FX 61-184 AIRFOIL (fx61184-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: FX 61-184 AIRFOIL (fx61184-il) Reynolds number: 1,000,000 Max Cl/Cd: 120.66 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx61184-il-1000000-n5.txt Download as CSV file: xf-fx61184-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: FX 61-184 AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-19.750 -0.8997 0.10700 0.10411 -0.0550 1.0000 0.0048
-19.500 -0.9229 0.09902 0.09599 -0.0593 1.0000 0.0048
-19.250 -0.9447 0.09160 0.08842 -0.0632 1.0000 0.0047
-19.000 -0.9605 0.08534 0.08204 -0.0665 1.0000 0.0047
-18.750 -0.9684 0.08053 0.07713 -0.0689 1.0000 0.0050
-18.500 -0.9817 0.07504 0.07153 -0.0716 1.0000 0.0048
-18.250 -0.9870 0.07088 0.06727 -0.0736 1.0000 0.0049
-18.000 -0.9918 0.06691 0.06320 -0.0753 1.0000 0.0049
-17.750 -0.9928 0.06358 0.05979 -0.0767 1.0000 0.0051
-17.500 -0.9954 0.06010 0.05622 -0.0780 1.0000 0.0051
-17.250 -0.9929 0.05705 0.05309 -0.0796 0.9999 0.0053
-17.000 -0.9783 0.05358 0.04953 -0.0838 0.9979 0.0053
-16.750 -0.9584 0.05026 0.04612 -0.0885 0.9386 0.0056
-16.500 -0.9140 0.04708 0.04265 -0.0983 0.8884 0.0059
-16.250 -0.8829 0.04470 0.03999 -0.1044 0.8453 0.0060
-16.000 -0.8644 0.04248 0.03761 -0.1078 0.8252 0.0061
-15.750 -0.8468 0.04086 0.03586 -0.1098 0.8116 0.0065
-15.250 -0.8174 0.03768 0.03248 -0.1124 0.7939 0.0069
-14.750 -0.7897 0.03474 0.02935 -0.1143 0.7811 0.0071
-14.500 -0.7762 0.03337 0.02792 -0.1149 0.7753 0.0073
-14.000 -0.7495 0.03079 0.02520 -0.1159 0.7656 0.0077
-13.750 -0.7340 0.02978 0.02416 -0.1162 0.7615 0.0080
-13.500 -0.7189 0.02878 0.02311 -0.1164 0.7575 0.0082
-13.000 -0.6902 0.02676 0.02097 -0.1164 0.7508 0.0085
-12.750 -0.6738 0.02595 0.02012 -0.1164 0.7474 0.0089
-12.500 -0.6589 0.02505 0.01916 -0.1163 0.7440 0.0091
-12.250 -0.6430 0.02425 0.01830 -0.1161 0.7405 0.0093
-12.000 -0.6261 0.02353 0.01753 -0.1159 0.7376 0.0095
-11.750 -0.6119 0.02266 0.01662 -0.1155 0.7351 0.0096
-11.500 -0.5984 0.02176 0.01569 -0.1150 0.7326 0.0100
-11.250 -0.5831 0.02100 0.01491 -0.1146 0.7299 0.0103
-11.000 -0.5678 0.02027 0.01414 -0.1140 0.7269 0.0105
-10.750 -0.5517 0.01961 0.01345 -0.1134 0.7241 0.0108
-10.500 -0.5358 0.01897 0.01277 -0.1128 0.7213 0.0111
-10.250 -0.5179 0.01843 0.01221 -0.1123 0.7190 0.0118
-10.000 -0.5027 0.01776 0.01151 -0.1115 0.7163 0.0120
-9.750 -0.4871 0.01714 0.01086 -0.1106 0.7136 0.0122
-9.500 -0.4745 0.01642 0.01011 -0.1094 0.7109 0.0127
-9.250 -0.4614 0.01582 0.00950 -0.1081 0.7082 0.0134
-9.000 -0.4508 0.01526 0.00891 -0.1063 0.7057 0.0137
-8.750 -0.4335 0.01470 0.00831 -0.1058 0.7033 0.0142
-8.500 -0.4134 0.01416 0.00775 -0.1058 0.7012 0.0147
-8.250 -0.3916 0.01367 0.00722 -0.1058 0.6988 0.0152
-8.000 -0.3691 0.01325 0.00677 -0.1058 0.6962 0.0157
-7.750 -0.3460 0.01286 0.00636 -0.1057 0.6936 0.0165
