WORTMANN FX 60-126/1 AIRFOIL (fx601261-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: WORTMANN FX 60-126/1 AIRFOIL (fx601261-il) Reynolds number: 100,000 Max Cl/Cd: 60.46 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx601261-il-100000-n5.txt Download as CSV file: xf-fx601261-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: WORTMANN FX 60-126/1 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.3525 0.08601 0.08117 -0.0496 1.0000 0.0220
-9.000 -0.3574 0.08224 0.07748 -0.0501 1.0000 0.0217
-8.750 -0.3654 0.07813 0.07346 -0.0508 1.0000 0.0214
-8.500 -0.3823 0.07315 0.06858 -0.0518 1.0000 0.0210
-8.250 -0.4060 0.06922 0.06476 -0.0516 1.0000 0.0208
-8.000 -0.4321 0.06461 0.06020 -0.0535 0.9966 0.0206
-7.750 -0.4274 0.05242 0.04758 -0.0753 0.9778 0.0200
-7.500 -0.4116 0.04518 0.03974 -0.0859 0.9656 0.0193
-7.250 -0.3861 0.03931 0.03308 -0.0932 0.9573 0.0186
-7.000 -0.3570 0.03560 0.02868 -0.0971 0.9493 0.0182
-6.750 -0.3218 0.03296 0.02554 -0.1005 0.9447 0.0180
-6.500 -0.2930 0.03076 0.02304 -0.1019 0.9371 0.0179
-6.250 -0.2580 0.02872 0.02075 -0.1042 0.9327 0.0179
-6.000 -0.2246 0.02704 0.01887 -0.1058 0.9276 0.0179
-5.750 -0.1929 0.02566 0.01735 -0.1070 0.9213 0.0180
-5.500 -0.1574 0.02431 0.01592 -0.1088 0.9170 0.0181
-5.250 -0.1257 0.02314 0.01468 -0.1101 0.9106 0.0183
-5.000 -0.0914 0.02209 0.01353 -0.1118 0.9043 0.0185
-4.750 -0.0524 0.02105 0.01234 -0.1144 0.8999 0.0189
-4.500 -0.0220 0.02031 0.01144 -0.1153 0.8910 0.0194
-4.250 0.0157 0.01954 0.01048 -0.1175 0.8856 0.0201
-4.000 0.0469 0.01900 0.00977 -0.1183 0.8775 0.0210
-3.750 0.0820 0.01847 0.00908 -0.1197 0.8712 0.0222
-3.500 0.1143 0.01793 0.00848 -0.1207 0.8639 0.0255
-3.250 0.1485 0.01648 0.00772 -0.1232 0.8567 0.1613
-3.000 0.1812 0.01575 0.00757 -0.1247 0.8494 0.3067
-2.750 0.2118 0.01567 0.00764 -0.1251 0.8407 0.3818
-2.500 0.2418 0.01577 0.00774 -0.1251 0.8318 0.4289
-2.250 0.2722 0.01579 0.00769 -0.1252 0.8235 0.4507
-2.000 0.2997 0.01597 0.00785 -0.1248 0.8144 0.4805
-1.750 0.3299 0.01602 0.00783 -0.1248 0.8068 0.5000
-1.500 0.3572 0.01603 0.00776 -0.1245 0.7974 0.5107
-1.250 0.3880 0.01600 0.00759 -0.1247 0.7899 0.5229
-1.000 0.4138 0.01601 0.00759 -0.1241 0.7792 0.5325
-0.750 0.4422 0.01598 0.00748 -0.1239 0.7697 0.5420
-0.500 0.4708 0.01594 0.00736 -0.1238 0.7600 0.5519
-0.250 0.4974 0.01595 0.00736 -0.1233 0.7497 0.5608
0.000 0.5266 0.01594 0.00727 -0.1233 0.7413 0.5716
0.250 0.5532 0.01596 0.00729 -0.1229 0.7310 0.5818
0.500 0.5804 0.01596 0.00729 -0.1225 0.7209 0.5920
0.750 0.6090 0.01594 0.00721 -0.1223 0.7112 0.6030
1.000 0.6351 0.01596 0.00724 -0.1218 0.6992 0.6131
1.250 0.6618 0.01598 0.00727 -0.1214 0.6878 0.6231
1.500 0.6897 0.01600 0.00726 -0.1211 0.6778 0.6344
1.750 0.7167 0.01604 0.00732 -0.1207 0.6674 0.6463
2.000 0.7430 0.01610 0.00742 -0.1202 0.6563 0.6585
2.250 0.7695 0.01614 0.00748 -0.1197 0.6447 0.6723
2.500 0.7961 0.01618 0.00753 -0.1192 0.6329 0.6876
2.750 0.8216 0.01623 0.00763 -0.1185 0.6201 0.7042
3.000 0.8468 0.01630 0.00775 -0.1177 0.6070 0.7226
3.250 0.8716 0.01637 0.00790 -0.1169 0.5944 0.7442
3.500 0.8956 0.01642 0.00803 -0.1159 0.5824 0.7708
3.750 0.9177 0.01643 0.00813 -0.1144 0.5700 0.8075
