EH 2.0/12 (eh2012-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: EH 2.0/12 (eh2012-il) Reynolds number: 1,000,000 Max Cl/Cd: 97.64 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-eh2012-il-1000000-n5.txt Download as CSV file: xf-eh2012-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.750 -0.8667 0.10727 0.10521 -0.0017 1.0000 0.0054
-15.500 -1.1059 0.05349 0.05078 -0.0374 1.0000 0.0048
-15.250 -1.1356 0.04570 0.04277 -0.0424 1.0000 0.0048
-15.000 -1.1534 0.04106 0.03797 -0.0438 1.0000 0.0048
-14.750 -1.1660 0.03766 0.03441 -0.0436 1.0000 0.0047
-14.500 -1.1679 0.03552 0.03217 -0.0427 1.0000 0.0048
-14.250 -1.1743 0.03323 0.02975 -0.0410 1.0000 0.0049
-14.000 -1.1749 0.03154 0.02794 -0.0390 1.0000 0.0049
-13.750 -1.1747 0.02999 0.02627 -0.0367 1.0000 0.0050
-13.500 -1.1723 0.02868 0.02485 -0.0341 1.0000 0.0050
-13.250 -1.1672 0.02759 0.02366 -0.0315 1.0000 0.0052
-13.000 -1.1636 0.02641 0.02237 -0.0284 1.0000 0.0052
-12.750 -1.1536 0.02535 0.02120 -0.0263 1.0000 0.0052
-12.500 -1.1395 0.02445 0.02020 -0.0247 1.0000 0.0054
-12.250 -1.1261 0.02342 0.01905 -0.0229 1.0000 0.0054
-12.000 -1.1108 0.02248 0.01800 -0.0214 1.0000 0.0055
-11.750 -1.0934 0.02167 0.01709 -0.0200 1.0000 0.0056
-11.500 -1.0753 0.02088 0.01621 -0.0188 1.0000 0.0057
-11.250 -1.0564 0.02014 0.01538 -0.0176 1.0000 0.0057
-11.000 -1.0366 0.01946 0.01462 -0.0165 1.0000 0.0058
-10.750 -1.0183 0.01857 0.01363 -0.0152 1.0000 0.0059
-10.500 -0.9990 0.01775 0.01272 -0.0139 1.0000 0.0060
-10.250 -0.9786 0.01704 0.01193 -0.0129 1.0000 0.0063
-10.000 -0.9572 0.01643 0.01126 -0.0119 1.0000 0.0064
-9.750 -0.9353 0.01588 0.01066 -0.0109 1.0000 0.0066
-9.500 -0.9131 0.01536 0.01010 -0.0100 1.0000 0.0068
-9.250 -0.8807 0.01480 0.00948 -0.0113 0.9806 0.0070
-9.000 -0.8437 0.01425 0.00886 -0.0135 0.9477 0.0073
-8.750 -0.8188 0.01390 0.00834 -0.0129 0.9023 0.0075
-8.500 -0.7971 0.01361 0.00788 -0.0116 0.8654 0.0078
-8.250 -0.7741 0.01332 0.00745 -0.0106 0.8350 0.0080
-8.000 -0.7503 0.01305 0.00705 -0.0098 0.8082 0.0082
-7.750 -0.7267 0.01265 0.00653 -0.0090 0.7843 0.0089
-7.500 -0.7022 0.01236 0.00615 -0.0084 0.7623 0.0095
-7.250 -0.6773 0.01209 0.00579 -0.0078 0.7422 0.0101
-7.000 -0.6519 0.01186 0.00546 -0.0073 0.7231 0.0109
-6.750 -0.6265 0.01160 0.00512 -0.0068 0.7054 0.0117
-6.500 -0.6011 0.01133 0.00479 -0.0063 0.6889 0.0130
-6.250 -0.5753 0.01111 0.00450 -0.0059 0.6735 0.0142
-6.000 -0.5493 0.01089 0.00421 -0.0055 0.6592 0.0158