-7.500 -0.3218 0.01253 0.00601 -0.1057 0.6912 0.0176
-7.250 -0.2968 0.01224 0.00568 -0.1058 0.6886 0.0187
-7.000 -0.2710 0.01193 0.00537 -0.1060 0.6864 0.0203
-6.750 -0.2447 0.01163 0.00508 -0.1063 0.6840 0.0225
-6.500 -0.2180 0.01136 0.00480 -0.1066 0.6814 0.0252
-6.250 -0.1910 0.01110 0.00454 -0.1069 0.6788 0.0289
-6.000 -0.1638 0.01084 0.00429 -0.1072 0.6762 0.0342
-5.750 -0.1364 0.01059 0.00406 -0.1076 0.6736 0.0415
-5.500 -0.1085 0.01033 0.00382 -0.1081 0.6714 0.0518
-5.250 -0.0801 0.01004 0.00359 -0.1087 0.6691 0.0668
-5.000 -0.0516 0.00967 0.00333 -0.1095 0.6665 0.0943
-4.750 -0.0228 0.00919 0.00302 -0.1104 0.6636 0.1428
-4.500 0.0066 0.00864 0.00270 -0.1116 0.6607 0.2090
-4.250 0.0375 0.00784 0.00228 -0.1134 0.6579 0.3150
-4.000 0.0700 0.00710 0.00191 -0.1155 0.6553 0.4246
-3.750 0.1015 0.00680 0.00181 -0.1167 0.6522 0.4846
-3.500 0.1321 0.00672 0.00181 -0.1174 0.6487 0.5211
-3.250 0.1621 0.00673 0.00181 -0.1179 0.6453 0.5343
-3.000 0.1918 0.00675 0.00179 -0.1184 0.6421 0.5418
-2.750 0.2217 0.00676 0.00178 -0.1189 0.6391 0.5459
-2.500 0.2517 0.00676 0.00177 -0.1194 0.6355 0.5499
-2.250 0.2815 0.00678 0.00175 -0.1199 0.6317 0.5533
-2.000 0.3111 0.00681 0.00172 -0.1203 0.6281 0.5559
-1.750 0.3406 0.00683 0.00172 -0.1208 0.6245 0.5583
-1.500 0.3704 0.00683 0.00172 -0.1213 0.6205 0.5606
-1.250 0.4000 0.00686 0.00173 -0.1217 0.6158 0.5631
-1.000 0.4291 0.00690 0.00173 -0.1220 0.6111 0.5656
-0.750 0.4587 0.00693 0.00174 -0.1225 0.6064 0.5679
-0.500 0.4881 0.00696 0.00175 -0.1229 0.6013 0.5699
-0.250 0.5171 0.00702 0.00176 -0.1233 0.5962 0.5715
0.000 0.5465 0.00704 0.00178 -0.1237 0.5915 0.5732
0.250 0.5757 0.00707 0.00181 -0.1241 0.5860 0.5749
0.500 0.6045 0.00713 0.00184 -0.1244 0.5807 0.5766
0.750 0.6336 0.00717 0.00188 -0.1248 0.5757 0.5782
1.000 0.6625 0.00723 0.00193 -0.1251 0.5695 0.5798
1.250 0.6908 0.00731 0.00198 -0.1253 0.5629 0.5815
1.500 0.7197 0.00737 0.00203 -0.1256 0.5560 0.5831
1.750 0.7477 0.00747 0.00209 -0.1258 0.5489 0.5845
2.000 0.7764 0.00754 0.00215 -0.1261 0.5427 0.5859
2.250 0.8043 0.00764 0.00222 -0.1263 0.5350 0.5872
2.500 0.8325 0.00772 0.00230 -0.1265 0.5273 0.5887
3.000 0.8873 0.00796 0.00249 -0.1267 0.5065 0.5915
3.250 0.9146 0.00808 0.00260 -0.1268 0.4977 0.5929
3.500 0.9421 0.00820 0.00271 -0.1269 0.4899 0.5945
3.750 0.9693 0.00833 0.00283 -0.1270 0.4820 0.5960
4.000 0.9961 0.00847 0.00296 -0.1269 0.4724 0.5975
4.250 1.0233 0.00860 0.00308 -0.1270 0.4650 0.5988
4.500 1.0498 0.00876 0.00323 -0.1269 0.4559 0.6001
4.750 1.0762 0.00892 0.00337 -0.1269 0.4457 0.6014
5.000 1.1016 0.00913 0.00354 -0.1266 0.4331 0.6025
5.250 1.1261 0.00937 0.00373 -0.1262 0.4183 0.6035
5.500 1.1505 0.00961 0.00395 -0.1258 0.4041 0.6052
5.750 1.1743 0.00987 0.00417 -0.1253 0.3892 0.6068
6.000 1.1972 0.01017 0.00442 -0.1247 0.3724 0.6083
