EH 0.0/9.0 (eh0009-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: EH 0.0/9.0 (eh0009-il) Reynolds number: 1,000,000 Max Cl/Cd: 67.61 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-eh0009-il-1000000-n5.txt Download as CSV file: xf-eh0009-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EH 0.0/9.0
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
------ -------- --------- --------- -------- -------- --------
-14.750 -0.9105 0.10675 0.10498 0.0108 1.0000 0.0016
-14.500 -0.9505 0.09327 0.09141 0.0037 1.0000 0.0016
-14.250 -0.9806 0.08214 0.08020 -0.0024 1.0000 0.0015
-14.000 -1.0317 0.06627 0.06412 -0.0124 1.0000 0.0015
-13.750 -1.0475 0.05847 0.05620 -0.0179 1.0000 0.0015
-13.500 -1.0717 0.04997 0.04751 -0.0242 1.0000 0.0015
-13.250 -1.0894 0.04398 0.04134 -0.0279 1.0000 0.0015
-13.000 -1.1030 0.03963 0.03682 -0.0296 1.0000 0.0015
-12.750 -1.1204 0.03574 0.03273 -0.0294 1.0000 0.0015
-12.500 -1.1296 0.03320 0.03003 -0.0278 1.0000 0.0015
-12.250 -1.1385 0.03104 0.02769 -0.0248 1.0000 0.0015
-12.000 -1.1443 0.02914 0.02561 -0.0213 1.0000 0.0015
-11.750 -1.1402 0.02733 0.02361 -0.0192 1.0000 0.0015
-11.500 -1.1319 0.02570 0.02179 -0.0173 1.0000 0.0015
-11.250 -1.1212 0.02412 0.02002 -0.0156 1.0000 0.0016
-11.000 -1.1076 0.02274 0.01847 -0.0141 1.0000 0.0016
-10.750 -1.0923 0.02147 0.01701 -0.0128 1.0000 0.0017
-10.500 -1.0754 0.02032 0.01570 -0.0116 1.0000 0.0017
-10.250 -1.0568 0.01933 0.01458 -0.0106 1.0000 0.0017
-10.000 -1.0358 0.01861 0.01377 -0.0098 1.0000 0.0018
-9.750 -1.0158 0.01773 0.01276 -0.0089 1.0000 0.0018
-9.500 -0.9982 0.01642 0.01127 -0.0075 1.0000 0.0021
-9.250 -0.9770 0.01562 0.01038 -0.0067 1.0000 0.0022
-9.000 -0.9541 0.01509 0.00981 -0.0061 1.0000 0.0026
-8.750 -0.9312 0.01454 0.00920 -0.0054 1.0000 0.0028
-8.500 -0.9081 0.01400 0.00856 -0.0048 1.0000 0.0030
-8.250 -0.8847 0.01353 0.00804 -0.0041 1.0000 0.0033
-8.000 -0.8611 0.01308 0.00752 -0.0035 1.0000 0.0036
-7.750 -0.8372 0.01269 0.00709 -0.0029 1.0000 0.0038
-7.500 -0.8141 0.01218 0.00651 -0.0021 1.0000 0.0042
-7.250 -0.7910 0.01172 0.00601 -0.0013 1.0000 0.0048
-7.000 -0.7676 0.01135 0.00562 -0.0006 1.0000 0.0053
-6.750 -0.7442 0.01101 0.00526 0.0002 1.0000 0.0060
-6.500 -0.7206 0.01073 0.00495 0.0010 1.0000 0.0066
-6.250 -0.6976 0.01038 0.00455 0.0019 1.0000 0.0078
-6.000 -0.6661 0.01001 0.00419 0.0009 0.9970 0.0099
-5.750 -0.6334 0.00974 0.00390 -0.0004 0.9936 0.0115
-5.500 -0.6030 0.00939 0.00356 -0.0011 0.9893 0.0158
-5.250 -0.5710 0.00913 0.00329 -0.0021 0.9849 0.0188
-5.000 -0.5388 0.00885 0.00302 -0.0032 0.9798 0.0249
-4.750 -0.5076 0.00855 0.00275 -0.0040 0.9715 0.0359
-4.500 -0.4768 0.00825 0.00251 -0.0048 0.9611 0.0518
-4.250 -0.4479 0.00789 0.00227 -0.0051 0.9479 0.0805
-4.000 -0.4208 0.00762 0.00206 -0.0050 0.9323 0.1051
-3.750 -0.3951 0.00738 0.00188 -0.0045 0.9149 0.1308
-3.500 -0.3700 0.00712 0.00169 -0.0040 0.8971 0.1645
-3.250 -0.3442 0.00694 0.00154 -0.0036 0.8793 0.1893
-3.000 -0.3188 0.00670 0.00139 -0.0031 0.8610 0.2291
-2.750 -0.2929 0.00653 0.00127 -0.0027 0.8421 0.2609
-2.500 -0.2668 0.00638 0.00114 -0.0024 0.8220 0.2937
-2.250 -0.2407 0.00621 0.00104 -0.0020 0.8019 0.3314
-2.000 -0.2142 0.00610 0.00096 -0.0017 0.7811 0.3620
-1.500 -0.1610 0.00590 0.00082 -0.0012 0.7392 0.4221
-1.250 -0.1343 0.00583 0.00076 -0.0010 0.7162 0.4514
