EH 2.0/12 (eh2012-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: EH 2.0/12 (eh2012-il) Reynolds number: 1,000,000 Max Cl/Cd: 106.54 at α=7.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-eh2012-il-1000000.txt Download as CSV file: xf-eh2012-il-1000000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.750 -0.9234 0.05695 0.05473 -0.0336 1.0000 0.0075
-13.500 -0.9537 0.04816 0.04572 -0.0403 1.0000 0.0074
-13.250 -0.9752 0.04293 0.04030 -0.0423 1.0000 0.0075
-13.000 -0.9953 0.03884 0.03602 -0.0420 1.0000 0.0074
-12.750 -1.0090 0.03587 0.03287 -0.0404 1.0000 0.0074
-12.500 -1.0132 0.03393 0.03079 -0.0382 1.0000 0.0076
-12.250 -1.0220 0.03178 0.02848 -0.0350 1.0000 0.0075
-12.000 -1.0278 0.02996 0.02648 -0.0312 1.0000 0.0076
-11.750 -1.0243 0.02859 0.02496 -0.0284 1.0000 0.0078
-11.500 -1.0137 0.02742 0.02366 -0.0264 1.0000 0.0079
-11.250 -1.0027 0.02614 0.02223 -0.0245 1.0000 0.0080
-11.000 -0.9873 0.02521 0.02119 -0.0229 1.0000 0.0081
-10.750 -0.9701 0.02441 0.02027 -0.0216 1.0000 0.0082
-10.500 -0.9652 0.02191 0.01749 -0.0188 1.0000 0.0084
-10.250 -0.9548 0.02002 0.01541 -0.0166 1.0000 0.0087
-10.000 -0.9371 0.01903 0.01433 -0.0152 1.0000 0.0090
-9.750 -0.9174 0.01825 0.01347 -0.0140 1.0000 0.0092
-9.500 -0.8968 0.01756 0.01272 -0.0129 1.0000 0.0094
-9.250 -0.8761 0.01688 0.01196 -0.0118 1.0000 0.0096
-9.000 -0.8550 0.01625 0.01127 -0.0107 1.0000 0.0099
-8.750 -0.8340 0.01563 0.01057 -0.0095 1.0000 0.0102
-8.500 -0.8133 0.01503 0.00990 -0.0083 1.0000 0.0105
-8.250 -0.7926 0.01449 0.00931 -0.0069 1.0000 0.0108
-8.000 -0.7668 0.01400 0.00876 -0.0067 0.9974 0.0110
-7.750 -0.7320 0.01317 0.00784 -0.0084 0.9864 0.0115
-7.500 -0.6961 0.01236 0.00697 -0.0104 0.9706 0.0126
-7.250 -0.6622 0.01192 0.00647 -0.0118 0.9424 0.0135
-7.000 -0.6377 0.01167 0.00610 -0.0109 0.9052 0.0144
-6.750 -0.6151 0.01141 0.00569 -0.0097 0.8720 0.0153
-6.500 -0.5925 0.01101 0.00519 -0.0085 0.8431 0.0174
-6.250 -0.5680 0.01080 0.00487 -0.0077 0.8176 0.0190
-6.000 -0.5437 0.01049 0.00445 -0.0069 0.7940 0.0218
-5.750 -0.5184 0.01028 0.00418 -0.0064 0.7722 0.0249
-5.500 -0.4933 0.01002 0.00386 -0.0058 0.7520 0.0297
-5.250 -0.4673 0.00987 0.00364 -0.0053 0.7331 0.0335
-5.000 -0.4417 0.00964 0.00338 -0.0049 0.7159 0.0402
-4.750 -0.4155 0.00948 0.00317 -0.0045 0.6993 0.0464
-4.500 -0.3890 0.00934 0.00300 -0.0042 0.6834 0.0524
-4.250 -0.3627 0.00916 0.00281 -0.0038 0.6687 0.0608
-4.000 -0.3360 0.00904 0.00264 -0.0035 0.6543 0.0678
-3.750 -0.3094 0.00890 0.00248 -0.0032 0.6405 0.0771
-3.250 -0.2560 0.00861 0.00219 -0.0027 0.6144 0.1022
-3.000 -0.2292 0.00846 0.00206 -0.0024 0.6021 0.1181
-2.750 -0.2026 0.00830 0.00194 -0.0022 0.5906 0.1391
-2.500 -0.1761 0.00815 0.00182 -0.0019 0.5795 0.1647
-2.250 -0.1499 0.00794 0.00171 -0.0016 0.5685 0.2010
-2.000 -0.1241 0.00767 0.00159 -0.0012 0.5580 0.2543
-1.750 -0.0997 0.00729 0.00147 -0.0007 0.5480 0.3393
-1.500 -0.0782 0.00664 0.00131 0.0003 0.5384 0.4913
-1.250 -0.0565 0.00610 0.00122 0.0014 0.5291 0.6269
-1.000 -0.0324 0.00586 0.00119 0.0023 0.5197 0.7042
-0.750 -0.0067 0.00575 0.00119 0.0029 0.5102 0.7501
-0.500 0.0201 0.00572 0.00119 0.0033 0.5013 0.7792
-0.250 0.0469 0.00572 0.00120 0.0037 0.4921 0.8033
0.250 0.1017 0.00575 0.00123 0.0042 0.4747 0.8365
0.500 0.1292 0.00579 0.00126 0.0044 0.4659 0.8503
0.750 0.1564 0.00582 0.00129 0.0047 0.4580 0.8641
1.000 0.1831 0.00587 0.00134 0.0051 0.4495 0.8803
1.250 0.2097 0.00592 0.00140 0.0056 0.4416 0.8952
1.750 0.2616 0.00606 0.00155 0.0069 0.4261 0.9214
