E184 (8.33%) (e184-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: E184 (8.33%) (e184-il) Reynolds number: 1,000,000 Max Cl/Cd: 67.03 at α=3.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e184-il-1000000-n5.txt Download as CSV file: xf-e184-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: E184 (8.33%)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.9883 0.04151 0.03971 0.0044 1.0000 0.0044
-10.000 -1.0108 0.03281 0.03036 0.0057 1.0000 0.0046
-9.750 -1.0002 0.03117 0.02843 0.0075 0.9050 0.0047
-9.500 -0.9841 0.02998 0.02703 0.0087 0.8767 0.0048
-9.250 -0.9634 0.02939 0.02631 0.0093 0.8551 0.0050
-9.000 -0.9435 0.02840 0.02514 0.0100 0.8369 0.0051
-8.750 -0.9228 0.02741 0.02398 0.0105 0.8208 0.0052
-8.500 -0.9021 0.02627 0.02262 0.0111 0.8066 0.0054
-8.250 -0.8799 0.02539 0.02158 0.0116 0.7938 0.0056
-8.000 -0.8581 0.02429 0.02029 0.0122 0.7820 0.0059
-7.750 -0.8365 0.02296 0.01874 0.0128 0.7712 0.0062
-7.500 -0.8148 0.02146 0.01699 0.0135 0.7614 0.0065
-7.250 -0.7927 0.01998 0.01525 0.0142 0.7521 0.0067
-7.000 -0.7695 0.01868 0.01373 0.0149 0.7434 0.0069
-6.750 -0.7457 0.01754 0.01236 0.0155 0.7354 0.0070
-6.500 -0.7213 0.01651 0.01115 0.0160 0.7275 0.0072
-6.250 -0.6959 0.01583 0.01033 0.0164 0.7203 0.0074
-6.000 -0.6701 0.01525 0.00964 0.0167 0.7129 0.0076
-5.750 -0.6442 0.01465 0.00891 0.0171 0.7064 0.0078
-5.500 -0.6183 0.01403 0.00818 0.0174 0.6997 0.0079
-5.250 -0.5921 0.01351 0.00755 0.0177 0.6936 0.0080
-5.000 -0.5697 0.01184 0.00566 0.0187 0.6876 0.0088
-4.500 -0.5173 0.01085 0.00450 0.0194 0.6761 0.0096
-4.250 -0.4906 0.01049 0.00406 0.0197 0.6703 0.0099
-4.000 -0.4638 0.01016 0.00367 0.0199 0.6651 0.0102
-3.750 -0.4368 0.00984 0.00329 0.0201 0.6595 0.0104
-3.500 -0.4096 0.00958 0.00296 0.0203 0.6543 0.0106
-3.250 -0.3823 0.00932 0.00264 0.0205 0.6492 0.0110
-3.000 -0.3549 0.00911 0.00238 0.0206 0.6439 0.0114
-2.750 -0.3274 0.00891 0.00212 0.0208 0.6391 0.0116
-2.500 -0.2998 0.00872 0.00189 0.0209 0.6340 0.0119
-2.250 -0.2721 0.00858 0.00170 0.0210 0.6287 0.0123
-2.000 -0.2443 0.00844 0.00152 0.0211 0.6240 0.0130
-1.750 -0.2164 0.00832 0.00137 0.0212 0.6189 0.0158
-1.500 -0.1892 0.00808 0.00123 0.0213 0.6137 0.0408
-1.250 -0.1620 0.00783 0.00111 0.0214 0.6089 0.0790
-1.000 -0.1349 0.00757 0.00100 0.0215 0.6037 0.1255
-0.500 -0.0814 0.00698 0.00083 0.0218 0.5934 0.2567
-0.250 -0.0560 0.00649 0.00076 0.0221 0.5879 0.3834
0.000 -0.0319 0.00591 0.00069 0.0226 0.5825 0.5401
0.250 -0.0067 0.00556 0.00065 0.0231 0.5752 0.6367
0.500 0.0173 0.00520 0.00062 0.0239 0.5671 0.7362
