E184 (8.33%) (e184-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: E184 (8.33%) (e184-il) Reynolds number: 200,000 Max Cl/Cd: 53.54 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e184-il-200000-n5.txt Download as CSV file: xf-e184-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.6718 0.08829 0.08532 0.0204 1.0000 0.0158
-8.750 -0.6814 0.08151 0.07860 0.0154 1.0000 0.0155
-8.500 -0.7068 0.06989 0.06700 0.0058 1.0000 0.0145
-8.250 -0.7153 0.06110 0.05804 0.0015 1.0000 0.0141
-8.000 -0.7192 0.05442 0.05111 -0.0003 1.0000 0.0140
-7.750 -0.7189 0.04866 0.04502 -0.0010 1.0000 0.0140
-7.500 -0.7167 0.04319 0.03918 -0.0012 1.0000 0.0144
-7.250 -0.7042 0.04015 0.03591 -0.0013 1.0000 0.0152
-7.000 -0.6867 0.03804 0.03362 -0.0014 1.0000 0.0162
-6.750 -0.6700 0.03381 0.02889 -0.0012 0.9551 0.0165
-6.500 -0.6540 0.02986 0.02431 0.0002 0.9151 0.0163
-6.250 -0.6375 0.02706 0.02098 0.0020 0.8913 0.0164
-6.000 -0.6184 0.02484 0.01832 0.0037 0.8734 0.0166
-5.750 -0.5972 0.02296 0.01606 0.0050 0.8583 0.0169
-5.500 -0.5746 0.02137 0.01414 0.0062 0.8450 0.0174
-5.250 -0.5514 0.02001 0.01244 0.0073 0.8329 0.0179
-5.000 -0.5273 0.01881 0.01102 0.0081 0.8217 0.0184
-4.750 -0.5026 0.01795 0.00998 0.0089 0.8112 0.0197
-4.500 -0.4777 0.01719 0.00906 0.0096 0.8016 0.0209
-4.250 -0.4534 0.01632 0.00804 0.0104 0.7927 0.0212
-4.000 -0.4286 0.01554 0.00712 0.0111 0.7836 0.0215
-3.750 -0.4039 0.01482 0.00627 0.0118 0.7756 0.0220
-3.500 -0.3787 0.01418 0.00549 0.0124 0.7675 0.0232
-3.250 -0.3528 0.01370 0.00486 0.0129 0.7599 0.0254
-3.000 -0.3267 0.01331 0.00437 0.0134 0.7525 0.0297
-2.750 -0.3008 0.01281 0.00393 0.0138 0.7453 0.0516
-2.500 -0.2758 0.01224 0.00358 0.0143 0.7385 0.1118
-2.250 -0.2512 0.01161 0.00332 0.0146 0.7316 0.2023
-2.000 -0.2280 0.01088 0.00308 0.0152 0.7251 0.3313
-1.750 -0.2087 0.00989 0.00292 0.0166 0.7187 0.5293
-1.500 -0.1893 0.00911 0.00282 0.0188 0.7125 0.7004
-1.250 -0.1474 0.00872 0.00288 0.0168 0.7068 0.8620
-1.000 -0.0871 0.00880 0.00289 0.0105 0.7003 0.9305
-0.750 -0.0450 0.00892 0.00287 0.0078 0.6948 0.9589
-0.500 -0.0060 0.00899 0.00285 0.0056 0.6880 0.9784
-0.250 0.0365 0.00903 0.00277 0.0025 0.6823 0.9919
0.000 0.0774 0.00902 0.00268 -0.0004 0.6757 1.0000
0.250 0.1028 0.00902 0.00260 0.0001 0.6697 1.0000
0.500 0.1285 0.00904 0.00257 0.0004 0.6635 1.0000
0.750 0.1542 0.00906 0.00254 0.0008 0.6571 1.0000
1.000 0.1800 0.00910 0.00253 0.0012 0.6510 1.0000
1.250 0.2060 0.00913 0.00255 0.0016 0.6439 1.0000
1.500 0.2319 0.00917 0.00256 0.0020 0.6365 1.0000
1.750 0.2578 0.00921 0.00257 0.0024 0.6279 1.0000
2.000 0.2839 0.00924 0.00262 0.0027 0.6183 1.0000
2.250 0.3099 0.00929 0.00267 0.0032 0.6082 1.0000
2.500 0.3358 0.00934 0.00270 0.0036 0.5977 1.0000
2.750 0.3620 0.00938 0.00277 0.0040 0.5861 1.0000
3.000 0.3881 0.00944 0.00284 0.0044 0.5728 1.0000
3.250 0.4143 0.00950 0.00292 0.0048 0.5585 1.0000
3.500 0.4404 0.00958 0.00304 0.0052 0.5430 1.0000
3.750 0.4667 0.00966 0.00316 0.0055 0.5234 1.0000
4.000 0.4927 0.00977 0.00328 0.0059 0.5002 1.0000
4.250 0.5187 0.00992 0.00342 0.0063 0.4688 1.0000
4.500 0.5445 0.01017 0.00358 0.0067 0.4235 1.0000
4.750 0.5684 0.01104 0.00390 0.0067 0.2979 1.0000
5.000 0.5921 0.01214 0.00448 0.0065 0.1916 1.0000
5.250 0.6160 0.01303 0.00506 0.0064 0.1237 1.0000
5.500 0.6391 0.01404 0.00573 0.0065 0.0617 1.0000
5.750 0.6617 0.01515 0.00656 0.0068 0.0205 1.0000
6.000 0.6850 0.01599 0.00743 0.0073 0.0148 1.0000
6.250 0.7083 0.01673 0.00837 0.0078 0.0132 1.0000
6.500 0.7310 0.01757 0.00937 0.0085 0.0122 1.0000
6.750 0.7527 0.01852 0.01045 0.0091 0.0115 1.0000
7.000 0.7732 0.01962 0.01167 0.0100 0.0109 1.0000
7.250 0.7928 0.02081 0.01296 0.0109 0.0103 1.0000
7.500 0.8084 0.02277 0.01503 0.0121 0.0091 1.0000
7.750 0.8282 0.02391 0.01630 0.0130 0.0088 1.0000
8.000 0.8472 0.02526 0.01783 0.0141 0.0084 1.0000
8.250 0.8650 0.02702 0.01985 0.0153 0.0082 1.0000
8.500 0.8817 0.02899 0.02207 0.0165 0.0079 1.0000
8.750 0.8967 0.03125 0.02463 0.0178 0.0078 1.0000
9.000 0.9092 0.03377 0.02747 0.0191 0.0077 1.0000
9.250 0.9181 0.03656 0.03062 0.0204 0.0077 1.0000
9.500 0.9223 0.03966 0.03409 0.0219 0.0076 1.0000
9.750 0.9212 0.04295 0.03773 0.0234 0.0076 1.0000
10.000 0.9142 0.04614 0.04120 0.0249 0.0077 1.0000
10.250 0.9008 0.04935 0.04464 0.0262 0.0077 1.0000
10.500 0.8878 0.05299 0.04848 0.0260 0.0077 1.0000
10.750 0.8732 0.05734 0.05302 0.0246 0.0078 1.0000
11.000 0.8586 0.06217 0.05802 0.0222 0.0078 1.0000
11.250 0.8399 0.06838 0.06439 0.0184 0.0079 1.0000
11.500 0.8199 0.07581 0.07197 0.0133 0.0079 1.0000
11.750 0.8011 0.08433 0.08061 0.0072 0.0080 1.0000
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Polar data table (+)
Polar graphs
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