E184 (8.33%) (e184-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: E184 (8.33%) (e184-il) Reynolds number: 100,000 Max Cl/Cd: 44.45 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e184-il-100000.txt Download as CSV file: xf-e184-il-100000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.6281 0.10162 0.09739 0.0248 1.0000 0.1052
-8.500 -0.6406 0.09757 0.09344 0.0189 1.0000 0.1094
-8.250 -0.6675 0.09325 0.08919 0.0091 1.0000 0.1106
-8.000 -0.6380 0.08846 0.08443 0.0152 1.0000 0.1147
-7.750 -0.6358 0.08468 0.08068 0.0135 1.0000 0.1191
-7.250 -0.6374 0.07511 0.07110 0.0061 1.0000 0.1288
-7.000 -0.5673 0.06127 0.05763 0.0022 1.0000 0.1424
-6.500 -0.6191 0.06205 0.05780 -0.0011 1.0000 0.1547
-6.250 -0.6082 0.05833 0.05393 -0.0025 1.0000 0.1679
-5.750 -0.5699 0.03836 0.03183 -0.0061 1.0000 0.0692
-5.500 -0.5483 0.03442 0.02756 -0.0060 1.0000 0.0679
-5.250 -0.5247 0.03096 0.02368 -0.0057 1.0000 0.0667
-5.000 -0.4993 0.02763 0.01985 -0.0054 1.0000 0.0639
-4.750 -0.4728 0.02493 0.01664 -0.0051 1.0000 0.0625
-4.500 -0.4480 0.02290 0.01430 -0.0046 1.0000 0.0628
-4.250 -0.4308 0.02146 0.01270 -0.0031 1.0000 0.0642
-4.000 -0.4175 0.02034 0.01144 -0.0009 1.0000 0.0663
-3.750 -0.3880 0.01894 0.00997 -0.0017 0.9937 0.0730
-3.500 -0.3454 0.01738 0.00850 -0.0048 0.9836 0.0880
-3.250 -0.3108 0.01486 0.00681 -0.0064 0.9731 0.2089
-3.000 -0.2849 0.01259 0.00658 -0.0065 0.9627 0.6050
-2.750 -0.1834 0.01253 0.00709 -0.0155 0.9762 0.9483
-2.500 -0.0881 0.01238 0.00646 -0.0279 0.9848 1.0000
-2.250 -0.0430 0.01231 0.00610 -0.0325 0.9648 1.0000
-2.000 -0.0044 0.01230 0.00583 -0.0355 0.9473 1.0000
-1.750 0.0239 0.01240 0.00573 -0.0361 0.9304 1.0000
-1.500 0.0461 0.01256 0.00573 -0.0355 0.9149 1.0000
-1.250 0.0668 0.01274 0.00578 -0.0344 0.9009 1.0000
-1.000 0.0872 0.01293 0.00583 -0.0332 0.8883 1.0000
-0.750 0.1083 0.01312 0.00592 -0.0322 0.8763 1.0000
-0.500 0.1301 0.01333 0.00604 -0.0313 0.8651 1.0000
-0.250 0.1517 0.01356 0.00619 -0.0303 0.8548 1.0000
0.000 0.1721 0.01380 0.00635 -0.0289 0.8454 1.0000
0.250 0.1951 0.01404 0.00654 -0.0282 0.8353 1.0000
0.500 0.2181 0.01430 0.00676 -0.0275 0.8256 1.0000
0.750 0.2394 0.01456 0.00698 -0.0262 0.8169 1.0000
1.000 0.2624 0.01483 0.00725 -0.0254 0.8071 1.0000
1.250 0.2857 0.01512 0.00754 -0.0247 0.7972 1.0000
1.500 0.3072 0.01538 0.00779 -0.0233 0.7881 1.0000
1.750 0.3290 0.01562 0.00803 -0.0220 0.7781 1.0000
2.000 0.3520 0.01589 0.00834 -0.0211 0.7669 1.0000
2.250 0.3743 0.01615 0.00865 -0.0198 0.7559 1.0000
2.500 0.3955 0.01634 0.00887 -0.0182 0.7450 1.0000
2.750 0.4157 0.01645 0.00900 -0.0160 0.7342 1.0000
3.000 0.4376 0.01659 0.00919 -0.0144 0.7214 1.0000
3.250 0.4594 0.01670 0.00940 -0.0127 0.7080 1.0000
3.500 0.4808 0.01673 0.00949 -0.0108 0.6940 1.0000
3.750 0.5020 0.01669 0.00951 -0.0086 0.6793 1.0000
4.000 0.5234 0.01658 0.00946 -0.0064 0.6640 1.0000
4.250 0.5460 0.01650 0.00951 -0.0047 0.6446 1.0000
4.500 0.5677 0.01622 0.00935 -0.0024 0.6253 1.0000
4.750 0.5899 0.01592 0.00915 -0.0002 0.6027 1.0000
5.000 0.6124 0.01553 0.00886 0.0020 0.5761 1.0000
5.250 0.6351 0.01512 0.00856 0.0041 0.5405 1.0000
5.500 0.6578 0.01480 0.00828 0.0061 0.4814 1.0000
5.750 0.6753 0.01560 0.00821 0.0079 0.3011 1.0000
6.000 0.6874 0.01880 0.01000 0.0083 0.1146 1.0000
6.250 0.7018 0.02157 0.01232 0.0099 0.0648 1.0000
6.500 0.7198 0.02359 0.01422 0.0116 0.0555 1.0000
6.750 0.7412 0.02510 0.01580 0.0128 0.0489 1.0000
7.000 0.7617 0.02747 0.01812 0.0140 0.0444 1.0000
7.250 0.7849 0.02968 0.02064 0.0153 0.0429 1.0000
7.500 0.8070 0.03236 0.02366 0.0166 0.0423 1.0000
7.750 0.8268 0.03548 0.02718 0.0178 0.0424 1.0000
8.000 0.8436 0.03905 0.03118 0.0189 0.0430 1.0000
8.250 0.8570 0.04316 0.03569 0.0200 0.0440 1.0000
8.500 0.8691 0.04839 0.04116 0.0207 0.0455 1.0000
8.750 0.8670 0.05252 0.04638 0.0227 0.0514 1.0000
9.000 0.8085 0.04661 0.04114 0.0253 0.0533 1.0000
9.250 0.8167 0.05213 0.04674 0.0260 0.0586 1.0000
9.500 0.7785 0.05646 0.05146 0.0268 0.0601 1.0000
9.750 0.7490 0.06100 0.05614 0.0261 0.0605 1.0000
10.000 0.7211 0.06652 0.06176 0.0238 0.0606 1.0000
10.250 0.6931 0.07332 0.06862 0.0200 0.0605 1.0000
10.500 0.6602 0.08261 0.07795 0.0140 0.0610 1.0000
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Polar data table (+)
Polar graphs
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