E184 (8.33%) (e184-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: E184 (8.33%) (e184-il) Reynolds number: 100,000 Max Cl/Cd: 43.15 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e184-il-100000-n5.txt Download as CSV file: xf-e184-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.6527 0.10223 0.09791 0.0205 1.0000 0.0312
-9.250 -0.6516 0.09751 0.09322 0.0193 1.0000 0.0306
-9.000 -0.6507 0.09301 0.08875 0.0174 1.0000 0.0299
-8.750 -0.6525 0.08801 0.08379 0.0143 1.0000 0.0294
-8.500 -0.6570 0.08253 0.07837 0.0100 1.0000 0.0288
-8.250 -0.6642 0.07678 0.07264 0.0055 1.0000 0.0284
-8.000 -0.6685 0.07082 0.06662 0.0018 1.0000 0.0278
-7.750 -0.6706 0.06479 0.06047 -0.0012 1.0000 0.0272
-7.500 -0.6705 0.05865 0.05411 -0.0033 1.0000 0.0266
-7.250 -0.6669 0.05277 0.04793 -0.0045 1.0000 0.0260
-7.000 -0.6597 0.04719 0.04195 -0.0049 1.0000 0.0255
-6.750 -0.6487 0.04212 0.03640 -0.0048 1.0000 0.0252
-6.500 -0.6339 0.03774 0.03148 -0.0044 1.0000 0.0251
-6.250 -0.6157 0.03403 0.02725 -0.0039 1.0000 0.0252
-6.000 -0.5945 0.03092 0.02364 -0.0034 1.0000 0.0256
-5.750 -0.5708 0.02859 0.02091 -0.0032 1.0000 0.0270
-5.500 -0.5452 0.02669 0.01855 -0.0031 1.0000 0.0292
-5.250 -0.5171 0.02468 0.01616 -0.0033 0.9769 0.0301
-5.000 -0.4836 0.02277 0.01393 -0.0044 0.9438 0.0306
-4.750 -0.4551 0.02136 0.01227 -0.0043 0.9217 0.0312
-4.500 -0.4311 0.02002 0.01081 -0.0035 0.9037 0.0321
-4.250 -0.4091 0.01901 0.00967 -0.0022 0.8882 0.0337
-4.000 -0.3867 0.01825 0.00878 -0.0010 0.8742 0.0361
-3.750 -0.3637 0.01758 0.00794 0.0002 0.8617 0.0400
-3.500 -0.3404 0.01685 0.00707 0.0013 0.8500 0.0478
-3.250 -0.3176 0.01598 0.00639 0.0023 0.8393 0.0880
-3.000 -0.2957 0.01504 0.00593 0.0032 0.8297 0.1890
-2.750 -0.2746 0.01411 0.00562 0.0042 0.8205 0.3313
-2.500 -0.2549 0.01294 0.00543 0.0057 0.8112 0.5498
-2.250 -0.2268 0.01217 0.00532 0.0069 0.8039 0.7466
-2.000 -0.1623 0.01209 0.00532 0.0011 0.7970 0.8916
-1.750 -0.1136 0.01223 0.00522 -0.0024 0.7901 0.9444
-1.500 -0.0680 0.01231 0.00506 -0.0058 0.7822 0.9775
-1.250 -0.0180 0.01226 0.00478 -0.0104 0.7751 1.0000
-1.000 0.0056 0.01225 0.00462 -0.0098 0.7668 1.0000
-0.750 0.0299 0.01227 0.00449 -0.0093 0.7586 1.0000
-0.500 0.0535 0.01230 0.00438 -0.0085 0.7514 1.0000
-0.250 0.0786 0.01234 0.00433 -0.0082 0.7432 1.0000
0.000 0.1023 0.01240 0.00427 -0.0074 0.7367 1.0000
0.250 0.1278 0.01247 0.00429 -0.0071 0.7285 1.0000
0.500 0.1521 0.01255 0.00428 -0.0064 0.7220 1.0000
