FX 61-184 AIRFOIL (fx61184-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 61-184 AIRFOIL (fx61184-il) Reynolds number: 200,000 Max Cl/Cd: 71.08 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx61184-il-200000-n5.txt Download as CSV file: xf-fx61184-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.000 -0.5386 0.09581 0.09185 -0.0687 1.0000 0.0147
-14.750 -0.5758 0.08447 0.08030 -0.0756 1.0000 0.0146
-14.500 -0.6040 0.07617 0.07178 -0.0802 1.0000 0.0145
-14.250 -0.6252 0.06982 0.06525 -0.0833 1.0000 0.0145
-14.000 -0.6453 0.06426 0.05947 -0.0856 1.0000 0.0147
-13.750 -0.6630 0.05954 0.05453 -0.0869 1.0000 0.0148
-13.500 -0.6729 0.05468 0.04941 -0.0888 0.9812 0.0151
-13.250 -0.6651 0.04993 0.04429 -0.0946 0.9378 0.0156
-13.000 -0.6364 0.04701 0.04123 -0.1011 0.9209 0.0160
-12.750 -0.6074 0.04418 0.03818 -0.1077 0.9043 0.0167
-12.500 -0.5819 0.04142 0.03512 -0.1129 0.8873 0.0175
-12.250 -0.5597 0.03895 0.03229 -0.1162 0.8721 0.0182
-12.000 -0.5384 0.03695 0.02995 -0.1182 0.8601 0.0188
-11.500 -0.4989 0.03422 0.02699 -0.1208 0.8419 0.0204
-11.250 -0.4803 0.03308 0.02572 -0.1213 0.8348 0.0211
-11.000 -0.4626 0.03205 0.02456 -0.1211 0.8282 0.0218
-10.750 -0.4440 0.03108 0.02344 -0.1208 0.8220 0.0226
-10.500 -0.4250 0.03020 0.02240 -0.1204 0.8168 0.0232
-10.250 -0.4090 0.02929 0.02146 -0.1198 0.8115 0.0243
-10.000 -0.3928 0.02847 0.02060 -0.1193 0.8067 0.0250
-9.750 -0.3764 0.02770 0.01977 -0.1188 0.8025 0.0261
-9.500 -0.3612 0.02694 0.01895 -0.1180 0.7979 0.0274
-9.250 -0.3464 0.02618 0.01811 -0.1170 0.7934 0.0283
-9.000 -0.3331 0.02536 0.01722 -0.1159 0.7893 0.0292
-8.750 -0.3210 0.02449 0.01632 -0.1149 0.7857 0.0304
-8.500 -0.3094 0.02370 0.01552 -0.1137 0.7813 0.0317
-8.250 -0.2974 0.02295 0.01473 -0.1125 0.7771 0.0338
-8.000 -0.2856 0.02222 0.01393 -0.1111 0.7732 0.0358
-7.750 -0.2774 0.02139 0.01306 -0.1095 0.7698 0.0380
-7.500 -0.2696 0.02075 0.01240 -0.1075 0.7658 0.0403
-7.250 -0.2581 0.02009 0.01168 -0.1062 0.7619 0.0435
-7.000 -0.2451 0.01932 0.01091 -0.1054 0.7582 0.0482
-6.750 -0.2282 0.01867 0.01022 -0.1050 0.7550 0.0557
-6.500 -0.2101 0.01805 0.00959 -0.1046 0.7521 0.0674
-6.250 -0.1928 0.01737 0.00901 -0.1041 0.7484 0.0892
-6.000 -0.1761 0.01639 0.00831 -0.1040 0.7447 0.1426
-5.750 -0.1590 0.01489 0.00738 -0.1048 0.7413 0.2641
-5.500 -0.1360 0.01369 0.00685 -0.1060 0.7385 0.4086
-5.250 -0.1089 0.01373 0.00716 -0.1059 0.7358 0.4810
-5.000 -0.0815 0.01390 0.00735 -0.1058 0.7321 0.5125
-4.750 -0.0529 0.01417 0.00755 -0.1058 0.7286 0.5376
-4.500 -0.0244 0.01469 0.00803 -0.1055 0.7255 0.5590
-4.250 0.0047 0.01508 0.00831 -0.1055 0.7227 0.5728
-4.000 0.0327 0.01535 0.00852 -0.1052 0.7202 0.5771
-3.750 0.0597 0.01541 0.00853 -0.1051 0.7164 0.5817
-3.500 0.0892 0.01529 0.00826 -0.1060 0.7128 0.5878
-3.250 0.1167 0.01537 0.00830 -0.1058 0.7096 0.5901
-3.000 0.1451 0.01543 0.00829 -0.1059 0.7068 0.5926
-2.750 0.1744 0.01544 0.00821 -0.1062 0.7042 0.5957
-2.500 0.2018 0.01540 0.00813 -0.1065 0.7001 0.5996
-2.250 0.2313 0.01529 0.00791 -0.1073 0.6963 0.6039
-2.000 0.2590 0.01532 0.00791 -0.1073 0.6929 0.6057
-1.750 0.2876 0.01533 0.00787 -0.1074 0.6900 0.6077
-1.500 0.3156 0.01535 0.00785 -0.1076 0.6866 0.6101
-1.250 0.3429 0.01534 0.00784 -0.1077 0.6823 0.6127
-1.000 0.3719 0.01529 0.00773 -0.1083 0.6784 0.6158
-0.750 0.4028 0.01518 0.00752 -0.1093 0.6751 0.6193
-0.500 0.4318 0.01516 0.00745 -0.1096 0.6722 0.6209
-0.250 0.4576 0.01520 0.00754 -0.1094 0.6673 0.6225
