FX 61-184 AIRFOIL (fx61184-il) Xfoil prediction polar at RE=200,000 Ncrit=9
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Airfoil: FX 61-184 AIRFOIL (fx61184-il) Reynolds number: 200,000 Max Cl/Cd: 69.47 at α=8.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx61184-il-200000.txt Download as CSV file: xf-fx61184-il-200000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.250 -0.1812 0.09197 0.08875 -0.0913 0.9371 0.0839
-12.000 -0.5595 0.06036 0.05604 -0.1016 0.9575 0.0352
-11.750 -0.5530 0.05423 0.04972 -0.1064 0.9488 0.0343
-11.500 -0.5477 0.04852 0.04365 -0.1124 0.9393 0.0336
-11.250 -0.5402 0.04401 0.03861 -0.1185 0.9277 0.0345
-11.000 -0.5315 0.04090 0.03502 -0.1217 0.9153 0.0350
-10.750 -0.5222 0.03847 0.03216 -0.1226 0.9049 0.0353
-10.500 -0.5037 0.03555 0.02886 -0.1237 0.8980 0.0356
-10.250 -0.4787 0.03222 0.02538 -0.1241 0.8917 0.0367
-10.000 -0.4549 0.03105 0.02418 -0.1246 0.8852 0.0385
-9.750 -0.4321 0.02971 0.02267 -0.1245 0.8795 0.0397
-9.500 -0.4082 0.02834 0.02111 -0.1240 0.8738 0.0409
-9.250 -0.3782 0.02710 0.01967 -0.1242 0.8691 0.0421
-9.000 -0.3402 0.02578 0.01821 -0.1252 0.8657 0.0445
-8.750 -0.3136 0.02503 0.01752 -0.1246 0.8608 0.0467
-8.500 -0.2893 0.02442 0.01689 -0.1238 0.8558 0.0487
-8.250 -0.2657 0.02384 0.01624 -0.1231 0.8515 0.0514
-8.000 -0.2496 0.02322 0.01561 -0.1214 0.8468 0.0543
-7.750 -0.2395 0.02252 0.01498 -0.1193 0.8412 0.0577
-7.500 -0.2276 0.02194 0.01435 -0.1176 0.8364 0.0619
-7.250 -0.2256 0.02125 0.01366 -0.1147 0.8315 0.0660
-7.000 -0.2224 0.02047 0.01292 -0.1124 0.8260 0.0718
-6.750 -0.2141 0.01951 0.01197 -0.1112 0.8211 0.0828
-6.500 -0.2042 0.01842 0.01099 -0.1103 0.8170 0.1111
-6.250 -0.2066 0.01597 0.00960 -0.1098 0.8111 0.2873
-6.000 -0.1873 0.01532 0.00996 -0.1095 0.8069 0.4893
-5.750 -0.1577 0.01598 0.01056 -0.1091 0.8035 0.5311
-5.500 -0.1294 0.01674 0.01119 -0.1087 0.8000 0.5535
-5.250 -0.1050 0.01766 0.01211 -0.1071 0.7954 0.5652
-5.000 -0.0782 0.01845 0.01283 -0.1060 0.7914 0.5759
-4.750 -0.0500 0.01936 0.01364 -0.1050 0.7881 0.5887
-4.500 -0.0226 0.02149 0.01583 -0.1012 0.7854 0.5952
-4.250 -0.0018 0.02243 0.01677 -0.0988 0.7803 0.6060
-4.000 0.0229 0.02325 0.01757 -0.0966 0.7762 0.6092
-3.750 0.0505 0.02278 0.01692 -0.0982 0.7726 0.6203
-3.500 0.0783 0.02312 0.01720 -0.0972 0.7699 0.6220
-3.250 0.0982 0.02349 0.01758 -0.0952 0.7649 0.6247
