EH 1.0/9.0 (eh1090-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: EH 1.0/9.0 (eh1090-il) Reynolds number: 200,000 Max Cl/Cd: 56.74 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-eh1090-il-200000.txt Download as CSV file: xf-eh1090-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: EH 1.0/9.0
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
------ -------- --------- --------- -------- -------- --------
-7.500 -0.6443 0.05722 0.05355 -0.0194 1.0000 0.0581
-7.250 -0.6341 0.05433 0.05062 -0.0189 1.0000 0.0603
-7.000 -0.6265 0.05069 0.04677 -0.0185 1.0000 0.0633
-6.750 -0.6261 0.04612 0.04162 -0.0176 1.0000 0.0697
-6.500 -0.6189 0.03316 0.02729 -0.0130 1.0000 0.0318
-6.250 -0.6023 0.02915 0.02300 -0.0116 1.0000 0.0300
-6.000 -0.5847 0.02576 0.01916 -0.0099 1.0000 0.0293
-5.750 -0.5640 0.02315 0.01615 -0.0084 1.0000 0.0294
-5.500 -0.5416 0.02111 0.01380 -0.0070 1.0000 0.0299
-5.250 -0.5182 0.01972 0.01217 -0.0058 1.0000 0.0310
-5.000 -0.4974 0.01761 0.00999 -0.0046 1.0000 0.0347
-4.750 -0.4754 0.01651 0.00885 -0.0033 1.0000 0.0380
-4.500 -0.4539 0.01548 0.00770 -0.0018 1.0000 0.0419
-4.250 -0.4353 0.01419 0.00646 0.0000 1.0000 0.0504
-4.000 -0.4160 0.01328 0.00564 0.0016 1.0000 0.0718
-3.750 -0.3972 0.01246 0.00501 0.0031 1.0000 0.1111
-3.500 -0.3789 0.01174 0.00456 0.0046 1.0000 0.1634
-3.250 -0.3622 0.01095 0.00421 0.0062 1.0000 0.2455
-3.000 -0.3488 0.00998 0.00392 0.0082 1.0000 0.3948
-2.750 -0.3387 0.00908 0.00390 0.0113 1.0000 0.5859
-2.500 -0.3022 0.00862 0.00407 0.0102 0.9894 0.7575
-2.250 -0.2615 0.00863 0.00420 0.0085 0.9794 0.8336
-2.000 -0.2188 0.00877 0.00434 0.0065 0.9702 0.8824
-1.750 -0.1749 0.00891 0.00438 0.0042 0.9596 0.9110
-1.500 -0.1282 0.00904 0.00440 0.0011 0.9481 0.9289
-1.250 -0.0748 0.00923 0.00446 -0.0032 0.9369 0.9443
-1.000 -0.0199 0.00934 0.00446 -0.0080 0.9217 0.9560
-0.750 0.0383 0.00940 0.00441 -0.0135 0.9027 0.9656
-0.500 0.0901 0.00939 0.00426 -0.0179 0.8767 0.9761
-0.250 0.1359 0.00933 0.00406 -0.0213 0.8477 0.9862
0.000 0.1784 0.00925 0.00382 -0.0242 0.8180 0.9949
0.250 0.2128 0.00916 0.00357 -0.0257 0.7891 1.0000
0.500 0.2323 0.00916 0.00344 -0.0241 0.7620 1.0000
0.750 0.2525 0.00918 0.00333 -0.0228 0.7365 1.0000
1.000 0.2733 0.00921 0.00325 -0.0215 0.7129 1.0000
1.250 0.2944 0.00927 0.00320 -0.0202 0.6910 1.0000
1.500 0.3161 0.00932 0.00317 -0.0192 0.6689 1.0000
2.000 0.3603 0.00947 0.00316 -0.0170 0.6277 1.0000
2.250 0.3825 0.00958 0.00320 -0.0160 0.6085 1.0000
2.500 0.4050 0.00969 0.00326 -0.0150 0.5887 1.0000
2.750 0.4275 0.00982 0.00334 -0.0140 0.5696 1.0000
3.000 0.4500 0.00998 0.00342 -0.0130 0.5513 1.0000
3.250 0.4727 0.01012 0.00355 -0.0120 0.5318 1.0000
3.500 0.4954 0.01029 0.00371 -0.0110 0.5129 1.0000
3.750 0.5182 0.01046 0.00385 -0.0101 0.4932 1.0000
4.000 0.5410 0.01064 0.00401 -0.0091 0.4726 1.0000
4.250 0.5638 0.01085 0.00419 -0.0081 0.4533 1.0000
4.500 0.5870 0.01105 0.00442 -0.0072 0.4340 1.0000
4.750 0.6099 0.01129 0.00468 -0.0063 0.4149 1.0000
5.000 0.6329 0.01152 0.00493 -0.0054 0.3928 1.0000
5.250 0.6556 0.01177 0.00517 -0.0044 0.3691 1.0000
5.500 0.6780 0.01201 0.00540 -0.0034 0.3372 1.0000
5.750 0.6996 0.01233 0.00562 -0.0024 0.2951 1.0000
6.000 0.7211 0.01277 0.00594 -0.0014 0.2502 1.0000
6.250 0.7414 0.01343 0.00642 -0.0004 0.1899 1.0000
6.500 0.7529 0.01553 0.00764 0.0014 0.0604 1.0000
6.750 0.7678 0.01729 0.00934 0.0034 0.0389 1.0000
7.000 0.7864 0.01845 0.01062 0.0050 0.0346 1.0000
7.250 0.8048 0.01958 0.01181 0.0063 0.0305 1.0000
7.500 0.8187 0.02164 0.01389 0.0082 0.0273 1.0000
7.750 0.8386 0.02302 0.01541 0.0095 0.0262 1.0000
8.000 0.8585 0.02475 0.01728 0.0109 0.0251 1.0000
8.250 0.8785 0.02682 0.01959 0.0122 0.0244 1.0000
8.500 0.8977 0.02913 0.02216 0.0135 0.0240 1.0000
8.750 0.9151 0.03120 0.02448 0.0147 0.0228 1.0000
9.000 0.9310 0.03287 0.02630 0.0157 0.0210 1.0000
9.250 0.9438 0.03571 0.02947 0.0172 0.0208 1.0000
9.500 0.9512 0.03942 0.03365 0.0192 0.0214 1.0000
9.750 0.9475 0.04412 0.03893 0.0217 0.0227 1.0000
10.000 0.9387 0.04872 0.04395 0.0238 0.0238 1.0000
10.250 0.9263 0.05268 0.04818 0.0257 0.0248 1.0000
10.500 0.9087 0.05625 0.05195 0.0274 0.0254 1.0000
10.750 0.8890 0.06035 0.05623 0.0273 0.0257 1.0000
11.000 0.8708 0.06503 0.06104 0.0254 0.0261 1.0000
11.250 0.8515 0.07064 0.06678 0.0220 0.0265 1.0000
11.500 0.8300 0.07782 0.07405 0.0178 0.0271 1.0000
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Polar data table (+)
Polar graphs
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