0.000 0.4851 0.01521 0.00756 -0.1095 0.6631 0.6243
0.250 0.5137 0.01519 0.00752 -0.1098 0.6596 0.6263
0.500 0.5432 0.01516 0.00744 -0.1103 0.6564 0.6284
0.750 0.5700 0.01518 0.00750 -0.1104 0.6510 0.6309
1.000 0.5989 0.01516 0.00745 -0.1109 0.6465 0.6336
1.250 0.6294 0.01509 0.00731 -0.1117 0.6426 0.6360
1.500 0.6562 0.01511 0.00738 -0.1117 0.6380 0.6373
1.750 0.6826 0.01515 0.00747 -0.1116 0.6327 0.6389
2.000 0.7105 0.01516 0.00748 -0.1117 0.6283 0.6406
2.250 0.7387 0.01517 0.00750 -0.1119 0.6241 0.6424
2.500 0.7651 0.01523 0.00761 -0.1119 0.6183 0.6443
2.750 0.7933 0.01523 0.00763 -0.1122 0.6135 0.6462
3.000 0.8222 0.01525 0.00762 -0.1127 0.6089 0.6486
3.250 0.8491 0.01531 0.00773 -0.1128 0.6024 0.6511
3.500 0.8771 0.01532 0.00774 -0.1131 0.5968 0.6529
3.750 0.9032 0.01538 0.00786 -0.1129 0.5907 0.6543
4.000 0.9291 0.01545 0.00799 -0.1128 0.5843 0.6558
4.250 0.9567 0.01549 0.00803 -0.1128 0.5788 0.6574
4.500 0.9813 0.01559 0.00822 -0.1125 0.5705 0.6592
4.750 1.0084 0.01564 0.00825 -0.1125 0.5635 0.6613
5.000 1.0328 0.01576 0.00844 -0.1121 0.5540 0.6636
5.250 1.0587 0.01586 0.00853 -0.1120 0.5453 0.6660
5.500 1.0839 0.01599 0.00867 -0.1118 0.5361 0.6681
5.750 1.1079 0.01613 0.00888 -0.1113 0.5280 0.6696
6.000 1.1316 0.01629 0.00909 -0.1108 0.5196 0.6711
6.250 1.1545 0.01648 0.00935 -0.1102 0.5108 0.6728
6.500 1.1776 0.01668 0.00958 -0.1095 0.5018 0.6747
6.750 1.1988 0.01691 0.00988 -0.1086 0.4912 0.6769
7.000 1.2197 0.01716 0.01017 -0.1077 0.4801 0.6794
7.250 1.2396 0.01745 0.01045 -0.1065 0.4682 0.6819
7.750 1.2734 0.01809 0.01118 -0.1033 0.4427 0.6859
8.000 1.2863 0.01845 0.01159 -0.1010 0.4298 0.6877
8.250 1.2980 0.01890 0.01207 -0.0986 0.4159 0.6897
8.500 1.3074 0.01948 0.01266 -0.0959 0.3995 0.6919
8.750 1.3143 0.02019 0.01335 -0.0931 0.3811 0.6944
9.000 1.3189 0.02108 0.01419 -0.0901 0.3620 0.6971
9.250 1.3223 0.02213 0.01519 -0.0873 0.3419 0.6999
9.500 1.3235 0.02336 0.01639 -0.0845 0.3207 0.7020
9.750 1.3222 0.02486 0.01782 -0.0816 0.2993 0.7042
10.000 1.3224 0.02644 0.01937 -0.0793 0.2779 0.7066
10.250 1.3225 0.02815 0.02103 -0.0771 0.2578 0.7090
10.500 1.3231 0.02996 0.02279 -0.0752 0.2398 0.7116
10.750 1.3243 0.03182 0.02461 -0.0735 0.2234 0.7142
11.000 1.3262 0.03371 0.02647 -0.0721 0.2074 0.7167
11.250 1.3281 0.03562 0.02839 -0.0706 0.1923 0.7190
11.500 1.3297 0.03765 0.03041 -0.0693 0.1784 0.7217
11.750 1.3326 0.03966 0.03243 -0.0682 0.1650 0.7247
12.000 1.3358 0.04172 0.03451 -0.0673 0.1518 0.7279
12.250 1.3386 0.04391 0.03671 -0.0665 0.1387 0.7311
12.500 1.3407 0.04621 0.03903 -0.0657 0.1262 0.7338
12.750 1.3425 0.04862 0.04146 -0.0650 0.1145 0.7366
13.000 1.3442 0.05115 0.04400 -0.0645 0.1037 0.7397
13.250 1.3455 0.05382 0.04668 -0.0641 0.0936 0.7431
13.500 1.3475 0.05650 0.04938 -0.0639 0.0841 0.7466
13.750 1.3495 0.05923 0.05217 -0.0637 0.0757 0.7499
14.000 1.3500 0.06220 0.05519 -0.0636 0.0685 0.7533
14.250 1.3512 0.06516 0.05822 -0.0636 0.0622 0.7574
14.500 1.3518 0.06830 0.06141 -0.0638 0.0573 0.7619
14.750 1.3528 0.07142 0.06461 -0.0640 0.0528 0.7663
15.000 1.3509 0.07497 0.06823 -0.0643 0.0493 0.7711
15.250 1.3538 0.07799 0.07139 -0.0647 0.0462 0.7769
15.500 1.3540 0.08141 0.07491 -0.0652 0.0435 0.7825
15.750 1.3519 0.08518 0.07877 -0.0659 0.0412 0.7887
16.250 1.3531 0.09212 0.08598 -0.0674 0.0372 0.8041
16.500 1.3522 0.09585 0.08984 -0.0683 0.0353 0.8138
16.750 1.3489 0.09992 0.09401 -0.0693 0.0337 0.8257
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