FX 61-168 AIRFOIL (fx61168-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: FX 61-168 AIRFOIL (fx61168-il) Reynolds number: 1,000,000 Max Cl/Cd: 129.7 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx61168-il-1000000.txt Download as CSV file: xf-fx61168-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.500 -0.5716 0.06537 0.06341 -0.0666 1.0000 0.0059
-12.250 -0.6019 0.05827 0.05615 -0.0699 1.0000 0.0059
-12.000 -0.6250 0.05319 0.05096 -0.0714 1.0000 0.0058
-11.750 -0.6650 0.04470 0.04209 -0.0752 0.9990 0.0058
-11.500 -0.6750 0.03845 0.03551 -0.0802 0.9958 0.0057
-11.250 -0.6719 0.03431 0.03104 -0.0832 0.9913 0.0059
-10.750 -0.6487 0.02915 0.02544 -0.0867 0.9750 0.0060
-10.500 -0.6563 0.02462 0.02048 -0.0853 0.9511 0.0063
-10.250 -0.6052 0.02250 0.01819 -0.0926 0.9348 0.0066
-10.000 -0.5228 0.02078 0.01625 -0.1058 0.9060 0.0070
-9.750 -0.4502 0.01954 0.01464 -0.1166 0.8525 0.0074
-9.500 -0.4268 0.01882 0.01362 -0.1169 0.8036 0.0077
-9.250 -0.4106 0.01823 0.01282 -0.1157 0.7721 0.0079
-9.000 -0.3962 0.01764 0.01206 -0.1141 0.7480 0.0081
-8.750 -0.3835 0.01704 0.01132 -0.1122 0.7281 0.0082
-8.500 -0.3661 0.01663 0.01079 -0.1111 0.7126 0.0084
-8.250 -0.3524 0.01574 0.00978 -0.1096 0.7004 0.0086
-8.000 -0.3387 0.01485 0.00879 -0.1083 0.6898 0.0091
-7.750 -0.3183 0.01439 0.00829 -0.1077 0.6812 0.0096
-7.500 -0.2958 0.01414 0.00797 -0.1073 0.6736 0.0102
-7.250 -0.2735 0.01373 0.00752 -0.1069 0.6670 0.0108
-7.000 -0.2506 0.01340 0.00711 -0.1065 0.6607 0.0112
-6.750 -0.2284 0.01286 0.00650 -0.1061 0.6554 0.0117
-6.500 -0.2061 0.01223 0.00582 -0.1058 0.6502 0.0124
-6.250 -0.1811 0.01191 0.00544 -0.1058 0.6454 0.0133
-6.000 -0.1549 0.01160 0.00510 -0.1059 0.6413 0.0142
-5.750 -0.1280 0.01135 0.00481 -0.1061 0.6374 0.0152
-5.500 -0.1017 0.01090 0.00432 -0.1063 0.6335 0.0175
-5.250 -0.0743 0.01070 0.00405 -0.1066 0.6295 0.0195
-5.000 -0.0464 0.01037 0.00371 -0.1070 0.6260 0.0239
-4.750 -0.0180 0.01003 0.00343 -0.1075 0.6223 0.0365
-4.500 0.0107 0.00957 0.00313 -0.1083 0.6186 0.0816
-4.250 0.0421 0.00842 0.00260 -0.1107 0.6150 0.2502
-4.000 0.0771 0.00742 0.00218 -0.1137 0.6119 0.4203
-3.750 0.1101 0.00702 0.00204 -0.1153 0.6091 0.5041
-3.500 0.1412 0.00689 0.00199 -0.1162 0.6060 0.5446
-3.250 0.1715 0.00687 0.00199 -0.1168 0.6030 0.5695
-3.000 0.2014 0.00693 0.00203 -0.1173 0.5997 0.5909
-2.750 0.2311 0.00701 0.00208 -0.1177 0.5964 0.6050
-2.500 0.2606 0.00707 0.00215 -0.1180 0.5934 0.6152
-2.250 0.2905 0.00713 0.00215 -0.1184 0.5903 0.6211
-2.000 0.3197 0.00715 0.00215 -0.1188 0.5874 0.6246
-1.750 0.3489 0.00722 0.00218 -0.1191 0.5844 0.6280
-1.500 0.3784 0.00730 0.00221 -0.1195 0.5815 0.6316
-1.250 0.4081 0.00733 0.00222 -0.1199 0.5793 0.6351
-1.000 0.4376 0.00735 0.00223 -0.1204 0.5767 0.6382
-0.750 0.4668 0.00738 0.00226 -0.1207 0.5739 0.6412
-0.500 0.4957 0.00744 0.00230 -0.1209 0.5707 0.6442
-0.250 0.5247 0.00755 0.00236 -0.1213 0.5669 0.6473
0.000 0.5541 0.00758 0.00238 -0.1217 0.5642 0.6503
0.250 0.5834 0.00760 0.00240 -0.1220 0.5610 0.6531
0.500 0.6122 0.00763 0.00244 -0.1223 0.5578 0.6556
0.750 0.6408 0.00770 0.00250 -0.1225 0.5545 0.6581
1.000 0.6696 0.00780 0.00257 -0.1228 0.5513 0.6607
1.250 0.6988 0.00783 0.00262 -0.1232 0.5486 0.6631
1.500 0.7280 0.00787 0.00266 -0.1235 0.5454 0.6652