-3.000 0.1218 0.02360 0.01765 -0.0943 0.7603 0.6291
-2.750 0.1504 0.02310 0.01701 -0.0960 0.7567 0.6375
-2.500 0.1781 0.02325 0.01709 -0.0953 0.7538 0.6396
-2.250 0.1975 0.02343 0.01729 -0.0937 0.7486 0.6428
-2.000 0.2269 0.02287 0.01660 -0.0962 0.7438 0.6518
-1.750 0.2527 0.02284 0.01653 -0.0954 0.7402 0.6539
-1.500 0.2808 0.02287 0.01649 -0.0951 0.7374 0.6560
-1.250 0.2995 0.02300 0.01666 -0.0936 0.7318 0.6591
-1.000 0.3260 0.02284 0.01646 -0.0941 0.7271 0.6636
-0.750 0.3598 0.02238 0.01588 -0.0965 0.7236 0.6692
-0.500 0.3881 0.02233 0.01579 -0.0962 0.7210 0.6711
-0.250 0.4056 0.02249 0.01601 -0.0946 0.7148 0.6737
0.000 0.4321 0.02239 0.01589 -0.0947 0.7102 0.6768
0.250 0.4658 0.02208 0.01550 -0.0965 0.7069 0.6811
0.500 0.5029 0.02172 0.01502 -0.0992 0.7042 0.6850
0.750 0.5180 0.02188 0.01530 -0.0971 0.6971 0.6868
1.000 0.5449 0.02177 0.01518 -0.0969 0.6929 0.6890
1.250 0.5770 0.02155 0.01491 -0.0979 0.6899 0.6914
1.500 0.6027 0.02154 0.01492 -0.0982 0.6847 0.6944
1.750 0.6324 0.02141 0.01479 -0.0995 0.6792 0.6983
2.000 0.6666 0.02111 0.01443 -0.1012 0.6756 0.7009
2.250 0.6982 0.02089 0.01419 -0.1018 0.6728 0.7024
2.500 0.7153 0.02108 0.01450 -0.1003 0.6657 0.7045
2.750 0.7441 0.02094 0.01436 -0.1006 0.6612 0.7069
3.000 0.7786 0.02066 0.01405 -0.1020 0.6580 0.7095
3.250 0.8033 0.02070 0.01415 -0.1022 0.6516 0.7121
3.500 0.8361 0.02051 0.01395 -0.1038 0.6462 0.7150
3.750 0.8702 0.02020 0.01361 -0.1051 0.6426 0.7173
4.000 0.8916 0.02027 0.01379 -0.1041 0.6363 0.7192
4.250 0.9190 0.02013 0.01369 -0.1042 0.6306 0.7210
4.500 0.9540 0.01976 0.01329 -0.1055 0.6264 0.7231
4.750 0.9758 0.01982 0.01345 -0.1049 0.6184 0.7255
5.000 1.0094 0.01951 0.01313 -0.1061 0.6127 0.7284
5.250 1.0383 0.01940 0.01306 -0.1068 0.6050 0.7313
5.500 1.0671 0.01917 0.01285 -0.1071 0.5981 0.7332
5.750 1.0940 0.01909 0.01283 -0.1071 0.5916 0.7350
6.000 1.1185 0.01906 0.01287 -0.1067 0.5840 0.7371
6.250 1.1481 0.01894 0.01277 -0.1072 0.5774 0.7393
6.500 1.1716 0.01897 0.01290 -0.1067 0.5686 0.7420
6.750 1.2000 0.01892 0.01287 -0.1071 0.5603 0.7451
7.000 1.2281 0.01888 0.01284 -0.1075 0.5507 0.7478
7.250 1.2487 0.01892 0.01298 -0.1064 0.5405 0.7498
7.500 1.2745 0.01889 0.01297 -0.1061 0.5310 0.7519
7.750 1.2945 0.01899 0.01315 -0.1049 0.5197 0.7543
8.000 1.3143 0.01915 0.01339 -0.1038 0.5082 0.7570
8.250 1.3345 0.01929 0.01357 -0.1028 0.4954 0.7600
8.500 1.3532 0.01948 0.01376 -0.1016 0.4810 0.7633
