EH 1.5/9.0 (eh1590-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: EH 1.5/9.0 (eh1590-il) Reynolds number: 100,000 Max Cl/Cd: 45.53 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-eh1590-il-100000-n5.txt Download as CSV file: xf-eh1590-il-100000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.5707 0.08909 0.08441 -0.0023 1.0000 0.0228
-8.750 -0.5781 0.08288 0.07826 -0.0068 1.0000 0.0220
-8.500 -0.5915 0.07561 0.07105 -0.0131 1.0000 0.0213
-8.250 -0.6089 0.06737 0.06276 -0.0171 1.0000 0.0203
-7.750 -0.6137 0.05719 0.05215 -0.0187 1.0000 0.0198
-7.500 -0.6133 0.05261 0.04733 -0.0185 1.0000 0.0197
-7.250 -0.6101 0.04807 0.04243 -0.0178 1.0000 0.0196
-7.000 -0.6037 0.04375 0.03771 -0.0169 1.0000 0.0197
-6.750 -0.5958 0.03946 0.03302 -0.0157 1.0000 0.0201
-6.500 -0.5825 0.03687 0.03023 -0.0149 1.0000 0.0214
-6.250 -0.5653 0.03497 0.02812 -0.0141 1.0000 0.0231
-6.000 -0.5482 0.03215 0.02488 -0.0128 1.0000 0.0243
-5.750 -0.5294 0.02915 0.02139 -0.0114 1.0000 0.0248
-5.500 -0.5085 0.02662 0.01842 -0.0101 1.0000 0.0255
-5.250 -0.4861 0.02445 0.01588 -0.0089 1.0000 0.0266
-5.000 -0.4629 0.02263 0.01376 -0.0077 1.0000 0.0280
-4.750 -0.4401 0.02107 0.01201 -0.0066 1.0000 0.0297
-4.500 -0.4188 0.01997 0.01089 -0.0056 1.0000 0.0346
-4.250 -0.3969 0.01897 0.00976 -0.0044 1.0000 0.0398
-4.000 -0.3770 0.01785 0.00866 -0.0030 1.0000 0.0460
-3.750 -0.3569 0.01709 0.00792 -0.0016 1.0000 0.0582
-3.500 -0.3376 0.01633 0.00720 -0.0002 1.0000 0.0744
-3.250 -0.3103 0.01560 0.00657 -0.0004 0.9918 0.1025
-3.000 -0.2726 0.01482 0.00596 -0.0029 0.9735 0.1519
-2.750 -0.2368 0.01392 0.00547 -0.0050 0.9539 0.2423
-2.500 -0.2091 0.01241 0.00509 -0.0055 0.9318 0.4931
-2.250 -0.1778 0.01170 0.00533 -0.0044 0.9132 0.7624
-2.000 -0.1392 0.01179 0.00536 -0.0050 0.8917 0.8467
-1.750 -0.0987 0.01195 0.00534 -0.0062 0.8689 0.8907
-1.500 -0.0563 0.01213 0.00529 -0.0080 0.8451 0.9228
-1.250 0.0097 0.01241 0.00528 -0.0143 0.8222 0.9588
-1.000 0.0686 0.01246 0.00506 -0.0200 0.7965 0.9813
-0.750 0.1062 0.01237 0.00476 -0.0220 0.7702 0.9886
-0.500 0.1413 0.01232 0.00448 -0.0236 0.7459 0.9958
-0.250 0.1714 0.01228 0.00428 -0.0242 0.7230 1.0000
0.000 0.1932 0.01229 0.00414 -0.0232 0.7025 1.0000
0.250 0.2150 0.01231 0.00404 -0.0221 0.6828 1.0000
0.500 0.2369 0.01235 0.00395 -0.0210 0.6647 1.0000
0.750 0.2595 0.01241 0.00389 -0.0201 0.6474 1.0000
1.000 0.2821 0.01248 0.00387 -0.0192 0.6303 1.0000
1.250 0.3046 0.01256 0.00387 -0.0183 0.6141 1.0000
1.500 0.3271 0.01266 0.00391 -0.0173 0.5985 1.0000