1.750 0.7569 0.00792 0.00269 -0.1239 0.5417 0.6670
2.000 0.7850 0.00797 0.00273 -0.1241 0.5375 0.6692
2.250 0.8137 0.00800 0.00279 -0.1243 0.5336 0.6710
2.500 0.8423 0.00803 0.00285 -0.1246 0.5296 0.6728
2.750 0.8705 0.00809 0.00291 -0.1248 0.5250 0.6747
3.000 0.8985 0.00817 0.00299 -0.1249 0.5201 0.6767
3.250 0.9273 0.00821 0.00305 -0.1252 0.5153 0.6787
3.500 0.9555 0.00828 0.00311 -0.1255 0.5104 0.6805
3.750 0.9835 0.00837 0.00319 -0.1256 0.5047 0.6819
4.000 1.0117 0.00839 0.00324 -0.1259 0.4978 0.6838
4.250 1.0388 0.00848 0.00333 -0.1259 0.4911 0.6855
4.500 1.0666 0.00854 0.00342 -0.1260 0.4831 0.6872
4.750 1.0935 0.00866 0.00353 -0.1260 0.4742 0.6889
5.000 1.1204 0.00877 0.00364 -0.1259 0.4645 0.6906
5.250 1.1476 0.00889 0.00377 -0.1260 0.4562 0.6924
5.500 1.1738 0.00905 0.00392 -0.1259 0.4461 0.6942
6.000 1.2253 0.00945 0.00425 -0.1255 0.4198 0.6971
6.250 1.2501 0.00966 0.00443 -0.1251 0.4048 0.6991
6.500 1.2738 0.00994 0.00467 -0.1246 0.3876 0.7008
6.750 1.2971 0.01025 0.00492 -0.1240 0.3674 0.7024
7.000 1.3194 0.01061 0.00522 -0.1232 0.3474 0.7042
7.250 1.3407 0.01103 0.00555 -0.1223 0.3250 0.7060
7.500 1.3598 0.01156 0.00594 -0.1210 0.2959 0.7077
7.750 1.3771 0.01217 0.00639 -0.1194 0.2651 0.7093
8.000 1.3926 0.01283 0.00689 -0.1175 0.2341 0.7109
8.250 1.4060 0.01357 0.00746 -0.1153 0.2031 0.7123
8.500 1.4158 0.01427 0.00803 -0.1124 0.1762 0.7142
8.750 1.4249 0.01496 0.00862 -0.1094 0.1542 0.7159
9.000 1.4338 0.01569 0.00926 -0.1064 0.1335 0.7176
9.250 1.4421 0.01646 0.00995 -0.1034 0.1160 0.7194
9.500 1.4487 0.01731 0.01072 -0.1003 0.0983 0.7212
9.750 1.4546 0.01822 0.01157 -0.0972 0.0825 0.7229
10.000 1.4534 0.01951 0.01274 -0.0933 0.0621 0.7245
10.250 1.4560 0.02071 0.01388 -0.0902 0.0494 0.7261
10.500 1.4543 0.02224 0.01534 -0.0869 0.0357 0.7276
10.750 1.4544 0.02380 0.01689 -0.0842 0.0268 0.7298
11.000 1.4572 0.02535 0.01845 -0.0820 0.0207 0.7316
11.250 1.4593 0.02708 0.02019 -0.0801 0.0154 0.7333
11.500 1.4598 0.02907 0.02220 -0.0784 0.0100 0.7351
11.750 1.4584 0.03138 0.02452 -0.0768 0.0049 0.7368
12.000 1.4616 0.03341 0.02661 -0.0757 0.0038 0.7386
12.250 1.4658 0.03545 0.02872 -0.0748 0.0035 0.7402
12.500 1.4702 0.03753 0.03086 -0.0741 0.0032 0.7419
12.750 1.4748 0.03966 0.03307 -0.0734 0.0030 0.7439
13.250 1.4823 0.04424 0.03784 -0.0725 0.0028 0.7480
13.500 1.4858 0.04664 0.04032 -0.0721 0.0028 0.7499
13.750 1.4891 0.04912 0.04289 -0.0719 0.0027 0.7518
14.000 1.4914 0.05177 0.04563 -0.0717 0.0026 0.7537
14.250 1.4932 0.05456 0.04850 -0.0716 0.0026 0.7556
14.500 1.4945 0.05748 0.05151 -0.0717 0.0025 0.7573
14.750 1.4955 0.06054 0.05466 -0.0719 0.0025 0.7595
15.000 1.4960 0.06374 0.05797 -0.0722 0.0024 0.7616
15.250 1.4958 0.06709 0.06143 -0.0726 0.0024 0.7638
15.500 1.4950 0.07062 0.06505 -0.0731 0.0023 0.7661
15.750 1.4933 0.07436 0.06890 -0.0738 0.0023 0.7684
16.000 1.4908 0.07832 0.07296 -0.0746 0.0022 0.7708
16.250 1.4872 0.08254 0.07728 -0.0757 0.0022 0.7730
16.500 1.4834 0.08690 0.08176 -0.0769 0.0021 0.7755
16.750 1.4778 0.09164 0.08662 -0.0783 0.0021 0.7780
17.000 1.4721 0.09650 0.09159 -0.0798 0.0021 0.7806
17.250 1.4636 0.10193 0.09715 -0.0817 0.0020 0.7830
17.500 1.4520 0.10796 0.10331 -0.0840 0.0020 0.7852
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