2.000 0.2885 0.00614 0.00159 0.0072 0.4180 0.9285
2.250 0.3161 0.00620 0.00164 0.0074 0.4104 0.9339
2.500 0.3428 0.00629 0.00169 0.0077 0.4027 0.9402
2.750 0.3709 0.00635 0.00175 0.0078 0.3949 0.9449
3.000 0.3982 0.00645 0.00182 0.0080 0.3874 0.9504
3.250 0.4249 0.00653 0.00188 0.0083 0.3797 0.9562
3.500 0.4545 0.00663 0.00196 0.0079 0.3723 0.9601
3.750 0.4837 0.00674 0.00204 0.0077 0.3643 0.9645
4.000 0.5107 0.00684 0.00213 0.0079 0.3572 0.9700
4.250 0.5436 0.00695 0.00223 0.0068 0.3495 0.9722
4.500 0.5768 0.00708 0.00233 0.0056 0.3417 0.9744
4.750 0.6099 0.00721 0.00244 0.0043 0.3335 0.9768
5.000 0.6424 0.00733 0.00255 0.0033 0.3258 0.9793
5.250 0.6720 0.00749 0.00268 0.0028 0.3173 0.9829
5.500 0.7075 0.00761 0.00279 0.0010 0.3094 0.9837
5.750 0.7423 0.00777 0.00293 -0.0006 0.3011 0.9848
6.000 0.7768 0.00790 0.00306 -0.0022 0.2925 0.9861
6.250 0.8107 0.00806 0.00321 -0.0037 0.2841 0.9877
6.500 0.8437 0.00824 0.00337 -0.0050 0.2748 0.9896
6.750 0.8762 0.00839 0.00352 -0.0062 0.2655 0.9917
7.000 0.9072 0.00861 0.00370 -0.0071 0.2524 0.9939
7.250 0.9409 0.00884 0.00389 -0.0087 0.2369 0.9952
7.500 0.9738 0.00914 0.00411 -0.0101 0.2189 0.9967
7.750 1.0063 0.00945 0.00436 -0.0115 0.2008 0.9984
8.000 1.0386 0.00977 0.00462 -0.0129 0.1849 0.9998
8.250 1.0587 0.01010 0.00490 -0.0117 0.1700 1.0000
8.500 1.0762 0.01048 0.00522 -0.0100 0.1532 1.0000
8.750 1.0924 0.01096 0.00560 -0.0081 0.1339 1.0000
9.000 1.1076 0.01153 0.00605 -0.0061 0.1113 1.0000
9.250 1.1218 0.01219 0.00657 -0.0040 0.0878 1.0000
9.500 1.1337 0.01304 0.00726 -0.0017 0.0614 1.0000
9.750 1.1439 0.01403 0.00807 0.0009 0.0346 1.0000
10.000 1.1549 0.01497 0.00891 0.0033 0.0196 1.0000
10.250 1.1701 0.01563 0.00956 0.0051 0.0153 1.0000
10.500 1.1855 0.01628 0.01024 0.0068 0.0130 1.0000
10.750 1.2019 0.01684 0.01085 0.0083 0.0119 1.0000
11.000 1.2159 0.01752 0.01156 0.0101 0.0109 1.0000
11.250 1.2248 0.01845 0.01258 0.0126 0.0098 1.0000
11.500 1.2363 0.01902 0.01321 0.0148 0.0096 1.0000
11.750 1.2436 0.01970 0.01395 0.0175 0.0091 1.0000
12.000 1.2501 0.02053 0.01484 0.0200 0.0087 1.0000
12.250 1.2557 0.02153 0.01591 0.0221 0.0084 1.0000
12.500 1.2601 0.02276 0.01720 0.0239 0.0081 1.0000
12.750 1.2631 0.02427 0.01878 0.0253 0.0078 1.0000
13.000 1.2634 0.02621 0.02081 0.0263 0.0076 1.0000
13.250 1.2494 0.02977 0.02453 0.0268 0.0071 1.0000
13.500 1.2544 0.03177 0.02660 0.0268 0.0070 1.0000
13.750 1.2582 0.03399 0.02892 0.0266 0.0068 1.0000
14.000 1.2595 0.03657 0.03158 0.0262 0.0067 1.0000
14.250 1.2584 0.03950 0.03460 0.0256 0.0065 1.0000
14.500 1.2558 0.04265 0.03783 0.0249 0.0064 1.0000
14.750 1.2529 0.04591 0.04118 0.0241 0.0061 1.0000
15.000 1.2390 0.05056 0.04596 0.0228 0.0063 1.0000
15.250 1.2357 0.05399 0.04946 0.0218 0.0062 1.0000
15.500 1.2317 0.05754 0.05308 0.0207 0.0058 1.0000
15.750 1.2207 0.06216 0.05782 0.0191 0.0059 1.0000
16.000 1.2154 0.06616 0.06188 0.0177 0.0057 1.0000
16.250 1.2062 0.07075 0.06656 0.0160 0.0057 1.0000
16.500 1.1940 0.07594 0.07185 0.0140 0.0056 1.0000
16.750 1.1856 0.08064 0.07663 0.0121 0.0056 1.0000
17.000 1.1756 0.08569 0.08177 0.0101 0.0055 1.0000
17.250 1.1687 0.09037 0.08652 0.0081 0.0055 1.0000
17.500 1.1566 0.09592 0.09216 0.0057 0.0054 1.0000
17.750 1.1496 0.10076 0.09708 0.0036 0.0054 1.0000
18.000 1.1371 0.10656 0.10295 0.0010 0.0052 1.0000
18.250 1.1287 0.11174 0.10821 -0.0014 0.0051 1.0000
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Polar data table (+)
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