EH 1.5/9.0 (eh1590-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: EH 1.5/9.0 (eh1590-il) Reynolds number: 100,000 Max Cl/Cd: 45.6 at α=7° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-eh1590-il-100000.txt Download as CSV file: xf-eh1590-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: EH 1.5/9.0
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.5552 0.08876 0.08429 -0.0023 1.0000 0.1017
-8.000 -0.5732 0.08445 0.08007 -0.0081 1.0000 0.1046
-7.750 -0.6075 0.08139 0.07675 -0.0155 1.0000 0.1064
-7.500 -0.5758 0.07558 0.07122 -0.0113 1.0000 0.1098
-7.250 -0.5703 0.07204 0.06766 -0.0117 1.0000 0.1148
-7.000 -0.5823 0.06752 0.06290 -0.0157 1.0000 0.1213
-6.750 -0.5641 0.06423 0.05974 -0.0137 1.0000 0.1279
-6.500 -0.5604 0.06033 0.05573 -0.0145 1.0000 0.1378
-6.250 -0.5536 0.05693 0.05221 -0.0147 1.0000 0.1505
-6.000 -0.5441 0.05368 0.04884 -0.0144 1.0000 0.1638
-5.750 -0.5327 0.05047 0.04548 -0.0138 1.0000 0.1775
-5.500 -0.5082 0.03639 0.02940 -0.0133 1.0000 0.0649
-5.250 -0.4902 0.03245 0.02518 -0.0120 1.0000 0.0618
-5.000 -0.4701 0.02902 0.02125 -0.0103 1.0000 0.0595
-4.750 -0.4482 0.02619 0.01791 -0.0086 1.0000 0.0592
-4.500 -0.4249 0.02394 0.01528 -0.0072 1.0000 0.0611
-4.250 -0.4014 0.02235 0.01332 -0.0058 1.0000 0.0668
-4.000 -0.3789 0.02062 0.01162 -0.0047 1.0000 0.0754
-3.750 -0.3565 0.01905 0.01005 -0.0033 1.0000 0.0868
-3.500 -0.3356 0.01780 0.00880 -0.0018 1.0000 0.1073
-3.250 -0.3177 0.01659 0.00785 -0.0001 1.0000 0.1378
-3.000 -0.3019 0.01549 0.00700 0.0019 1.0000 0.1799
-2.750 -0.2892 0.01428 0.00634 0.0042 1.0000 0.2551
-2.500 -0.2873 0.01186 0.00655 0.0104 1.0000 0.7737
-2.250 -0.1005 0.01311 0.00700 -0.0125 1.0000 0.9793
-2.000 -0.0194 0.01269 0.00621 -0.0233 1.0000 1.0000
-1.750 -0.0042 0.01255 0.00603 -0.0221 1.0000 1.0000
-1.500 0.0017 0.01259 0.00606 -0.0196 1.0000 1.0000
-1.250 0.0122 0.01287 0.00632 -0.0190 0.9898 1.0000
-1.000 0.0798 0.01275 0.00604 -0.0273 0.9663 1.0000
-0.750 0.1394 0.01258 0.00572 -0.0339 0.9365 1.0000
-0.500 0.1826 0.01246 0.00546 -0.0368 0.9020 1.0000
-0.250 0.2079 0.01247 0.00531 -0.0360 0.8679 1.0000
0.000 0.2276 0.01254 0.00524 -0.0341 0.8378 1.0000
0.250 0.2467 0.01263 0.00520 -0.0322 0.8114 1.0000
0.500 0.2663 0.01274 0.00516 -0.0303 0.7883 1.0000
0.750 0.2863 0.01287 0.00519 -0.0287 0.7650 1.0000
1.000 0.3064 0.01302 0.00521 -0.0270 0.7447 1.0000
1.250 0.3272 0.01319 0.00531 -0.0255 0.7243 1.0000
1.500 0.3481 0.01337 0.00537 -0.0240 0.7061 1.0000
1.750 0.3695 0.01356 0.00550 -0.0227 0.6877 1.0000
2.000 0.3912 0.01377 0.00565 -0.0215 0.6698 1.0000
2.250 0.4131 0.01398 0.00580 -0.0202 0.6530 1.0000
2.500 0.4351 0.01421 0.00599 -0.0190 0.6369 1.0000
2.750 0.4574 0.01445 0.00618 -0.0178 0.6214 1.0000
3.000 0.4798 0.01471 0.00643 -0.0167 0.6050 1.0000
3.250 0.5024 0.01498 0.00670 -0.0156 0.5889 1.0000
3.500 0.5250 0.01526 0.00698 -0.0146 0.5732 1.0000
3.750 0.5478 0.01555 0.00731 -0.0135 0.5579 1.0000
4.000 0.5707 0.01585 0.00762 -0.0125 0.5426 1.0000
4.250 0.5937 0.01615 0.00794 -0.0114 0.5275 1.0000
4.500 0.6168 0.01647 0.00827 -0.0104 0.5124 1.0000
4.750 0.6399 0.01679 0.00861 -0.0094 0.4973 1.0000
5.000 0.6630 0.01712 0.00902 -0.0083 0.4819 1.0000
5.250 0.6858 0.01747 0.00948 -0.0073 0.4650 1.0000
5.500 0.7087 0.01780 0.00990 -0.0063 0.4480 1.0000
5.750 0.7318 0.01811 0.01028 -0.0052 0.4307 1.0000
6.000 0.7551 0.01840 0.01058 -0.0041 0.4134 1.0000
6.250 0.7773 0.01869 0.01109 -0.0030 0.3926 1.0000
6.500 0.7989 0.01872 0.01117 -0.0016 0.3676 1.0000
6.750 0.8176 0.01834 0.01078 0.0002 0.3281 1.0000
7.000 0.8368 0.01835 0.01088 0.0016 0.2847 1.0000
7.250 0.8509 0.01915 0.01136 0.0034 0.1789 1.0000
7.500 0.8509 0.02276 0.01389 0.0063 0.0753 1.0000
7.750 0.8623 0.02476 0.01587 0.0085 0.0621 1.0000
8.000 0.8771 0.02648 0.01765 0.0105 0.0551 1.0000
8.250 0.8923 0.02869 0.01985 0.0122 0.0501 1.0000
8.500 0.9110 0.03033 0.02166 0.0135 0.0450 1.0000
8.750 0.9310 0.03263 0.02400 0.0147 0.0424 1.0000
9.000 0.9521 0.03579 0.02725 0.0156 0.0410 1.0000
9.250 0.9709 0.03953 0.03125 0.0165 0.0404 1.0000
9.500 0.9852 0.04306 0.03515 0.0179 0.0404 1.0000
9.750 0.9949 0.04661 0.03910 0.0193 0.0404 1.0000
10.000 0.9986 0.05077 0.04365 0.0207 0.0402 1.0000
10.250 0.9963 0.05529 0.04855 0.0221 0.0400 1.0000
10.500 0.9910 0.05872 0.05229 0.0236 0.0399 1.0000
10.750 0.9790 0.06166 0.05555 0.0252 0.0396 1.0000
11.000 0.9709 0.06561 0.05971 0.0264 0.0401 1.0000
11.250 0.9563 0.06834 0.06264 0.0272 0.0403 1.0000
11.500 0.9367 0.07109 0.06566 0.0263 0.0412 1.0000
11.750 0.9113 0.07639 0.07116 0.0229 0.0416 1.0000
12.000 0.8382 0.09158 0.08672 0.0093 0.0478 1.0000
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Polar data table (+)
Polar graphs
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