-5.750 -0.5234 0.01067 0.00395 -0.0051 0.6451 0.0181
-5.500 -0.4970 0.01048 0.00371 -0.0048 0.6319 0.0204
-5.250 -0.4709 0.01027 0.00348 -0.0044 0.6192 0.0238
-5.000 -0.4444 0.01010 0.00326 -0.0041 0.6074 0.0273
-4.750 -0.4180 0.00992 0.00306 -0.0038 0.5956 0.0323
-4.500 -0.3915 0.00974 0.00288 -0.0035 0.5839 0.0379
-4.250 -0.3646 0.00960 0.00271 -0.0033 0.5734 0.0430
-4.000 -0.3379 0.00945 0.00254 -0.0030 0.5626 0.0496
-3.750 -0.3110 0.00933 0.00239 -0.0028 0.5518 0.0555
-3.500 -0.2840 0.00919 0.00226 -0.0026 0.5414 0.0637
-3.250 -0.2570 0.00906 0.00213 -0.0024 0.5316 0.0727
-3.000 -0.2300 0.00896 0.00200 -0.0022 0.5216 0.0817
-2.750 -0.2028 0.00885 0.00189 -0.0020 0.5120 0.0923
-2.500 -0.1756 0.00874 0.00179 -0.0018 0.5032 0.1044
-2.250 -0.1485 0.00863 0.00169 -0.0017 0.4943 0.1189
-2.000 -0.1213 0.00851 0.00161 -0.0015 0.4858 0.1359
-1.750 -0.0944 0.00840 0.00153 -0.0013 0.4771 0.1564
-1.500 -0.0674 0.00826 0.00145 -0.0011 0.4692 0.1839
-1.250 -0.0406 0.00813 0.00138 -0.0009 0.4612 0.2147
-1.000 -0.0143 0.00792 0.00131 -0.0007 0.4528 0.2640
-0.750 0.0116 0.00767 0.00124 -0.0004 0.4455 0.3274
-0.500 0.0362 0.00730 0.00116 0.0001 0.4376 0.4224
-0.250 0.0600 0.00690 0.00109 0.0008 0.4303 0.5333
0.000 0.0844 0.00659 0.00105 0.0014 0.4226 0.6221
0.250 0.1099 0.00643 0.00104 0.0020 0.4154 0.6821
0.500 0.1361 0.00634 0.00106 0.0024 0.4077 0.7248
0.750 0.1625 0.00628 0.00109 0.0028 0.4011 0.7620
1.000 0.1885 0.00623 0.00114 0.0033 0.3934 0.8001
1.250 0.2150 0.00622 0.00119 0.0037 0.3864 0.8281
1.500 0.2416 0.00624 0.00125 0.0041 0.3794 0.8522
1.750 0.2684 0.00628 0.00131 0.0045 0.3726 0.8701
2.000 0.2961 0.00634 0.00135 0.0046 0.3650 0.8784
2.250 0.3240 0.00641 0.00140 0.0047 0.3583 0.8841
2.500 0.3518 0.00647 0.00146 0.0047 0.3510 0.8902
2.750 0.3796 0.00656 0.00151 0.0048 0.3441 0.8963
3.000 0.4073 0.00662 0.00158 0.0049 0.3372 0.9020
3.250 0.4348 0.00672 0.00166 0.0049 0.3300 0.9082
3.500 0.4626 0.00679 0.00173 0.0050 0.3234 0.9137
3.750 0.4899 0.00690 0.00181 0.0051 0.3160 0.9196
4.000 0.5174 0.00699 0.00190 0.0052 0.3094 0.9255
4.250 0.5449 0.00710 0.00200 0.0053 0.3027 0.9309
4.500 0.5724 0.00719 0.00210 0.0054 0.2959 0.9368
4.750 0.5996 0.00732 0.00221 0.0055 0.2885 0.9423
5.000 0.6277 0.00743 0.00233 0.0054 0.2819 0.9473
5.500 0.6832 0.00770 0.00258 0.0053 0.2665 0.9578
5.750 0.7122 0.00787 0.00273 0.0050 0.2588 0.9622
6.000 0.7406 0.00801 0.00287 0.0048 0.2514 0.9672
