E184 (8.33%) (e184-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: E184 (8.33%) (e184-il) Reynolds number: 1,000,000 Max Cl/Cd: 82.39 at α=3.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e184-il-1000000.txt Download as CSV file: xf-e184-il-1000000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.6836 0.08063 0.07933 0.0201 1.0000 0.0101
-8.500 -0.6977 0.07396 0.07269 0.0139 1.0000 0.0101
-8.250 -0.7080 0.06667 0.06534 0.0093 1.0000 0.0101
-8.000 -0.7149 0.05770 0.05619 0.0055 0.9466 0.0101
-7.750 -0.7252 0.05177 0.04991 0.0064 0.8900 0.0101
-7.500 -0.7282 0.04596 0.04374 0.0069 0.8645 0.0101
-7.250 -0.7253 0.04080 0.03817 0.0078 0.8456 0.0101
-7.000 -0.7381 0.02974 0.02640 0.0099 0.8311 0.0094
-6.750 -0.7257 0.02538 0.02139 0.0117 0.8174 0.0106
-6.250 -0.6872 0.01996 0.01527 0.0139 0.7936 0.0112
-6.000 -0.6639 0.01842 0.01351 0.0146 0.7830 0.0115
-5.750 -0.6399 0.01693 0.01178 0.0153 0.7734 0.0117
-5.500 -0.6154 0.01541 0.01001 0.0161 0.7642 0.0117
-5.250 -0.5902 0.01429 0.00873 0.0167 0.7556 0.0119
-5.000 -0.5643 0.01365 0.00799 0.0170 0.7475 0.0125
-4.750 -0.5387 0.01270 0.00691 0.0176 0.7396 0.0129
-4.500 -0.5130 0.01191 0.00600 0.0181 0.7325 0.0133
-4.250 -0.4870 0.01128 0.00526 0.0186 0.7252 0.0139
-4.000 -0.4607 0.01076 0.00465 0.0190 0.7188 0.0144
-3.750 -0.4343 0.01028 0.00409 0.0194 0.7120 0.0147
-3.500 -0.4077 0.00988 0.00359 0.0198 0.7060 0.0150
-3.250 -0.3807 0.00952 0.00317 0.0200 0.6997 0.0152
-3.000 -0.3537 0.00922 0.00278 0.0203 0.6938 0.0157
-2.750 -0.3267 0.00882 0.00227 0.0206 0.6881 0.0169
-2.500 -0.2993 0.00855 0.00195 0.0209 0.6823 0.0198
-2.250 -0.2719 0.00835 0.00173 0.0211 0.6769 0.0270
-2.000 -0.2458 0.00784 0.00149 0.0214 0.6712 0.0948
-1.750 -0.2195 0.00747 0.00134 0.0216 0.6658 0.1597
-1.500 -0.1932 0.00708 0.00122 0.0217 0.6606 0.2384
-1.250 -0.1680 0.00655 0.00110 0.0221 0.6550 0.3573
-1.000 -0.1427 0.00614 0.00100 0.0224 0.6498 0.4637
-0.750 -0.1181 0.00564 0.00093 0.0230 0.6445 0.5864
-0.500 -0.0963 0.00507 0.00086 0.0243 0.6391 0.7346
-0.250 -0.0702 0.00447 0.00092 0.0252 0.6340 0.9226
0.000 -0.0148 0.00460 0.00105 0.0194 0.6276 0.9653
0.250 0.0213 0.00471 0.00109 0.0177 0.6209 0.9764
0.500 0.0581 0.00479 0.00114 0.0159 0.6131 0.9844
0.750 0.0995 0.00485 0.00115 0.0130 0.6054 0.9886
1.000 0.1384 0.00492 0.00117 0.0106 0.5965 0.9932
1.250 0.1790 0.00494 0.00117 0.0078 0.5882 0.9963
1.500 0.2189 0.00496 0.00114 0.0051 0.5792 0.9992
1.750 0.2495 0.00497 0.00113 0.0045 0.5693 1.0000
2.000 0.2757 0.00498 0.00112 0.0049 0.5600 1.0000
2.250 0.3021 0.00501 0.00112 0.0052 0.5505 1.0000
2.500 0.3286 0.00505 0.00114 0.0055 0.5390 1.0000
2.750 0.3552 0.00509 0.00116 0.0057 0.5262 1.0000
3.000 0.3818 0.00514 0.00120 0.0060 0.5122 1.0000
3.250 0.4086 0.00522 0.00124 0.0062 0.4953 1.0000
3.500 0.4354 0.00534 0.00130 0.0064 0.4690 1.0000
3.750 0.4622 0.00561 0.00138 0.0064 0.4135 1.0000
4.000 0.4890 0.00610 0.00156 0.0062 0.3308 1.0000
4.250 0.5157 0.00686 0.00188 0.0058 0.2248 1.0000
4.500 0.5421 0.00742 0.00217 0.0056 0.1580 1.0000
4.750 0.5682 0.00804 0.00249 0.0055 0.0957 1.0000
5.000 0.5939 0.00878 0.00292 0.0054 0.0327 1.0000
5.250 0.6197 0.00940 0.00343 0.0055 0.0102 1.0000
5.500 0.6455 0.00976 0.00385 0.0058 0.0090 1.0000
5.750 0.6711 0.01017 0.00431 0.0061 0.0082 1.0000
6.000 0.6962 0.01073 0.00495 0.0065 0.0074 1.0000
6.250 0.7203 0.01158 0.00592 0.0069 0.0070 1.0000
6.500 0.7446 0.01221 0.00662 0.0073 0.0068 1.0000
6.750 0.7686 0.01278 0.00726 0.0078 0.0067 1.0000
7.000 0.7923 0.01341 0.00797 0.0083 0.0064 1.0000
7.250 0.8152 0.01416 0.00879 0.0089 0.0059 1.0000
7.500 0.8370 0.01511 0.00982 0.0097 0.0056 1.0000
7.750 0.8579 0.01620 0.01101 0.0106 0.0054 1.0000
8.000 0.8775 0.01761 0.01255 0.0117 0.0054 1.0000
8.250 0.8953 0.01959 0.01474 0.0131 0.0056 1.0000
8.500 0.9101 0.02262 0.01808 0.0148 0.0062 1.0000
18.250 0.6298 0.20218 0.20069 -0.0487 0.0055 1.0000
18.500 0.6345 0.20546 0.20398 -0.0505 0.0051 1.0000
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Polar data table (+)
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