EPPLER 485 AIRFOIL (e485-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 485 AIRFOIL (e485-il) Reynolds number: 100,000 Max Cl/Cd: 44.45 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e485-il-100000-n5.txt Download as CSV file: xf-e485-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.000 -0.5948 0.09404 0.08893 -0.0280 1.0000 0.0218
-11.750 -0.6166 0.08353 0.07842 -0.0347 1.0000 0.0212
-11.500 -0.6489 0.07279 0.06757 -0.0425 1.0000 0.0201
-11.250 -0.6769 0.06558 0.06019 -0.0471 1.0000 0.0200
-11.000 -0.7041 0.05990 0.05432 -0.0489 1.0000 0.0198
-10.750 -0.7251 0.05578 0.04998 -0.0486 1.0000 0.0198
-10.500 -0.7441 0.05222 0.04622 -0.0469 1.0000 0.0198
-10.250 -0.7589 0.04942 0.04317 -0.0440 1.0000 0.0200
-10.000 -0.7709 0.04677 0.04027 -0.0405 1.0000 0.0203
-9.750 -0.7773 0.04395 0.03713 -0.0374 1.0000 0.0207
-9.500 -0.7799 0.04109 0.03390 -0.0342 1.0000 0.0213
-9.250 -0.7773 0.03841 0.03084 -0.0314 1.0000 0.0218
-9.000 -0.7711 0.03583 0.02781 -0.0286 1.0000 0.0226
-8.750 -0.7609 0.03373 0.02556 -0.0264 1.0000 0.0233
-8.500 -0.7495 0.03228 0.02404 -0.0243 1.0000 0.0245
-8.250 -0.7372 0.03114 0.02277 -0.0222 1.0000 0.0263
-8.000 -0.7234 0.02973 0.02110 -0.0200 1.0000 0.0288
-7.750 -0.7102 0.02822 0.01950 -0.0178 1.0000 0.0307
-7.500 -0.6977 0.02717 0.01841 -0.0156 1.0000 0.0329
-7.250 -0.6846 0.02624 0.01736 -0.0133 1.0000 0.0364
-7.000 -0.6732 0.02513 0.01618 -0.0106 1.0000 0.0395
-6.750 -0.6632 0.02426 0.01531 -0.0079 1.0000 0.0426
-6.500 -0.6523 0.02355 0.01449 -0.0051 1.0000 0.0473
-6.250 -0.6360 0.02265 0.01362 -0.0037 0.9978 0.0530
-6.000 -0.6040 0.02166 0.01255 -0.0052 0.9905 0.0633
-5.750 -0.5714 0.02074 0.01164 -0.0068 0.9834 0.0769
-5.500 -0.5412 0.01991 0.01083 -0.0079 0.9750 0.0950
-5.250 -0.5093 0.01909 0.01012 -0.0094 0.9678 0.1207
-5.000 -0.4793 0.01832 0.00949 -0.0104 0.9595 0.1574
-4.750 -0.4491 0.01750 0.00892 -0.0115 0.9519 0.2123
-4.500 -0.4193 0.01667 0.00843 -0.0125 0.9442 0.2863
-4.250 -0.3926 0.01585 0.00803 -0.0128 0.9360 0.3788
-4.000 -0.3651 0.01512 0.00776 -0.0129 0.9284 0.4842
-3.750 -0.3390 0.01471 0.00775 -0.0121 0.9198 0.5794
-3.500 -0.3061 0.01463 0.00787 -0.0122 0.9133 0.6557
-3.250 -0.2766 0.01471 0.00797 -0.0118 0.9045 0.7047
-3.000 -0.2423 0.01486 0.00805 -0.0121 0.8977 0.7399
-2.750 -0.2141 0.01501 0.00813 -0.0115 0.8880 0.7668
-2.500 -0.1804 0.01518 0.00819 -0.0118 0.8808 0.7885
-2.250 -0.1534 0.01533 0.00823 -0.0110 0.8706 0.8074
-2.000 -0.1246 0.01547 0.00827 -0.0105 0.8611 0.8236
-1.750 -0.0911 0.01563 0.00832 -0.0108 0.8528 0.8367
-1.500 -0.0600 0.01579 0.00839 -0.0108 0.8424 0.8480
-1.250 -0.0286 0.01587 0.00837 -0.0109 0.8328 0.8586
-1.000 -0.0002 0.01589 0.00830 -0.0106 0.8227 0.8695
-0.750 0.0338 0.01596 0.00829 -0.0113 0.8114 0.8768
-0.500 0.0622 0.01596 0.00822 -0.0111 0.8001 0.8858
-0.250 0.0966 0.01597 0.00814 -0.0120 0.7894 0.8923
0.000 0.1250 0.01594 0.00804 -0.0119 0.7778 0.9002
0.250 0.1591 0.01593 0.00798 -0.0129 0.7650 0.9057
0.500 0.1848 0.01589 0.00789 -0.0124 0.7520 0.9138
0.750 0.2208 0.01586 0.00780 -0.0138 0.7385 0.9181
1.000 0.2502 0.01582 0.00772 -0.0140 0.7246 0.9246
1.250 0.2814 0.01577 0.00763 -0.0146 0.7101 0.9299
1.500 0.3162 0.01572 0.00754 -0.0160 0.6945 0.9342