8.750 1.3662 0.01969 0.01401 -0.0992 0.4660 0.7658
9.000 1.3745 0.01996 0.01432 -0.0961 0.4506 0.7685
9.250 1.3805 0.02038 0.01476 -0.0927 0.4336 0.7714
9.500 1.3859 0.02097 0.01536 -0.0896 0.4155 0.7745
9.750 1.3909 0.02173 0.01609 -0.0867 0.3969 0.7778
10.000 1.3936 0.02264 0.01698 -0.0838 0.3784 0.7808
10.250 1.3938 0.02373 0.01806 -0.0806 0.3596 0.7840
10.500 1.3938 0.02503 0.01936 -0.0779 0.3398 0.7878
10.750 1.3934 0.02656 0.02085 -0.0755 0.3195 0.7917
11.000 1.3923 0.02832 0.02253 -0.0734 0.2998 0.7954
11.250 1.3905 0.03010 0.02430 -0.0711 0.2810 0.7986
11.500 1.3892 0.03202 0.02622 -0.0692 0.2623 0.8023
11.750 1.3879 0.03409 0.02825 -0.0676 0.2445 0.8064
12.000 1.3868 0.03632 0.03044 -0.0662 0.2275 0.8106
12.250 1.3846 0.03857 0.03268 -0.0647 0.2113 0.8145
12.500 1.3825 0.04094 0.03506 -0.0634 0.1957 0.8193
12.750 1.3805 0.04353 0.03762 -0.0625 0.1804 0.8245
13.000 1.3777 0.04621 0.04030 -0.0615 0.1652 0.8295
13.250 1.3741 0.04910 0.04319 -0.0607 0.1497 0.8350
13.500 1.3704 0.05223 0.04630 -0.0602 0.1336 0.8411
13.750 1.3648 0.05551 0.04958 -0.0596 0.1185 0.8471
14.000 1.3584 0.05907 0.05311 -0.0592 0.1051 0.8541
14.250 1.3506 0.06285 0.05685 -0.0589 0.0944 0.8618
14.500 1.3470 0.06621 0.06026 -0.0586 0.0849 0.8722
14.750 1.3422 0.06948 0.06361 -0.0581 0.0779 0.8870
15.000 1.3313 0.07187 0.06613 -0.0559 0.0736 0.9745
15.250 1.3310 0.07568 0.06992 -0.0569 0.0686 1.0000
15.500 1.3350 0.07902 0.07333 -0.0579 0.0640 1.0000
15.750 1.3352 0.08265 0.07691 -0.0588 0.0604 1.0000
16.000 1.3400 0.08575 0.08008 -0.0596 0.0572 1.0000
16.250 1.3439 0.08902 0.08343 -0.0606 0.0541 1.0000
16.500 1.3461 0.09246 0.08690 -0.0617 0.0514 1.0000
16.750 1.3504 0.09537 0.08978 -0.0622 0.0487 1.0000
17.000 1.3540 0.09873 0.09330 -0.0634 0.0466 1.0000
17.250 1.3567 0.10216 0.09681 -0.0646 0.0444 1.0000
17.500 1.3584 0.10570 0.10039 -0.0660 0.0424 1.0000
17.750 1.3634 0.10843 0.10308 -0.0666 0.0402 1.0000
18.000 1.3640 0.11237 0.10721 -0.0683 0.0386 1.0000
18.250 1.3658 0.11599 0.11095 -0.0698 0.0370 1.0000
18.500 1.3678 0.11952 0.11454 -0.0714 0.0355 1.0000
18.750 1.3708 0.12273 0.11776 -0.0728 0.0339 1.0000
19.000 1.3742 0.12583 0.12095 -0.0739 0.0323 1.0000
19.250 1.3717 0.13035 0.12566 -0.0762 0.0309 1.0000
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Polar data table (+)
Polar graphs
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