EPPLER 664 AIRFOIL (e664-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 664 AIRFOIL (e664-il) Reynolds number: 200,000 Max Cl/Cd: 58.27 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e664-il-200000-n5.txt Download as CSV file: xf-e664-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 664 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
------ -------- --------- --------- -------- -------- --------
-13.000 -0.3473 0.09692 0.09319 -0.0867 0.9398 0.0156
-12.750 -0.3664 0.08384 0.08005 -0.0955 0.9320 0.0153
-12.500 -0.4089 0.06537 0.06129 -0.1118 0.9209 0.0149
-12.250 -0.4310 0.05679 0.05236 -0.1197 0.9071 0.0148
-12.000 -0.4487 0.05105 0.04627 -0.1232 0.8935 0.0147
-11.750 -0.4638 0.04676 0.04162 -0.1240 0.8815 0.0147
-11.500 -0.4782 0.04330 0.03782 -0.1229 0.8708 0.0148
-11.250 -0.4845 0.04071 0.03494 -0.1213 0.8627 0.0147
-11.000 -0.4935 0.03810 0.03198 -0.1188 0.8548 0.0148
-10.750 -0.4955 0.03595 0.02949 -0.1165 0.8487 0.0149
-10.500 -0.4960 0.03388 0.02709 -0.1138 0.8426 0.0150
-10.250 -0.4903 0.03219 0.02512 -0.1117 0.8373 0.0151
-10.000 -0.4830 0.03060 0.02316 -0.1095 0.8329 0.0154
-9.750 -0.4704 0.02923 0.02162 -0.1080 0.8292 0.0158
-9.500 -0.4550 0.02806 0.02035 -0.1069 0.8254 0.0161
-9.250 -0.4390 0.02709 0.01925 -0.1057 0.8219 0.0166
-9.000 -0.4204 0.02611 0.01812 -0.1048 0.8189 0.0171
-8.750 -0.3984 0.02508 0.01693 -0.1044 0.8164 0.0174
-8.500 -0.3747 0.02406 0.01575 -0.1041 0.8141 0.0178
-8.250 -0.3524 0.02316 0.01476 -0.1036 0.8111 0.0182
-8.000 -0.3309 0.02235 0.01385 -0.1029 0.8081 0.0186
-7.750 -0.3102 0.02164 0.01304 -0.1020 0.8052 0.0190
-7.500 -0.2914 0.02091 0.01225 -0.1010 0.8027 0.0195
-7.250 -0.2735 0.02029 0.01160 -0.0998 0.8005 0.0202
-6.750 -0.2388 0.01933 0.01053 -0.0970 0.7959 0.0218
-6.500 -0.2219 0.01895 0.01011 -0.0955 0.7933 0.0237
-6.250 -0.2054 0.01853 0.00968 -0.0940 0.7907 0.0254
-6.000 -0.1871 0.01815 0.00924 -0.0926 0.7881 0.0274
-5.750 -0.1682 0.01774 0.00880 -0.0914 0.7858 0.0301
-5.500 -0.1489 0.01735 0.00839 -0.0902 0.7840 0.0357
-5.250 -0.1297 0.01695 0.00802 -0.0890 0.7823 0.0489
-5.000 -0.1132 0.01657 0.00778 -0.0874 0.7800 0.0735
-4.750 -0.0969 0.01621 0.00758 -0.0859 0.7774 0.1035
-4.500 -0.0805 0.01583 0.00737 -0.0843 0.7748 0.1424
-4.250 -0.0669 0.01528 0.00715 -0.0824 0.7724 0.2103
-4.000 -0.0586 0.01446 0.00685 -0.0798 0.7702 0.3263
-3.750 -0.0533 0.01340 0.00654 -0.0765 0.7680 0.4872
-3.500 -0.0263 0.01461 0.00868 -0.0728 0.7667 0.6791
-3.250 -0.0043 0.01480 0.00877 -0.0719 0.7647 0.7121
-3.000 0.0166 0.01510 0.00901 -0.0707 0.7620 0.7323
-2.750 0.0397 0.01545 0.00927 -0.0696 0.7594 0.7461
-2.500 0.0634 0.01572 0.00945 -0.0689 0.7570 0.7575
-2.250 0.0891 0.01615 0.00980 -0.0681 0.7549 0.7680
-2.000 0.1180 0.01691 0.01051 -0.0670 0.7531 0.7778
-1.750 0.1450 0.01742 0.01094 -0.0662 0.7513 0.7893
-1.500 0.1762 0.01786 0.01132 -0.0660 0.7498 0.7956
-1.250 0.1923 0.01790 0.01133 -0.0643 0.7467 0.8032
-1.000 0.2152 0.01798 0.01139 -0.0634 0.7437 0.8050
-0.750 0.2392 0.01801 0.01138 -0.0628 0.7410 0.8071
-0.500 0.2639 0.01798 0.01131 -0.0625 0.7386 0.8094
-0.250 0.2894 0.01789 0.01116 -0.0624 0.7365 0.8120
0.000 0.3159 0.01776 0.01095 -0.0627 0.7346 0.8150
0.250 0.3401 0.01764 0.01078 -0.0628 0.7322 0.8179
0.500 0.3581 0.01771 0.01089 -0.0611 0.7282 0.8193
0.750 0.3810 0.01770 0.01088 -0.0605 0.7249 0.8206
1.000 0.4072 0.01762 0.01076 -0.0604 0.7218 0.8217
1.250 0.4363 0.01749 0.01060 -0.0609 0.7192 0.8231
1.500 0.4644 0.01740 0.01048 -0.0612 0.7164 0.8245