0.750 0.0400 0.00484 0.00060 0.0252 0.5587 0.8396
1.000 0.0729 0.00465 0.00068 0.0244 0.5490 0.9271
1.250 0.1242 0.00476 0.00077 0.0193 0.5360 0.9586
1.750 0.1894 0.00494 0.00087 0.0174 0.5141 0.9783
2.000 0.2219 0.00505 0.00093 0.0164 0.4989 0.9840
2.250 0.2588 0.00514 0.00097 0.0144 0.4826 0.9877
2.500 0.2935 0.00526 0.00104 0.0128 0.4635 0.9912
2.750 0.3277 0.00542 0.00111 0.0114 0.4366 0.9942
3.000 0.3655 0.00560 0.00118 0.0090 0.4021 0.9964
3.250 0.4015 0.00599 0.00131 0.0069 0.3322 0.9985
3.500 0.4357 0.00676 0.00160 0.0048 0.2148 0.9998
3.750 0.4635 0.00724 0.00182 0.0044 0.1515 1.0000
4.000 0.4899 0.00779 0.00208 0.0042 0.0877 1.0000
4.250 0.5160 0.00819 0.00232 0.0043 0.0520 1.0000
4.500 0.5420 0.00860 0.00259 0.0043 0.0235 1.0000
4.750 0.5680 0.00899 0.00292 0.0045 0.0078 1.0000
5.000 0.5939 0.00925 0.00319 0.0048 0.0060 1.0000
5.250 0.6198 0.00954 0.00353 0.0051 0.0052 1.0000
5.500 0.6455 0.00987 0.00391 0.0054 0.0046 1.0000
5.750 0.6710 0.01015 0.00423 0.0057 0.0044 1.0000
6.000 0.6964 0.01050 0.00462 0.0060 0.0042 1.0000
6.250 0.7216 0.01089 0.00508 0.0064 0.0039 1.0000
6.500 0.7465 0.01131 0.00556 0.0067 0.0037 1.0000
6.750 0.7712 0.01179 0.00609 0.0071 0.0035 1.0000
7.000 0.7955 0.01227 0.00662 0.0075 0.0032 1.0000
7.250 0.8195 0.01279 0.00719 0.0079 0.0030 1.0000
7.500 0.8430 0.01340 0.00786 0.0084 0.0028 1.0000
7.750 0.8658 0.01410 0.00864 0.0090 0.0027 1.0000
8.000 0.8869 0.01508 0.00974 0.0097 0.0025 1.0000
8.250 0.9057 0.01646 0.01126 0.0106 0.0024 1.0000
8.500 0.9213 0.01840 0.01340 0.0119 0.0023 1.0000
8.750 0.9391 0.01979 0.01493 0.0130 0.0023 1.0000
9.000 0.9564 0.02120 0.01649 0.0141 0.0023 1.0000
9.250 0.9730 0.02261 0.01806 0.0153 0.0023 1.0000
9.500 0.9875 0.02424 0.01988 0.0165 0.0023 1.0000
9.750 0.9992 0.02618 0.02202 0.0179 0.0023 1.0000
10.000 1.0086 0.02821 0.02426 0.0195 0.0023 1.0000
10.250 1.0140 0.03045 0.02673 0.0211 0.0023 1.0000
10.500 1.0205 0.03213 0.02859 0.0226 0.0023 1.0000
10.750 1.0252 0.03344 0.03003 0.0243 0.0022 1.0000
11.000 1.0083 0.03656 0.03335 0.0266 0.0023 1.0000
11.250 1.0091 0.03847 0.03539 0.0270 0.0022 1.0000
11.500 0.9973 0.04224 0.03935 0.0266 0.0022 1.0000
11.750 0.9927 0.04546 0.04271 0.0257 0.0022 1.0000
12.000 0.9845 0.04945 0.04685 0.0240 0.0022 1.0000
12.250 0.9589 0.05647 0.05406 0.0203 0.0022 1.0000
12.500 0.9492 0.06168 0.05940 0.0171 0.0022 1.0000
12.750 0.9239 0.07035 0.06824 0.0114 0.0022 1.0000
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Polar data table (+)
Polar graphs
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