1.750 0.3498 0.01278 0.00395 -0.0164 0.5835 1.0000
2.000 0.3725 0.01290 0.00402 -0.0154 0.5688 1.0000
2.250 0.3953 0.01304 0.00411 -0.0145 0.5545 1.0000
2.500 0.4182 0.01319 0.00425 -0.0136 0.5404 1.0000
2.750 0.4412 0.01336 0.00439 -0.0127 0.5265 1.0000
3.000 0.4643 0.01353 0.00454 -0.0118 0.5127 1.0000
3.250 0.4875 0.01372 0.00473 -0.0110 0.4992 1.0000
3.500 0.5107 0.01392 0.00493 -0.0101 0.4856 1.0000
3.750 0.5340 0.01413 0.00519 -0.0093 0.4721 1.0000
4.000 0.5573 0.01435 0.00544 -0.0084 0.4585 1.0000
4.250 0.5806 0.01459 0.00571 -0.0076 0.4449 1.0000
4.500 0.6040 0.01484 0.00600 -0.0068 0.4312 1.0000
4.750 0.6273 0.01510 0.00632 -0.0059 0.4173 1.0000
5.000 0.6506 0.01537 0.00670 -0.0051 0.4031 1.0000
5.250 0.6739 0.01566 0.00706 -0.0042 0.3886 1.0000
5.500 0.6970 0.01596 0.00744 -0.0034 0.3734 1.0000
5.750 0.7201 0.01628 0.00783 -0.0025 0.3576 1.0000
6.000 0.7433 0.01661 0.00829 -0.0017 0.3397 1.0000
6.250 0.7661 0.01695 0.00879 -0.0009 0.3204 1.0000
6.500 0.7881 0.01731 0.00921 0.0001 0.2934 1.0000
6.750 0.8074 0.01783 0.00956 0.0011 0.2372 1.0000
7.000 0.8255 0.01875 0.01019 0.0021 0.1708 1.0000
7.250 0.8401 0.02031 0.01129 0.0033 0.0922 1.0000
7.500 0.8521 0.02232 0.01291 0.0049 0.0449 1.0000
7.750 0.8673 0.02384 0.01448 0.0063 0.0342 1.0000
8.000 0.8801 0.02554 0.01635 0.0079 0.0294 1.0000
8.250 0.8942 0.02697 0.01800 0.0095 0.0272 1.0000
8.500 0.9078 0.02838 0.01959 0.0110 0.0245 1.0000
8.750 0.9198 0.02988 0.02118 0.0125 0.0216 1.0000
9.000 0.9265 0.03202 0.02340 0.0144 0.0200 1.0000
9.250 0.9383 0.03381 0.02532 0.0160 0.0193 1.0000
9.500 0.9508 0.03573 0.02743 0.0175 0.0187 1.0000
9.750 0.9628 0.03787 0.02978 0.0190 0.0181 1.0000
10.000 0.9734 0.04027 0.03242 0.0204 0.0176 1.0000
10.250 0.9808 0.04285 0.03527 0.0219 0.0171 1.0000
10.500 0.9830 0.04533 0.03800 0.0236 0.0167 1.0000
10.750 0.9812 0.04786 0.04076 0.0251 0.0160 1.0000
11.000 0.9772 0.05077 0.04390 0.0259 0.0156 1.0000
11.250 0.9714 0.05381 0.04716 0.0260 0.0152 1.0000
11.500 0.9632 0.05744 0.05108 0.0253 0.0150 1.0000
11.750 0.9541 0.06117 0.05497 0.0237 0.0145 1.0000
12.000 0.9424 0.06585 0.05985 0.0215 0.0143 1.0000
12.250 0.9296 0.07103 0.06523 0.0186 0.0143 1.0000
12.500 0.9139 0.07715 0.07155 0.0149 0.0145 1.0000
12.750 0.8922 0.08501 0.07958 0.0099 0.0150 1.0000
13.000 0.8693 0.09375 0.08850 0.0040 0.0155 1.0000
13.250 0.8419 0.10447 0.09937 -0.0030 0.0164 1.0000
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Polar data table (+)
Polar graphs
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