1.750 0.4806 0.01744 0.01056 -0.0595 0.7112 0.8263
2.000 0.5052 0.01736 0.01049 -0.0593 0.7073 0.8280
2.250 0.5341 0.01722 0.01033 -0.0599 0.7042 0.8297
2.500 0.5668 0.01705 0.01012 -0.0613 0.7016 0.8310
2.750 0.5842 0.01709 0.01022 -0.0600 0.6957 0.8329
3.000 0.6079 0.01701 0.01017 -0.0595 0.6910 0.8337
3.250 0.6372 0.01685 0.01002 -0.0600 0.6875 0.8344
3.500 0.6604 0.01681 0.01001 -0.0593 0.6828 0.8355
3.750 0.6785 0.01682 0.01010 -0.0577 0.6765 0.8369
4.000 0.7073 0.01665 0.00994 -0.0581 0.6719 0.8378
4.250 0.7274 0.01662 0.00997 -0.0570 0.6654 0.8390
4.500 0.7494 0.01654 0.00995 -0.0562 0.6586 0.8401
4.750 0.7757 0.01641 0.00984 -0.0562 0.6527 0.8411
5.000 0.7927 0.01641 0.00992 -0.0545 0.6438 0.8426
5.250 0.8153 0.01633 0.00989 -0.0539 0.6356 0.8440
5.500 0.8375 0.01625 0.00985 -0.0531 0.6261 0.8456
5.750 0.8537 0.01625 0.00990 -0.0514 0.6148 0.8471
6.000 0.8721 0.01620 0.00988 -0.0499 0.6027 0.8482
6.250 0.8905 0.01615 0.00987 -0.0483 0.5892 0.8491
6.500 0.9103 0.01614 0.00986 -0.0470 0.5738 0.8500
6.750 0.9303 0.01619 0.00987 -0.0458 0.5556 0.8510
7.000 0.9496 0.01631 0.00993 -0.0445 0.5350 0.8520
7.250 0.9656 0.01657 0.01014 -0.0427 0.5132 0.8532
7.500 0.9792 0.01695 0.01044 -0.0407 0.4896 0.8548
7.750 0.9907 0.01745 0.01086 -0.0384 0.4651 0.8564
8.000 1.0001 0.01807 0.01139 -0.0360 0.4402 0.8579
8.250 1.0091 0.01878 0.01202 -0.0337 0.4161 0.8593
8.500 1.0170 0.01960 0.01275 -0.0315 0.3928 0.8607
8.750 1.0258 0.02045 0.01354 -0.0295 0.3700 0.8620
9.000 1.0324 0.02140 0.01442 -0.0273 0.3469 0.8632
9.250 1.0383 0.02237 0.01534 -0.0250 0.3249 0.8642
9.500 1.0446 0.02340 0.01632 -0.0228 0.3030 0.8655
9.750 1.0503 0.02451 0.01737 -0.0207 0.2824 0.8669
10.000 1.0574 0.02561 0.01843 -0.0189 0.2617 0.8684
10.250 1.0643 0.02679 0.01956 -0.0172 0.2413 0.8698
10.500 1.0710 0.02804 0.02075 -0.0156 0.2222 0.8710
10.750 1.0784 0.02931 0.02198 -0.0142 0.2031 0.8722
11.000 1.0850 0.03069 0.02329 -0.0129 0.1821 0.8734
11.250 1.0905 0.03220 0.02472 -0.0115 0.1622 0.8746
11.500 1.0974 0.03367 0.02612 -0.0104 0.1430 0.8757
11.750 1.1042 0.03522 0.02760 -0.0094 0.1249 0.8768
12.000 1.1099 0.03687 0.02918 -0.0084 0.1077 0.8778
12.250 1.1163 0.03842 0.03070 -0.0073 0.0941 0.8788
12.500 1.1234 0.03997 0.03225 -0.0064 0.0827 0.8799
12.750 1.1313 0.04150 0.03381 -0.0055 0.0733 0.8812
13.000 1.1385 0.04316 0.03550 -0.0048 0.0649 0.8826
13.250 1.1453 0.04491 0.03727 -0.0041 0.0569 0.8840
13.500 1.1512 0.04682 0.03920 -0.0035 0.0490 0.8853
14.000 1.1612 0.05101 0.04343 -0.0026 0.0345 0.8877
14.250 1.1657 0.05325 0.04573 -0.0023 0.0292 0.8889
14.500 1.1692 0.05568 0.04821 -0.0021 0.0247 0.8900
14.750 1.1718 0.05829 0.05087 -0.0020 0.0221 0.8911
15.250 1.1756 0.06379 0.05658 -0.0021 0.0188 0.8933
15.500 1.1769 0.06669 0.05959 -0.0022 0.0177 0.8945
15.750 1.1777 0.06973 0.06277 -0.0025 0.0170 0.8957
16.000 1.1779 0.07295 0.06612 -0.0030 0.0163 0.8969
16.250 1.1767 0.07643 0.06973 -0.0037 0.0157 0.8981
16.500 1.1745 0.08016 0.07357 -0.0045 0.0154 0.8994
16.750 1.1707 0.08419 0.07772 -0.0056 0.0149 0.9008
17.000 1.1690 0.08805 0.08172 -0.0067 0.0146 0.9022
17.250 1.1664 0.09210 0.08592 -0.0080 0.0142 0.9037
17.500 1.1642 0.09619 0.09015 -0.0095 0.0138 0.9053
18.000 1.1573 0.10483 0.09907 -0.0129 0.0132 0.9082
18.250 1.1536 0.10925 0.10362 -0.0147 0.0129 0.9097
18.500 1.1496 0.11379 0.10828 -0.0167 0.0126 0.9113
18.750 1.1450 0.11848 0.11308 -0.0190 0.0124 0.9130
19.000 1.1412 0.12307 0.11778 -0.0212 0.0122 0.9148
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