EH 2.0/12 (eh2012-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: EH 2.0/12 (eh2012-il) Reynolds number: 100,000 Max Cl/Cd: 45.86 at α=8° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-eh2012-il-100000-n5.txt Download as CSV file: xf-eh2012-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EH 2.0/12
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
------ -------- --------- --------- -------- -------- --------
-10.750 -0.5547 0.09666 0.09180 -0.0102 1.0000 0.0271
-10.500 -0.6075 0.07575 0.07095 -0.0242 1.0000 0.0255
-10.250 -0.6313 0.06746 0.06260 -0.0307 1.0000 0.0252
-10.000 -0.6559 0.06160 0.05661 -0.0334 1.0000 0.0251
-9.750 -0.6787 0.05711 0.05197 -0.0332 1.0000 0.0250
-9.500 -0.7003 0.05295 0.04758 -0.0311 1.0000 0.0250
-9.250 -0.7148 0.04858 0.04285 -0.0290 1.0000 0.0251
-9.000 -0.7239 0.04425 0.03804 -0.0266 1.0000 0.0254
-8.750 -0.7211 0.04131 0.03483 -0.0247 1.0000 0.0261
-8.500 -0.7083 0.03999 0.03346 -0.0235 1.0000 0.0273
-8.250 -0.6970 0.03809 0.03135 -0.0220 1.0000 0.0285
-8.000 -0.6863 0.03561 0.02851 -0.0202 1.0000 0.0297
-7.750 -0.6742 0.03290 0.02536 -0.0182 1.0000 0.0311
-7.500 -0.6589 0.03045 0.02247 -0.0165 1.0000 0.0323
-7.250 -0.6418 0.02852 0.02031 -0.0150 1.0000 0.0339
-7.000 -0.6236 0.02759 0.01938 -0.0138 1.0000 0.0363
-6.750 -0.6050 0.02641 0.01802 -0.0124 1.0000 0.0394
-6.500 -0.5856 0.02497 0.01628 -0.0108 1.0000 0.0422
-6.250 -0.5689 0.02387 0.01524 -0.0092 1.0000 0.0451
-6.000 -0.5522 0.02314 0.01446 -0.0075 1.0000 0.0497
-5.750 -0.5144 0.02188 0.01310 -0.0099 0.9830 0.0561
-5.500 -0.4766 0.02101 0.01209 -0.0120 0.9636 0.0652
-5.250 -0.4401 0.02012 0.01119 -0.0141 0.9434 0.0748
-5.000 -0.4051 0.01932 0.01036 -0.0157 0.9217 0.0857
-4.750 -0.3721 0.01864 0.00963 -0.0167 0.8993 0.0981
-4.500 -0.3429 0.01804 0.00898 -0.0169 0.8761 0.1113
-4.250 -0.3164 0.01753 0.00841 -0.0164 0.8536 0.1263
-4.000 -0.2920 0.01707 0.00791 -0.0156 0.8317 0.1435
-3.750 -0.2684 0.01663 0.00746 -0.0145 0.8112 0.1653
-3.500 -0.2454 0.01619 0.00704 -0.0134 0.7923 0.1939
-3.250 -0.2232 0.01568 0.00664 -0.0123 0.7740 0.2371
-3.000 -0.2025 0.01503 0.00628 -0.0110 0.7569 0.3127
-2.750 -0.1865 0.01402 0.00601 -0.0087 0.7410 0.4776
-2.500 -0.1651 0.01346 0.00621 -0.0062 0.7261 0.6752
-2.250 -0.1366 0.01355 0.00635 -0.0050 0.7113 0.7601
-2.000 -0.1088 0.01373 0.00643 -0.0040 0.6970 0.8061
-1.750 -0.0794 0.01393 0.00649 -0.0033 0.6831 0.8376
-1.500 -0.0486 0.01416 0.00654 -0.0030 0.6698 0.8625
-1.250 -0.0138 0.01445 0.00666 -0.0033 0.6565 0.8857
-1.000 0.0277 0.01486 0.00691 -0.0047 0.6428 0.9123
-0.750 0.0875 0.01526 0.00709 -0.0099 0.6281 0.9325
-0.500 0.1239 0.01532 0.00700 -0.0115 0.6151 0.9429
-0.250 0.1598 0.01531 0.00684 -0.0132 0.6025 0.9485
0.000 0.1891 0.01533 0.00672 -0.0136 0.5909 0.9559
0.250 0.2255 0.01530 0.00656 -0.0154 0.5796 0.9604
0.500 0.2579 0.01531 0.00644 -0.0165 0.5683 0.9664
0.750 0.2904 0.01531 0.00636 -0.0177 0.5570 0.9719