-1.000 -0.1075 0.00578 0.00071 -0.0008 0.6920 0.4800
-0.750 -0.0807 0.00574 0.00068 -0.0006 0.6671 0.5079
-0.500 -0.0538 0.00571 0.00066 -0.0004 0.6423 0.5356
-0.250 -0.0269 0.00568 0.00064 -0.0002 0.6175 0.5643
0.000 0.0000 0.00567 0.00063 0.0000 0.5921 0.5922
0.250 0.0268 0.00568 0.00064 0.0002 0.5643 0.6176
0.500 0.0537 0.00571 0.00066 0.0004 0.5356 0.6422
0.750 0.0806 0.00574 0.00068 0.0006 0.5074 0.6672
1.000 0.1075 0.00578 0.00071 0.0008 0.4801 0.6919
1.250 0.1342 0.00583 0.00076 0.0010 0.4516 0.7160
1.500 0.1609 0.00590 0.00082 0.0013 0.4219 0.7390
2.000 0.2141 0.00610 0.00096 0.0018 0.3619 0.7811
2.250 0.2406 0.00622 0.00104 0.0020 0.3310 0.8020
2.500 0.2667 0.00638 0.00114 0.0024 0.2936 0.8221
2.750 0.2928 0.00653 0.00127 0.0027 0.2610 0.8422
3.000 0.3187 0.00670 0.00139 0.0031 0.2301 0.8611
3.250 0.3441 0.00694 0.00154 0.0036 0.1898 0.8794
3.500 0.3699 0.00712 0.00168 0.0040 0.1652 0.8973
3.750 0.3951 0.00738 0.00188 0.0046 0.1307 0.9150
4.000 0.4208 0.00762 0.00206 0.0050 0.1050 0.9323
4.250 0.4479 0.00788 0.00226 0.0051 0.0815 0.9480
4.500 0.4769 0.00825 0.00251 0.0048 0.0522 0.9612
4.750 0.5078 0.00855 0.00275 0.0040 0.0359 0.9716
5.000 0.5390 0.00885 0.00302 0.0031 0.0249 0.9799
5.250 0.5712 0.00913 0.00329 0.0020 0.0188 0.9850
5.500 0.6033 0.00939 0.00356 0.0010 0.0157 0.9894
6.000 0.6665 0.01001 0.00419 -0.0010 0.0099 0.9972
6.250 0.6972 0.01039 0.00455 -0.0018 0.0077 1.0000
6.500 0.7202 0.01074 0.00496 -0.0009 0.0066 1.0000
6.750 0.7439 0.01102 0.00527 -0.0001 0.0060 1.0000
7.000 0.7674 0.01135 0.00562 0.0006 0.0054 1.0000
7.250 0.7909 0.01172 0.00602 0.0013 0.0048 1.0000
7.500 0.8141 0.01218 0.00651 0.0021 0.0042 1.0000
7.750 0.8373 0.01268 0.00707 0.0029 0.0038 1.0000
8.000 0.8610 0.01310 0.00755 0.0035 0.0036 1.0000
8.250 0.8846 0.01355 0.00806 0.0041 0.0033 1.0000
8.500 0.9082 0.01402 0.00859 0.0047 0.0030 1.0000
8.750 0.9313 0.01456 0.00922 0.0054 0.0028 1.0000
9.000 0.9545 0.01506 0.00977 0.0060 0.0025 1.0000
9.250 0.9771 0.01565 0.01041 0.0067 0.0023 1.0000
9.500 0.9987 0.01639 0.01124 0.0075 0.0021 1.0000
9.750 1.0160 0.01774 0.01278 0.0088 0.0018 1.0000
10.000 1.0368 0.01851 0.01366 0.0096 0.0018 1.0000
10.250 1.0569 0.01935 0.01461 0.0105 0.0018 1.0000
10.500 1.0757 0.02033 0.01571 0.0115 0.0017 1.0000
10.750 1.0926 0.02149 0.01703 0.0127 0.0017 1.0000
11.000 1.1085 0.02269 0.01841 0.0140 0.0016 1.0000
11.250 1.1221 0.02408 0.01998 0.0155 0.0016 1.0000
11.500 1.1330 0.02564 0.02172 0.0171 0.0016 1.0000
11.750 1.1407 0.02736 0.02364 0.0191 0.0015 1.0000
12.000 1.1447 0.02919 0.02566 0.0212 0.0015 1.0000
12.250 1.1396 0.03105 0.02770 0.0247 0.0015 1.0000
12.500 1.1314 0.03315 0.02997 0.0275 0.0015 1.0000
12.750 1.1204 0.03584 0.03284 0.0293 0.0015 1.0000
13.000 1.1058 0.03944 0.03663 0.0294 0.0015 1.0000
13.250 1.0921 0.04378 0.04113 0.0279 0.0015 1.0000
13.500 1.0682 0.05078 0.04835 0.0234 0.0015 1.0000
13.750 1.0508 0.05810 0.05582 0.0180 0.0015 1.0000
14.000 1.0258 0.06791 0.06579 0.0110 0.0015 1.0000
14.250 0.9884 0.08080 0.07884 0.0029 0.0015 1.0000
14.500 0.9508 0.09361 0.09175 -0.0042 0.0016 1.0000
14.750 0.9117 0.10691 0.10514 -0.0111 0.0016 1.0000
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Polar data table (+)
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