FX 61-168 AIRFOIL (fx61168-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 61-168 AIRFOIL (fx61168-il) Reynolds number: 500,000 Max Cl/Cd: 101.21 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx61168-il-500000-n5.txt Download as CSV file: xf-fx61168-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: FX 61-168 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.000 -0.5796 0.07067 0.06810 -0.0658 1.0000 0.0052
-12.750 -0.6342 0.05890 0.05601 -0.0719 1.0000 0.0050
-12.500 -0.6618 0.05287 0.04977 -0.0737 1.0000 0.0051
-12.250 -0.6804 0.04724 0.04387 -0.0762 0.9992 0.0051
-11.750 -0.6867 0.03808 0.03410 -0.0819 0.9903 0.0054
-11.500 -0.6860 0.03494 0.03072 -0.0825 0.9812 0.0054
-11.000 -0.6650 0.03016 0.02548 -0.0840 0.9410 0.0057
-10.750 -0.6128 0.02737 0.02233 -0.0926 0.9193 0.0059
-10.500 -0.5366 0.02456 0.01914 -0.1059 0.8921 0.0063
-10.000 -0.4470 0.02260 0.01660 -0.1169 0.8021 0.0070
-9.750 -0.4301 0.02197 0.01577 -0.1163 0.7736 0.0072
-9.250 -0.3997 0.02065 0.01411 -0.1139 0.7337 0.0079
-9.000 -0.3855 0.01997 0.01328 -0.1125 0.7189 0.0081
-8.750 -0.3715 0.01933 0.01251 -0.1110 0.7068 0.0084
-8.500 -0.3604 0.01862 0.01170 -0.1090 0.6965 0.0086
-8.250 -0.3506 0.01791 0.01092 -0.1070 0.6877 0.0088
-8.000 -0.3352 0.01728 0.01023 -0.1059 0.6794 0.0091
-7.750 -0.3173 0.01676 0.00964 -0.1051 0.6721 0.0095
-7.500 -0.2984 0.01624 0.00903 -0.1044 0.6651 0.0099
-7.000 -0.2575 0.01530 0.00794 -0.1032 0.6539 0.0109
-6.750 -0.2356 0.01486 0.00744 -0.1028 0.6488 0.0118
-6.250 -0.1892 0.01404 0.00652 -0.1023 0.6402 0.0136
-6.000 -0.1645 0.01368 0.00610 -0.1022 0.6358 0.0145
-5.750 -0.1396 0.01331 0.00567 -0.1022 0.6316 0.0158
-5.500 -0.1139 0.01299 0.00530 -0.1023 0.6278 0.0177
-5.250 -0.0871 0.01271 0.00498 -0.1025 0.6243 0.0201
-5.000 -0.0602 0.01240 0.00467 -0.1028 0.6208 0.0249
-4.750 -0.0330 0.01211 0.00439 -0.1031 0.6176 0.0344
-4.500 -0.0055 0.01179 0.00411 -0.1036 0.6144 0.0547
-4.250 0.0226 0.01129 0.00378 -0.1044 0.6113 0.1059
-4.000 0.0534 0.01000 0.00319 -0.1070 0.6078 0.2867
-3.750 0.0873 0.00908 0.00278 -0.1097 0.6042 0.4324
-3.500 0.1192 0.00875 0.00269 -0.1110 0.6007 0.5155
-3.250 0.1494 0.00871 0.00276 -0.1117 0.5978 0.5648
-3.000 0.1793 0.00876 0.00283 -0.1121 0.5950 0.5889
-2.750 0.2087 0.00882 0.00286 -0.1124 0.5919 0.5998
-2.500 0.2385 0.00885 0.00281 -0.1129 0.5888 0.6057
-2.250 0.2676 0.00889 0.00281 -0.1132 0.5859 0.6096
-2.000 0.2967 0.00896 0.00281 -0.1135 0.5830 0.6137
-1.750 0.3263 0.00899 0.00280 -0.1139 0.5796 0.6183
-1.500 0.3558 0.00902 0.00278 -0.1143 0.5759 0.6222
-1.250 0.3846 0.00907 0.00281 -0.1146 0.5725 0.6255
-1.000 0.4136 0.00913 0.00284 -0.1149 0.5696 0.6295
-0.750 0.4428 0.00921 0.00284 -0.1152 0.5668 0.6338
-0.500 0.4723 0.00924 0.00286 -0.1157 0.5638 0.6374
-0.250 0.5011 0.00929 0.00293 -0.1159 0.5609 0.6403
0.000 0.5300 0.00935 0.00297 -0.1162 0.5579 0.6432
0.250 0.5588 0.00941 0.00301 -0.1165 0.5548 0.6462
0.500 0.5877 0.00949 0.00303 -0.1168 0.5516 0.6490
0.750 0.6171 0.00952 0.00306 -0.1173 0.5477 0.6516
1.000 0.6454 0.00956 0.00311 -0.1175 0.5436 0.6535
1.250 0.6737 0.00962 0.00317 -0.1177 0.5398 0.6555
1.500 0.7019 0.00971 0.00324 -0.1178 0.5364 0.6575
1.750 0.7307 0.00975 0.00331 -0.1182 0.5326 0.6596
