EH 2.0/7.0 (eh2070-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: EH 2.0/7.0 (eh2070-il) Reynolds number: 200,000 Max Cl/Cd: 60.04 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-eh2070-il-200000.txt Download as CSV file: xf-eh2070-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: EH 2.0/7.0
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.5348 0.09302 0.08980 0.0102 1.0000 0.0293
-7.750 -0.5344 0.08940 0.08623 0.0075 1.0000 0.0301
-7.500 -0.5365 0.08572 0.08260 0.0041 1.0000 0.0306
-7.250 -0.5332 0.08175 0.07862 -0.0009 1.0000 0.0313
-7.000 -0.5243 0.07801 0.07481 -0.0056 1.0000 0.0319
-6.750 -0.5131 0.07436 0.07104 -0.0087 1.0000 0.0323
-6.500 -0.5009 0.07060 0.06716 -0.0105 1.0000 0.0325
-6.250 -0.4644 0.05156 0.04847 -0.0116 1.0000 0.0338
-6.000 -0.4559 0.04741 0.04432 -0.0114 1.0000 0.0349
-5.750 -0.4450 0.04338 0.04025 -0.0119 1.0000 0.0363
-5.500 -0.4323 0.03930 0.03603 -0.0126 1.0000 0.0383
-5.250 -0.4170 0.03515 0.03172 -0.0135 1.0000 0.0410
-5.000 -0.3907 0.03312 0.02910 -0.0138 1.0000 0.0451
-4.750 -0.3824 0.02640 0.02235 -0.0143 1.0000 0.0468
-4.500 -0.3661 0.02331 0.01926 -0.0140 1.0000 0.0492
-4.250 -0.3462 0.02065 0.01641 -0.0137 1.0000 0.0539
-4.000 -0.3268 0.01759 0.01303 -0.0132 1.0000 0.0614
-3.750 -0.3070 0.01552 0.01076 -0.0126 1.0000 0.0744
-3.500 -0.2859 0.01384 0.00875 -0.0117 1.0000 0.0864
-3.250 -0.2698 0.02278 0.01659 -0.0075 1.0000 0.0431
-3.000 -0.2437 0.01976 0.01295 -0.0053 1.0000 0.0330
-2.750 -0.2207 0.01753 0.01052 -0.0041 1.0000 0.0317
-2.500 -0.1970 0.01580 0.00855 -0.0030 0.9987 0.0317
-2.250 -0.1525 0.01353 0.00613 -0.0061 0.9802 0.0352
-2.000 -0.1086 0.01257 0.00513 -0.0091 0.9522 0.0447
-1.750 -0.0719 0.01117 0.00381 -0.0106 0.9170 0.0753
-1.500 -0.0494 0.00956 0.00321 -0.0098 0.8780 0.3211
-1.250 0.0209 0.00822 0.00361 -0.0150 0.8562 0.9787
-1.000 0.0876 0.00827 0.00323 -0.0227 0.8193 1.0000
-0.750 0.1079 0.00835 0.00304 -0.0210 0.7849 1.0000
-0.500 0.1291 0.00843 0.00288 -0.0196 0.7569 1.0000
-0.250 0.1512 0.00851 0.00272 -0.0184 0.7325 1.0000
0.000 0.1737 0.00860 0.00260 -0.0173 0.7112 1.0000
0.250 0.1967 0.00868 0.00252 -0.0164 0.6904 1.0000
0.500 0.2198 0.00878 0.00246 -0.0155 0.6721 1.0000
0.750 0.2431 0.00888 0.00243 -0.0146 0.6548 1.0000
1.000 0.2667 0.00898 0.00242 -0.0138 0.6377 1.0000
1.250 0.2904 0.00910 0.00243 -0.0130 0.6217 1.0000
1.500 0.3143 0.00922 0.00245 -0.0122 0.6066 1.0000
1.750 0.3382 0.00935 0.00250 -0.0114 0.5919 1.0000
2.000 0.3623 0.00949 0.00257 -0.0107 0.5778 1.0000
2.250 0.3865 0.00963 0.00267 -0.0100 0.5639 1.0000
2.500 0.4108 0.00978 0.00277 -0.0093 0.5502 1.0000
2.750 0.4352 0.00994 0.00289 -0.0087 0.5367 1.0000
3.000 0.4597 0.01010 0.00303 -0.0080 0.5232 1.0000
3.250 0.4843 0.01027 0.00318 -0.0074 0.5100 1.0000
3.500 0.5091 0.01045 0.00341 -0.0068 0.4972 1.0000
3.750 0.5339 0.01065 0.00362 -0.0062 0.4846 1.0000
4.000 0.5587 0.01085 0.00385 -0.0056 0.4719 1.0000
4.250 0.5836 0.01106 0.00410 -0.0051 0.4591 1.0000
4.500 0.6085 0.01127 0.00435 -0.0045 0.4456 1.0000
4.750 0.6334 0.01148 0.00467 -0.0039 0.4315 1.0000
5.000 0.6584 0.01169 0.00497 -0.0034 0.4170 1.0000
5.250 0.6820 0.01166 0.00493 -0.0025 0.3828 1.0000
5.500 0.7055 0.01175 0.00496 -0.0017 0.3326 1.0000
5.750 0.7185 0.01404 0.00583 -0.0006 0.0688 1.0000
6.000 0.7376 0.01589 0.00758 0.0007 0.0304 1.0000
6.250 0.7585 0.01707 0.00895 0.0016 0.0235 1.0000
6.500 0.7748 0.01909 0.01110 0.0031 0.0215 1.0000
6.750 0.7948 0.02054 0.01266 0.0044 0.0208 1.0000
7.000 0.8148 0.02234 0.01455 0.0058 0.0205 1.0000
7.250 0.8357 0.02449 0.01681 0.0070 0.0207 1.0000
7.500 0.8570 0.02728 0.01978 0.0082 0.0211 1.0000
7.750 0.8794 0.03005 0.02273 0.0091 0.0221 1.0000
8.000 0.9043 0.03150 0.02468 0.0109 0.0256 1.0000
8.250 0.9186 0.03771 0.03140 0.0124 0.0314 1.0000
12.250 0.6546 0.12969 0.12647 -0.0203 0.0623 1.0000
12.500 0.6549 0.13354 0.13033 -0.0217 0.0598 1.0000
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Polar data table (+)
Polar graphs
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