6.250 0.7695 0.00819 0.00303 0.0044 0.2434 0.9712
6.500 0.8005 0.00837 0.00321 0.0035 0.2343 0.9740
6.750 0.8308 0.00856 0.00339 0.0028 0.2256 0.9773
7.000 0.8592 0.00880 0.00360 0.0025 0.2141 0.9813
7.250 0.8889 0.00914 0.00385 0.0017 0.1940 0.9840
7.500 0.9196 0.00954 0.00415 0.0007 0.1733 0.9858
7.750 0.9491 0.01004 0.00452 -0.0002 0.1474 0.9880
8.000 0.9773 0.01061 0.00494 -0.0009 0.1204 0.9908
8.250 1.0048 0.01112 0.00536 -0.0014 0.1003 0.9937
8.500 1.0336 0.01171 0.00585 -0.0023 0.0797 0.9960
8.750 1.0614 0.01243 0.00643 -0.0031 0.0572 0.9986
9.000 1.0839 0.01318 0.00707 -0.0029 0.0370 1.0000
9.250 1.0978 0.01386 0.00766 -0.0008 0.0235 1.0000
9.500 1.1142 0.01439 0.00817 0.0009 0.0170 1.0000
10.000 1.1493 0.01534 0.00914 0.0040 0.0116 1.0000
10.250 1.1663 0.01586 0.00968 0.0055 0.0098 1.0000
10.500 1.1845 0.01631 0.01016 0.0068 0.0090 1.0000
10.750 1.2016 0.01682 0.01070 0.0082 0.0083 1.0000
11.000 1.2172 0.01740 0.01131 0.0097 0.0075 1.0000
11.250 1.2322 0.01798 0.01194 0.0113 0.0070 1.0000
11.500 1.2466 0.01853 0.01254 0.0130 0.0067 1.0000
11.750 1.2559 0.01913 0.01318 0.0156 0.0064 1.0000
12.000 1.2639 0.01981 0.01392 0.0181 0.0061 1.0000
12.250 1.2715 0.02061 0.01478 0.0203 0.0059 1.0000
12.500 1.2780 0.02159 0.01581 0.0223 0.0056 1.0000
12.750 1.2842 0.02273 0.01701 0.0238 0.0054 1.0000
13.000 1.2892 0.02410 0.01845 0.0251 0.0052 1.0000
13.250 1.2920 0.02582 0.02025 0.0261 0.0049 1.0000
13.500 1.2980 0.02744 0.02195 0.0266 0.0048 1.0000
13.750 1.3021 0.02937 0.02396 0.0268 0.0047 1.0000
14.000 1.3066 0.03137 0.02604 0.0269 0.0045 1.0000
14.250 1.3082 0.03379 0.02854 0.0267 0.0044 1.0000
14.500 1.3102 0.03624 0.03107 0.0264 0.0043 1.0000
14.750 1.3096 0.03907 0.03399 0.0258 0.0041 1.0000
15.000 1.3050 0.04242 0.03744 0.0251 0.0042 1.0000
15.250 1.3035 0.04547 0.04056 0.0243 0.0040 1.0000
15.500 1.2991 0.04890 0.04408 0.0234 0.0038 1.0000
15.750 1.2931 0.05259 0.04787 0.0224 0.0039 1.0000
16.000 1.2867 0.05640 0.05174 0.0212 0.0037 1.0000
16.250 1.2794 0.06046 0.05590 0.0199 0.0037 1.0000
16.500 1.2674 0.06531 0.06086 0.0181 0.0037 1.0000
16.750 1.2590 0.06977 0.06540 0.0164 0.0036 1.0000
17.000 1.2488 0.07461 0.07034 0.0146 0.0035 1.0000
17.250 1.2411 0.07914 0.07496 0.0128 0.0035 1.0000
17.500 1.2247 0.08515 0.08108 0.0102 0.0034 1.0000
17.750 1.2140 0.09040 0.08642 0.0080 0.0034 1.0000
|
Polar data table (+)
Polar graphs
<< Back to EH 2.0/12 (eh2012-il)