2.000 0.7593 0.00981 0.00337 -0.1184 0.5287 0.6620
2.250 0.7878 0.00988 0.00344 -0.1187 0.5250 0.6644
2.500 0.8162 0.00997 0.00350 -0.1190 0.5214 0.6666
2.750 0.8445 0.01001 0.00359 -0.1192 0.5166 0.6681
3.000 0.8721 0.01007 0.00368 -0.1193 0.5109 0.6698
3.250 0.8994 0.01017 0.00378 -0.1193 0.5057 0.6716
3.500 0.9274 0.01023 0.00388 -0.1195 0.5001 0.6736
3.750 0.9546 0.01033 0.00399 -0.1195 0.4940 0.6755
4.000 0.9820 0.01042 0.00409 -0.1196 0.4871 0.6774
4.250 1.0091 0.01052 0.00420 -0.1196 0.4798 0.6795
4.500 1.0363 0.01064 0.00433 -0.1197 0.4725 0.6815
4.750 1.0622 0.01077 0.00446 -0.1195 0.4627 0.6831
5.000 1.0882 0.01090 0.00461 -0.1193 0.4516 0.6846
5.250 1.1137 0.01107 0.00479 -0.1190 0.4411 0.6863
5.500 1.1385 0.01126 0.00498 -0.1186 0.4291 0.6881
5.750 1.1625 0.01150 0.00519 -0.1181 0.4156 0.6900
6.000 1.1867 0.01174 0.00542 -0.1176 0.4037 0.6920
6.250 1.2115 0.01197 0.00566 -0.1173 0.3930 0.6939
6.500 1.2351 0.01224 0.00592 -0.1168 0.3806 0.6957
6.750 1.2577 0.01256 0.00620 -0.1161 0.3661 0.6974
7.000 1.2792 0.01289 0.00653 -0.1152 0.3511 0.6990
7.250 1.3002 0.01325 0.00688 -0.1142 0.3359 0.7006
7.500 1.3181 0.01375 0.00730 -0.1127 0.3138 0.7021
7.750 1.3336 0.01434 0.00779 -0.1108 0.2868 0.7038
8.000 1.3455 0.01500 0.00833 -0.1083 0.2586 0.7057
8.250 1.3527 0.01581 0.00898 -0.1050 0.2278 0.7077
8.500 1.3582 0.01675 0.00976 -0.1016 0.1961 0.7095
8.750 1.3629 0.01774 0.01060 -0.0982 0.1695 0.7112
9.000 1.3675 0.01875 0.01150 -0.0950 0.1446 0.7127
9.250 1.3714 0.01981 0.01249 -0.0918 0.1255 0.7144
9.500 1.3760 0.02090 0.01352 -0.0889 0.1080 0.7161
9.750 1.3789 0.02213 0.01471 -0.0860 0.0923 0.7180
10.000 1.3830 0.02340 0.01597 -0.0835 0.0798 0.7198
10.250 1.3848 0.02492 0.01745 -0.0811 0.0664 0.7215
10.500 1.3866 0.02659 0.01911 -0.0790 0.0561 0.7233
10.750 1.3894 0.02831 0.02084 -0.0773 0.0471 0.7251
11.000 1.3911 0.03025 0.02278 -0.0757 0.0386 0.7267
11.250 1.3923 0.03236 0.02490 -0.0744 0.0315 0.7284
11.500 1.3936 0.03455 0.02712 -0.0733 0.0259 0.7302
11.750 1.3991 0.03648 0.02911 -0.0725 0.0227 0.7321
12.000 1.4021 0.03869 0.03138 -0.0717 0.0194 0.7339
12.250 1.4058 0.04090 0.03365 -0.0711 0.0163 0.7358
12.500 1.4086 0.04326 0.03606 -0.0706 0.0138 0.7376
12.750 1.4110 0.04573 0.03858 -0.0702 0.0113 0.7394
13.000 1.4110 0.04851 0.04141 -0.0698 0.0074 0.7411
13.500 1.4089 0.05455 0.04757 -0.0694 0.0036 0.7443
13.750 1.4105 0.05740 0.05052 -0.0694 0.0033 0.7460
14.000 1.4110 0.06046 0.05367 -0.0695 0.0030 0.7478
14.250 1.4128 0.06345 0.05677 -0.0697 0.0028 0.7500
14.500 1.4150 0.06647 0.05989 -0.0701 0.0027 0.7522
14.750 1.4164 0.06966 0.06319 -0.0705 0.0026 0.7544
15.000 1.4174 0.07298 0.06662 -0.0711 0.0025 0.7566
15.250 1.4182 0.07641 0.07015 -0.0717 0.0024 0.7586
15.500 1.4185 0.07998 0.07384 -0.0725 0.0023 0.7606
15.750 1.4183 0.08371 0.07771 -0.0735 0.0022 0.7627
16.000 1.4174 0.08759 0.08170 -0.0745 0.0022 0.7650
16.250 1.4160 0.09163 0.08586 -0.0757 0.0021 0.7673
16.500 1.4145 0.09577 0.09012 -0.0770 0.0021 0.7697
16.750 1.4119 0.10015 0.09462 -0.0785 0.0020 0.7720
17.000 1.4086 0.10471 0.09931 -0.0802 0.0020 0.7744
17.250 1.4051 0.10938 0.10411 -0.0820 0.0020 0.7769
17.500 1.4001 0.11437 0.10924 -0.0840 0.0019 0.7796
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