1.000 0.3247 0.01530 0.00626 -0.0192 0.5460 0.9769
1.250 0.3559 0.01534 0.00619 -0.0201 0.5360 0.9827
1.500 0.3910 0.01532 0.00611 -0.0219 0.5251 0.9872
1.750 0.4241 0.01534 0.00609 -0.0233 0.5145 0.9922
2.000 0.4577 0.01536 0.00604 -0.0248 0.5049 0.9969
2.250 0.4874 0.01541 0.00604 -0.0255 0.4950 1.0000
2.500 0.5092 0.01549 0.00613 -0.0246 0.4858 1.0000
2.750 0.5309 0.01560 0.00616 -0.0236 0.4780 1.0000
3.000 0.5526 0.01572 0.00631 -0.0227 0.4684 1.0000
3.250 0.5741 0.01586 0.00641 -0.0217 0.4605 1.0000
3.500 0.5956 0.01601 0.00659 -0.0208 0.4518 1.0000
3.750 0.6170 0.01618 0.00676 -0.0197 0.4435 1.0000
4.000 0.6383 0.01636 0.00693 -0.0187 0.4354 1.0000
4.250 0.6596 0.01656 0.00717 -0.0176 0.4270 1.0000
4.500 0.6808 0.01677 0.00736 -0.0165 0.4194 1.0000
4.750 0.7018 0.01700 0.00766 -0.0155 0.4107 1.0000
5.000 0.7229 0.01723 0.00787 -0.0143 0.4034 1.0000
5.250 0.7438 0.01748 0.00821 -0.0132 0.3946 1.0000
5.500 0.7648 0.01775 0.00850 -0.0121 0.3872 1.0000
5.750 0.7855 0.01802 0.00885 -0.0109 0.3786 1.0000
6.000 0.8063 0.01832 0.00919 -0.0098 0.3709 1.0000
6.250 0.8271 0.01862 0.00954 -0.0086 0.3628 1.0000
6.500 0.8477 0.01895 0.00997 -0.0075 0.3546 1.0000
6.750 0.8685 0.01926 0.01032 -0.0063 0.3469 1.0000
7.000 0.8888 0.01963 0.01080 -0.0051 0.3381 1.0000
7.250 0.9094 0.01997 0.01115 -0.0040 0.3305 1.0000
7.500 0.9292 0.02036 0.01171 -0.0028 0.3211 1.0000
7.750 0.9493 0.02074 0.01218 -0.0016 0.3127 1.0000
8.000 0.9691 0.02113 0.01265 -0.0003 0.3038 1.0000
8.250 0.9884 0.02158 0.01323 0.0009 0.2944 1.0000
8.500 1.0078 0.02200 0.01371 0.0021 0.2855 1.0000
8.750 1.0266 0.02245 0.01431 0.0034 0.2755 1.0000
9.000 1.0447 0.02295 0.01496 0.0047 0.2649 1.0000
9.250 1.0624 0.02345 0.01556 0.0061 0.2544 1.0000
9.500 1.0787 0.02397 0.01617 0.0076 0.2423 1.0000
9.750 1.0923 0.02452 0.01682 0.0093 0.2250 1.0000
10.000 1.1027 0.02519 0.01752 0.0112 0.2043 1.0000
10.250 1.1113 0.02606 0.01840 0.0132 0.1821 1.0000
10.500 1.1178 0.02711 0.01943 0.0153 0.1629 1.0000
10.750 1.1213 0.02829 0.02063 0.0177 0.1447 1.0000
11.000 1.1189 0.02972 0.02204 0.0205 0.1264 1.0000
11.250 1.1132 0.03159 0.02386 0.0228 0.1095 1.0000
11.500 1.1064 0.03389 0.02615 0.0243 0.0948 1.0000
11.750 1.0969 0.03678 0.02902 0.0250 0.0800 1.0000
12.000 1.0859 0.04018 0.03242 0.0250 0.0689 1.0000
12.250 1.0731 0.04413 0.03637 0.0244 0.0603 1.0000
12.500 1.0619 0.04818 0.04049 0.0235 0.0537 1.0000
12.750 1.0475 0.05284 0.04519 0.0221 0.0495 1.0000
13.000 1.0364 0.05729 0.04973 0.0207 0.0459 1.0000
13.250 1.0238 0.06207 0.05460 0.0191 0.0429 1.0000
13.500 1.0114 0.06696 0.05956 0.0173 0.0411 1.0000
13.750 0.9979 0.07210 0.06474 0.0154 0.0390 1.0000
14.000 0.9901 0.07661 0.06937 0.0138 0.0371 1.0000
14.250 0.9820 0.08130 0.07416 0.0120 0.0350 1.0000
14.500 0.9743 0.08605 0.07899 0.0101 0.0334 1.0000
14.750 0.9664 0.09093 0.08394 0.0081 0.0319 1.0000
|
Polar data table (+)
Polar graphs
<< Back to EH 2.0/12 (eh2012-il)