0.750 0.1777 0.01264 0.00434 -0.0061 0.7141 1.0000
1.000 0.2024 0.01274 0.00438 -0.0054 0.7075 1.0000
1.250 0.2280 0.01284 0.00449 -0.0051 0.6996 1.0000
1.500 0.2531 0.01295 0.00458 -0.0045 0.6925 1.0000
1.750 0.2784 0.01307 0.00470 -0.0040 0.6845 1.0000
2.000 0.3038 0.01318 0.00483 -0.0036 0.6759 1.0000
2.250 0.3282 0.01327 0.00494 -0.0027 0.6678 1.0000
2.500 0.3539 0.01338 0.00511 -0.0023 0.6571 1.0000
2.750 0.3790 0.01348 0.00524 -0.0017 0.6461 1.0000
3.000 0.4040 0.01355 0.00537 -0.0009 0.6344 1.0000
3.250 0.4289 0.01362 0.00549 -0.0002 0.6219 1.0000
3.500 0.4539 0.01367 0.00566 0.0006 0.6079 1.0000
3.750 0.4790 0.01372 0.00580 0.0013 0.5918 1.0000
4.000 0.5039 0.01376 0.00592 0.0021 0.5741 1.0000
4.250 0.5290 0.01381 0.00606 0.0029 0.5534 1.0000
4.500 0.5539 0.01386 0.00619 0.0038 0.5282 1.0000
4.750 0.5788 0.01396 0.00643 0.0045 0.4952 1.0000
5.000 0.6032 0.01413 0.00661 0.0054 0.4490 1.0000
5.250 0.6266 0.01452 0.00683 0.0062 0.3765 1.0000
5.500 0.6471 0.01567 0.00737 0.0068 0.2593 1.0000
5.750 0.6653 0.01748 0.00834 0.0069 0.1323 1.0000
6.000 0.6847 0.01897 0.00937 0.0073 0.0600 1.0000
6.250 0.7041 0.02054 0.01079 0.0082 0.0336 1.0000
6.500 0.7240 0.02186 0.01229 0.0091 0.0265 1.0000
6.750 0.7431 0.02317 0.01366 0.0100 0.0219 1.0000
7.000 0.7616 0.02455 0.01520 0.0111 0.0198 1.0000
7.250 0.7798 0.02602 0.01684 0.0123 0.0187 1.0000
7.500 0.7979 0.02765 0.01862 0.0135 0.0177 1.0000
7.750 0.8162 0.02937 0.02050 0.0147 0.0170 1.0000
8.000 0.8343 0.03131 0.02262 0.0158 0.0165 1.0000
8.250 0.8517 0.03350 0.02502 0.0170 0.0160 1.0000
8.500 0.8675 0.03597 0.02781 0.0181 0.0157 1.0000
8.750 0.8810 0.03876 0.03090 0.0192 0.0155 1.0000
9.000 0.8909 0.04184 0.03428 0.0202 0.0151 1.0000
9.250 0.8958 0.04533 0.03808 0.0213 0.0148 1.0000
9.500 0.8969 0.04837 0.04159 0.0225 0.0145 1.0000
9.750 0.8925 0.05173 0.04532 0.0236 0.0142 1.0000
10.000 0.8819 0.05498 0.04885 0.0247 0.0141 1.0000
10.250 0.8677 0.05857 0.05265 0.0249 0.0140 1.0000
10.500 0.8546 0.06255 0.05680 0.0239 0.0141 1.0000
10.750 0.8398 0.06723 0.06163 0.0218 0.0143 1.0000
11.000 0.8267 0.07218 0.06668 0.0192 0.0145 1.0000
11.250 0.8090 0.07850 0.07314 0.0151 0.0146 1.0000
11.500 0.7914 0.08575 0.08049 0.0101 0.0146 1.0000
11.750 0.7792 0.09258 0.08736 0.0059 0.0149 1.0000
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Polar data table (+)
Polar graphs
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