6.250 1.2192 0.01051 0.00471 -0.1239 0.3543 0.6098
6.500 1.2397 0.01089 0.00502 -0.1228 0.3345 0.6112
6.750 1.2581 0.01135 0.00538 -0.1214 0.3118 0.6127
7.000 1.2726 0.01196 0.00584 -0.1193 0.2830 0.6141
7.250 1.2859 0.01252 0.00629 -0.1170 0.2569 0.6154
7.500 1.2931 0.01317 0.00680 -0.1136 0.2301 0.6168
7.750 1.2995 0.01392 0.00741 -0.1102 0.2040 0.6180
8.000 1.3077 0.01463 0.00802 -0.1072 0.1835 0.6192
8.250 1.3198 0.01521 0.00857 -0.1050 0.1716 0.6208
8.500 1.3308 0.01586 0.00920 -0.1027 0.1600 0.6226
8.750 1.3398 0.01664 0.00994 -0.1002 0.1467 0.6242
9.000 1.3464 0.01758 0.01083 -0.0977 0.1313 0.6257
9.250 1.3530 0.01862 0.01182 -0.0953 0.1175 0.6273
9.500 1.3593 0.01976 0.01292 -0.0931 0.1045 0.6288
9.750 1.3640 0.02108 0.01419 -0.0909 0.0899 0.6304
10.000 1.3692 0.02246 0.01552 -0.0889 0.0769 0.6319
10.250 1.3754 0.02385 0.01686 -0.0872 0.0664 0.6333
10.500 1.3821 0.02525 0.01824 -0.0856 0.0579 0.6347
10.750 1.3901 0.02661 0.01959 -0.0842 0.0513 0.6359
11.000 1.3990 0.02794 0.02093 -0.0830 0.0454 0.6378
11.250 1.4060 0.02944 0.02245 -0.0817 0.0397 0.6397
11.500 1.4127 0.03101 0.02401 -0.0804 0.0343 0.6415
11.750 1.4213 0.03246 0.02549 -0.0794 0.0309 0.6433
12.000 1.4288 0.03404 0.02708 -0.0783 0.0278 0.6450
12.250 1.4369 0.03559 0.02867 -0.0774 0.0252 0.6467
12.500 1.4457 0.03714 0.03025 -0.0766 0.0233 0.6485
12.750 1.4524 0.03891 0.03204 -0.0757 0.0211 0.6500
13.000 1.4611 0.04054 0.03372 -0.0751 0.0195 0.6515
13.250 1.4687 0.04233 0.03555 -0.0744 0.0182 0.6532
13.500 1.4763 0.04418 0.03744 -0.0739 0.0170 0.6551
13.750 1.4851 0.04596 0.03928 -0.0734 0.0162 0.6573
14.000 1.4929 0.04786 0.04124 -0.0730 0.0153 0.6596
14.250 1.4997 0.04991 0.04334 -0.0726 0.0143 0.6618
14.500 1.5059 0.05209 0.04556 -0.0723 0.0134 0.6640
14.750 1.5139 0.05411 0.04765 -0.0721 0.0129 0.6661
15.000 1.5203 0.05635 0.04995 -0.0720 0.0122 0.6679
15.250 1.5258 0.05873 0.05237 -0.0719 0.0112 0.6700
15.500 1.5304 0.06128 0.05498 -0.0719 0.0104 0.6722
15.750 1.5361 0.06376 0.05754 -0.0720 0.0096 0.6746
16.000 1.5404 0.06644 0.06027 -0.0721 0.0086 0.6770
16.250 1.5435 0.06932 0.06322 -0.0724 0.0077 0.6794
16.500 1.5453 0.07241 0.06636 -0.0727 0.0062 0.6817
16.750 1.5437 0.07603 0.07002 -0.0732 0.0042 0.6837
17.000 1.5421 0.07975 0.07381 -0.0738 0.0033 0.6859
17.250 1.5424 0.08328 0.07744 -0.0745 0.0030 0.6886
17.500 1.5424 0.08688 0.08112 -0.0753 0.0027 0.6914
17.750 1.5420 0.09059 0.08493 -0.0762 0.0025 0.6945
18.000 1.5407 0.09452 0.08894 -0.0773 0.0024 0.6975
18.500 1.5401 0.10220 0.09682 -0.0797 0.0022 0.7041
18.750 1.5389 0.10623 0.10095 -0.0811 0.0021 0.7078
19.000 1.5370 0.11042 0.10524 -0.0826 0.0020 0.7115
19.250 1.5352 0.11461 0.10953 -0.0842 0.0020 0.7151
|
Polar data table (+)
Polar graphs
<< Back to FX 61-184 AIRFOIL (fx61184-il)