Eh 1.0/7.0 (eh1070-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: Eh 1.0/7.0 (eh1070-il) Reynolds number: 200,000 Max Cl/Cd: 49.86 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-eh1070-il-200000-n5.txt Download as CSV file: xf-eh1070-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: Eh 1.0/7.0
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.6036 0.08399 0.08071 0.0049 1.0000 0.0088
-8.000 -0.6093 0.07914 0.07593 0.0011 1.0000 0.0088
-7.750 -0.6143 0.07422 0.07100 -0.0028 1.0000 0.0085
-7.500 -0.6147 0.06880 0.06554 -0.0064 1.0000 0.0085
-7.250 -0.6126 0.06328 0.05993 -0.0092 1.0000 0.0084
-7.000 -0.6074 0.05783 0.05434 -0.0112 1.0000 0.0085
-6.750 -0.5989 0.05264 0.04896 -0.0124 1.0000 0.0089
-6.500 -0.5863 0.04757 0.04364 -0.0128 1.0000 0.0100
-6.250 -0.5702 0.04298 0.03875 -0.0126 1.0000 0.0110
-6.000 -0.5554 0.03852 0.03394 -0.0120 1.0000 0.0112
-5.750 -0.5408 0.03391 0.02891 -0.0111 1.0000 0.0110
-5.500 -0.5236 0.02989 0.02442 -0.0100 1.0000 0.0109
-5.250 -0.5039 0.02650 0.02054 -0.0089 1.0000 0.0109
-5.000 -0.4823 0.02360 0.01709 -0.0077 1.0000 0.0109
-4.750 -0.4591 0.02123 0.01431 -0.0066 1.0000 0.0111
-4.500 -0.4349 0.01940 0.01214 -0.0057 1.0000 0.0115
-4.250 -0.4117 0.01703 0.00947 -0.0045 1.0000 0.0123
-4.000 -0.3885 0.01566 0.00800 -0.0037 1.0000 0.0148
-3.750 -0.3643 0.01487 0.00714 -0.0030 1.0000 0.0174
-3.500 -0.3410 0.01384 0.00600 -0.0019 1.0000 0.0182
-3.250 -0.3177 0.01303 0.00508 -0.0009 1.0000 0.0193
-3.000 -0.2942 0.01241 0.00433 0.0000 1.0000 0.0211
-2.750 -0.2711 0.01173 0.00356 0.0010 1.0000 0.0295
-2.500 -0.2485 0.01115 0.00313 0.0019 1.0000 0.0644
-2.250 -0.2189 0.01002 0.00281 0.0006 0.9889 0.2309
-2.000 -0.1901 0.00863 0.00253 -0.0005 0.9715 0.5070
-1.750 -0.1640 0.00778 0.00253 0.0003 0.9519 0.7319
-1.500 -0.1324 0.00760 0.00256 0.0004 0.9305 0.8347
-1.250 -0.0962 0.00759 0.00248 -0.0005 0.9072 0.8840
-1.000 -0.0588 0.00764 0.00242 -0.0018 0.8811 0.9174
-0.750 -0.0169 0.00773 0.00239 -0.0040 0.8540 0.9474
-0.500 0.0329 0.00785 0.00235 -0.0080 0.8251 0.9725
-0.250 0.0716 0.00792 0.00222 -0.0101 0.7937 0.9827
0.000 0.1072 0.00796 0.00209 -0.0117 0.7621 0.9890
0.250 0.1411 0.00802 0.00199 -0.0129 0.7327 0.9953
0.500 0.1732 0.00808 0.00190 -0.0139 0.7046 1.0000
0.750 0.1957 0.00816 0.00186 -0.0129 0.6791 1.0000
1.000 0.2186 0.00825 0.00183 -0.0119 0.6547 1.0000
1.250 0.2417 0.00835 0.00182 -0.0110 0.6315 1.0000
1.500 0.2652 0.00846 0.00184 -0.0101 0.6089 1.0000
1.750 0.2888 0.00858 0.00188 -0.0093 0.5867 1.0000
2.000 0.3125 0.00872 0.00198 -0.0085 0.5644 1.0000
2.250 0.3365 0.00886 0.00206 -0.0077 0.5420 1.0000
2.500 0.3606 0.00901 0.00216 -0.0070 0.5214 1.0000
2.750 0.3849 0.00917 0.00229 -0.0063 0.5013 1.0000
3.000 0.4093 0.00934 0.00244 -0.0057 0.4806 1.0000
3.250 0.4336 0.00954 0.00260 -0.0050 0.4576 1.0000
3.500 0.4580 0.00974 0.00285 -0.0043 0.4334 1.0000
3.750 0.4825 0.00996 0.00307 -0.0037 0.4081 1.0000
4.000 0.5068 0.01022 0.00331 -0.0030 0.3798 1.0000
4.250 0.5300 0.01063 0.00354 -0.0023 0.3222 1.0000
4.500 0.5505 0.01157 0.00386 -0.0016 0.1953 1.0000
4.750 0.5711 0.01272 0.00448 -0.0009 0.0853 1.0000
5.000 0.5918 0.01400 0.00541 -0.0001 0.0224 1.0000
5.250 0.6149 0.01489 0.00651 0.0008 0.0163 1.0000
5.500 0.6373 0.01591 0.00774 0.0018 0.0144 1.0000
5.750 0.6592 0.01699 0.00900 0.0028 0.0134 1.0000
6.000 0.6817 0.01790 0.01003 0.0036 0.0111 1.0000
6.250 0.7037 0.01887 0.01107 0.0043 0.0090 1.0000
6.500 0.7230 0.02070 0.01304 0.0054 0.0081 1.0000
6.750 0.7410 0.02360 0.01618 0.0069 0.0075 1.0000
7.000 0.7613 0.02585 0.01869 0.0080 0.0074 1.0000
7.250 0.7810 0.02809 0.02127 0.0090 0.0072 1.0000
7.500 0.7985 0.03075 0.02431 0.0102 0.0072 1.0000
7.750 0.8133 0.03378 0.02775 0.0113 0.0071 1.0000
8.000 0.8247 0.03713 0.03152 0.0125 0.0071 1.0000
8.250 0.8323 0.04076 0.03563 0.0136 0.0072 1.0000
8.500 0.8353 0.04467 0.03991 0.0147 0.0072 1.0000
8.750 0.8331 0.04877 0.04434 0.0155 0.0073 1.0000
9.000 0.8254 0.05298 0.04880 0.0161 0.0074 1.0000
9.500 0.8018 0.06006 0.05622 0.0160 0.0075 1.0000
9.750 0.7871 0.06490 0.06120 0.0126 0.0075 1.0000
10.000 0.7787 0.06997 0.06639 0.0081 0.0076 1.0000
10.250 0.7680 0.07671 0.07322 0.0023 0.0077 1.0000
10.500 0.7600 0.08403 0.08062 -0.0034 0.0077 1.0000
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Polar data table (+)
Polar graphs
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