.0000
16.500 1.0548 0.08910 0.08439 0.0209 0.0223 1.0000
16.750 1.0457 0.09446 0.08985 0.0182 0.0218 1.0000
17.000 1.0322 0.10081 0.09634 0.0149 0.0214 1.0000
17.250 1.0161 0.10799 0.10369 0.0109 0.0213 1.0000
17.500 0.9974 0.11602 0.11190 0.0061 0.0212 1.0000
17.750 0.9756 0.12515 0.12122 0.0005 0.0212 1.0000
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