1.750 0.3433 0.01569 0.00747 -0.0158 0.6789 0.9407
2.000 0.3769 0.01564 0.00741 -0.0169 0.6621 0.9449
2.250 0.4102 0.01561 0.00732 -0.0180 0.6445 0.9492
2.500 0.4375 0.01561 0.00729 -0.0180 0.6266 0.9552
2.750 0.4703 0.01560 0.00728 -0.0191 0.6063 0.9592
3.000 0.5024 0.01561 0.00724 -0.0200 0.5858 0.9636
3.250 0.5300 0.01567 0.00727 -0.0201 0.5650 0.9692
3.500 0.5623 0.01572 0.00729 -0.0212 0.5421 0.9732
3.750 0.5932 0.01581 0.00734 -0.0220 0.5186 0.9777
4.000 0.6212 0.01596 0.00742 -0.0223 0.4953 0.9829
4.250 0.6533 0.01609 0.00754 -0.0234 0.4697 0.9868
4.500 0.6830 0.01629 0.00768 -0.0242 0.4448 0.9915
4.750 0.7128 0.01652 0.00785 -0.0250 0.4202 0.9960
5.000 0.7414 0.01678 0.00808 -0.0256 0.3953 1.0000
5.250 0.7573 0.01708 0.00835 -0.0237 0.3757 1.0000
5.500 0.7730 0.01739 0.00864 -0.0217 0.3559 1.0000
5.750 0.7879 0.01773 0.00896 -0.0196 0.3373 1.0000
6.000 0.8022 0.01810 0.00929 -0.0174 0.3199 1.0000
6.250 0.8157 0.01849 0.00967 -0.0151 0.3030 1.0000
6.500 0.8290 0.01888 0.01006 -0.0128 0.2870 1.0000
6.750 0.8417 0.01929 0.01047 -0.0103 0.2714 1.0000
7.000 0.8539 0.01973 0.01090 -0.0078 0.2565 1.0000
7.250 0.8659 0.02018 0.01136 -0.0052 0.2425 1.0000
7.500 0.8777 0.02067 0.01183 -0.0027 0.2289 1.0000
7.750 0.8897 0.02118 0.01237 -0.0002 0.2158 1.0000
8.000 0.9025 0.02170 0.01292 0.0021 0.2029 1.0000
8.250 0.9157 0.02227 0.01352 0.0043 0.1900 1.0000
8.500 0.9294 0.02288 0.01416 0.0063 0.1780 1.0000
8.750 0.9430 0.02354 0.01485 0.0083 0.1664 1.0000
9.000 0.9560 0.02424 0.01559 0.0102 0.1554 1.0000
9.250 0.9680 0.02501 0.01636 0.0122 0.1451 1.0000
9.500 0.9812 0.02577 0.01721 0.0140 0.1345 1.0000
9.750 0.9927 0.02660 0.01810 0.0160 0.1251 1.0000
10.000 1.0002 0.02752 0.01898 0.0185 0.1174 1.0000
10.250 1.0104 0.02841 0.02001 0.0205 0.1086 1.0000
10.500 1.0177 0.02947 0.02110 0.0226 0.1015 1.0000
10.750 1.0258 0.03057 0.02230 0.0245 0.0945 1.0000
11.000 1.0321 0.03185 0.02366 0.0263 0.0883 1.0000
11.250 1.0388 0.03316 0.02508 0.0279 0.0822 1.0000
11.500 1.0427 0.03471 0.02665 0.0295 0.0777 1.0000
11.750 1.0488 0.03625 0.02836 0.0307 0.0721 1.0000
12.000 1.0510 0.03803 0.03019 0.0319 0.0680 1.0000
12.250 1.0543 0.03995 0.03224 0.0329 0.0640 1.0000
12.500 1.0569 0.04198 0.03443 0.0336 0.0600 1.0000
12.750 1.0565 0.04427 0.03678 0.0341 0.0568 1.0000
13.000 1.0560 0.04677 0.03936 0.0344 0.0540 1.0000
13.250 1.0558 0.04941 0.04222 0.0346 0.0508 1.0000
13.500 1.0538 0.05225 0.04522 0.0343 0.0483 1.0000
13.750 1.0490 0.05547 0.04851 0.0337 0.0460 1.0000
14.000 1.0447 0.05885 0.05196 0.0330 0.0441 1.0000
14.250 1.0394 0.06263 0.05600 0.0320 0.0423 1.0000
14.500 1.0326 0.06672 0.06028 0.0306 0.0405 1.0000
14.750 1.0246 0.07111 0.06481 0.0288 0.0390 1.0000
15.000 1.0161 0.07576 0.06958 0.0267 0.0377 1.0000
15.250 1.0075 0.08057 0.07448 0.0244 0.0365 1.0000
15.500 0.9991 0.08546 0.07940 0.0221 0.0353 1.0000
15.750 0.9852 0.09183 0.08601 0.0188 0.0346 1.0000
16.000 0.9688 0.09895 0.09334 0.0148 0.0341 1.0000
16.250 0.9493 0.10700 0.10160 0.0103 0.0336 1.0000
16.500 0.9267 0.11614 0.11091 0.0051 0.0335 1.0000
16.750 0.8998 0.12673 0.12166 -0.0009 0.0338 1.0000
17.000 0.8605 0.14128 0.13630 -0.0090 0.0344 1.0000
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