4.000 0.9358 0.01631 0.00816 -0.1120 0.5568 0.8879
4.250 0.9628 0.01645 0.00828 -0.1118 0.5410 1.0000
4.500 0.9888 0.01672 0.00848 -0.1114 0.5234 1.0000
4.750 1.0140 0.01701 0.00872 -0.1110 0.5056 1.0000
5.000 1.0391 0.01732 0.00900 -0.1105 0.4888 1.0000
5.250 1.0636 0.01765 0.00929 -0.1099 0.4718 1.0000
5.500 1.0877 0.01800 0.00963 -0.1092 0.4544 1.0000
5.750 1.1113 0.01838 0.00998 -0.1085 0.4368 1.0000
6.000 1.1341 0.01879 0.01035 -0.1077 0.4185 1.0000
6.250 1.1561 0.01924 0.01076 -0.1067 0.3990 1.0000
6.500 1.1774 0.01971 0.01123 -0.1057 0.3775 1.0000
6.750 1.1974 0.02026 0.01170 -0.1045 0.3555 1.0000
7.000 1.2168 0.02085 0.01225 -0.1032 0.3324 1.0000
7.500 1.2523 0.02222 0.01349 -0.1003 0.2855 1.0000
7.750 1.2684 0.02301 0.01420 -0.0987 0.2628 1.0000
8.000 1.2841 0.02382 0.01498 -0.0971 0.2407 1.0000
8.250 1.2983 0.02471 0.01582 -0.0953 0.2224 1.0000
8.500 1.3125 0.02559 0.01670 -0.0936 0.2056 1.0000
8.750 1.3243 0.02651 0.01762 -0.0914 0.1915 1.0000
9.000 1.3349 0.02752 0.01863 -0.0892 0.1793 1.0000
9.250 1.3449 0.02859 0.01972 -0.0871 0.1682 1.0000
9.500 1.3538 0.02975 0.02090 -0.0849 0.1577 1.0000
9.750 1.3635 0.03090 0.02212 -0.0830 0.1476 1.0000
10.000 1.3718 0.03218 0.02345 -0.0810 0.1398 1.0000
10.250 1.3783 0.03362 0.02494 -0.0791 0.1333 1.0000
10.500 1.3859 0.03508 0.02648 -0.0774 0.1266 1.0000
10.750 1.3916 0.03671 0.02817 -0.0757 0.1193 1.0000
11.000 1.3983 0.03834 0.02989 -0.0743 0.1116 1.0000
11.250 1.4023 0.04022 0.03182 -0.0730 0.1044 1.0000
11.500 1.4079 0.04206 0.03376 -0.0718 0.0977 1.0000
11.750 1.4097 0.04430 0.03602 -0.0707 0.0927 1.0000
12.000 1.4141 0.04641 0.03827 -0.0698 0.0884 1.0000
12.250 1.4186 0.04859 0.04061 -0.0690 0.0842 1.0000
12.500 1.4201 0.05112 0.04324 -0.0683 0.0808 1.0000
12.750 1.4215 0.05375 0.04598 -0.0678 0.0773 1.0000
13.000 1.4256 0.05620 0.04863 -0.0675 0.0730 1.0000
13.250 1.4259 0.05911 0.05168 -0.0674 0.0692 1.0000
13.500 1.4254 0.06222 0.05489 -0.0674 0.0663 1.0000
13.750 1.4255 0.06537 0.05820 -0.0676 0.0637 1.0000
14.000 1.4240 0.06881 0.06180 -0.0679 0.0618 1.0000
14.250 1.4212 0.07253 0.06564 -0.0686 0.0602 1.0000
14.500 1.4175 0.07651 0.06973 -0.0694 0.0588 1.0000
14.750 1.4131 0.08069 0.07398 -0.0704 0.0575 1.0000
15.000 1.4124 0.08448 0.07800 -0.0713 0.0560 1.0000
15.250 1.4102 0.08860 0.08233 -0.0724 0.0544 1.0000
15.500 1.4068 0.09300 0.08692 -0.0738 0.0529 1.0000
15.750 1.4019 0.09775 0.09185 -0.0756 0.0513 1.0000
16.000 1.3954 0.10288 0.09714 -0.0778 0.0498 1.0000
16.250 1.3878 0.10833 0.10271 -0.0803 0.0485 1.0000
16.500 1.3803 0.11389 0.10839 -0.0829 0.0472 1.0000
16.750 1.3730 0.11967 0.11443 -0.0858 0.0455 1.0000
17.000 1.3643 0.12580 0.12079 -0.0890 0.0441 1.0000
17.250 1.3544 0.13233 0.12753 -0.0926 0.0427 1.0000
17.500 1.3440 0.13909 0.13446 -0.0965 0.0418 1.0000
17.750 1.3331 0.14615 0.14169 -0.1008 0.0410 1.0000
18.000 1.3219 0.15341 0.14910 -0.1053 0.0402 1.0000
18.250 1.3112 0.16068 0.15649 -0.1100 0.0394 1.0000
18.500 1.2968 0.16918 0.16514 -0.1155 0.0389 1.0000
18.750 1.2752 0.18001 0.17614 -0.1227 0.0386 1.0000
19.000 1.2494 0.19274 0.18897 -0.1310 0.0389 1.0000
19.250 1.2193 0.20825 0.20448 -0.1407 0.0390 1.0000
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