WORTMANN FX 60-126/1 AIRFOIL (fx601261-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: WORTMANN FX 60-126/1 AIRFOIL (fx601261-il) Reynolds number: 500,000 Max Cl/Cd: 84.22 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx601261-il-500000-n5.txt Download as CSV file: xf-fx601261-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.3413 0.10042 0.09813 -0.0408 1.0000 0.0119
-10.000 -0.3403 0.09709 0.09483 -0.0416 1.0000 0.0120
-8.750 -0.3469 0.06374 0.06158 -0.0647 0.9663 0.0127
-8.250 -0.3255 0.02933 0.02541 -0.1216 0.9053 0.0064
-8.000 -0.3018 0.02640 0.02210 -0.1247 0.8904 0.0063
-7.750 -0.2798 0.02404 0.01939 -0.1261 0.8777 0.0063
-7.500 -0.2569 0.02217 0.01719 -0.1268 0.8661 0.0062
-7.250 -0.2333 0.02062 0.01536 -0.1270 0.8551 0.0063
-7.000 -0.2089 0.01932 0.01381 -0.1271 0.8454 0.0064
-6.750 -0.1835 0.01826 0.01252 -0.1271 0.8370 0.0065
-6.500 -0.1577 0.01735 0.01144 -0.1271 0.8294 0.0066
-6.250 -0.1312 0.01664 0.01054 -0.1271 0.8226 0.0067
-6.000 -0.1045 0.01595 0.00973 -0.1271 0.8161 0.0067
-5.750 -0.0795 0.01471 0.00844 -0.1270 0.8091 0.0070
-5.500 -0.0531 0.01401 0.00770 -0.1271 0.8020 0.0074
-5.250 -0.0262 0.01345 0.00709 -0.1271 0.7939 0.0078
-5.000 0.0012 0.01290 0.00647 -0.1271 0.7866 0.0078
-4.750 0.0288 0.01236 0.00585 -0.1272 0.7789 0.0077
-4.500 0.0568 0.01188 0.00531 -0.1274 0.7720 0.0076
-4.250 0.0852 0.01144 0.00482 -0.1276 0.7646 0.0075
-4.000 0.1135 0.01106 0.00436 -0.1277 0.7572 0.0075
-3.750 0.1420 0.01072 0.00396 -0.1279 0.7483 0.0075
-3.500 0.1704 0.01044 0.00360 -0.1280 0.7399 0.0075
-3.250 0.1989 0.01021 0.00330 -0.1280 0.7310 0.0075
-3.000 0.2274 0.01002 0.00302 -0.1281 0.7229 0.0075
-2.750 0.2558 0.00987 0.00279 -0.1281 0.7135 0.0076
-2.500 0.2842 0.00973 0.00258 -0.1281 0.7036 0.0077
-2.250 0.3124 0.00964 0.00240 -0.1280 0.6932 0.0078
-2.000 0.3406 0.00956 0.00225 -0.1280 0.6825 0.0080
-1.750 0.3689 0.00950 0.00213 -0.1279 0.6726 0.0083
-1.500 0.3970 0.00946 0.00203 -0.1278 0.6629 0.0090
-1.250 0.4255 0.00934 0.00192 -0.1279 0.6524 0.0409
-1.000 0.4543 0.00904 0.00179 -0.1282 0.6415 0.1161
-0.750 0.4836 0.00841 0.00168 -0.1291 0.6290 0.2983
-0.500 0.5115 0.00827 0.00174 -0.1292 0.6148 0.3791
-0.250 0.5388 0.00832 0.00178 -0.1290 0.5975 0.4063
0.000 0.5660 0.00838 0.00185 -0.1288 0.5793 0.4404
0.250 0.5930 0.00849 0.00190 -0.1285 0.5604 0.4542
0.500 0.6201 0.00859 0.00196 -0.1283 0.5449 0.4649
0.750 0.6475 0.00870 0.00201 -0.1281 0.5311 0.4727
1.000 0.6747 0.00882 0.00208 -0.1278 0.5157 0.4799
1.250 0.7013 0.00898 0.00216 -0.1275 0.4959 0.4883
1.500 0.7273 0.00918 0.00226 -0.1271 0.4706 0.4966
1.750 0.7532 0.00940 0.00237 -0.1267 0.4443 0.5045
2.000 0.7790 0.00963 0.00250 -0.1263 0.4190 0.5120
2.250 0.8051 0.00985 0.00264 -0.1259 0.3982 0.5209
2.500 0.8313 0.01006 0.00279 -0.1256 0.3764 0.5295
2.750 0.8568 0.01034 0.00296 -0.1252 0.3525 0.5379
3.000 0.8824 0.01060 0.00315 -0.1248 0.3291 0.5458
3.250 0.9080 0.01088 0.00335 -0.1244 0.3072 0.5540
3.500 0.9336 0.01114 0.00355 -0.1240 0.2891 0.5624
3.750 0.9593 0.01139 0.00375 -0.1236 0.2726 0.5711
4.000 0.9844 0.01169 0.00400 -0.1232 0.2502 0.5811
4.250 1.0091 0.01202 0.00427 -0.1227 0.2312 0.5922
4.500 1.0341 0.01232 0.00453 -0.1222 0.2139 0.6045
5.000 1.0825 0.01306 0.00515 -0.1211 0.1749 0.6307
5.250 1.1072 0.01335 0.00546 -0.1206 0.1610 0.6450
5.500 1.1310 0.01372 0.00581 -0.1199 0.1430 0.6619
5.750 1.1546 0.01409 0.00617 -0.1193 0.1313 0.6818
6.000 1.1777 0.01448 0.00657 -0.1186 0.1164 0.7061
6.250 1.1993 0.01495 0.00702 -0.1177 0.0964 0.7387
6.500 1.2217 0.01524 0.00740 -0.1168 0.0887 0.7870
6.750 1.2354 0.01524 0.00767 -0.1138 0.0818 1.0000
7.000 1.2574 0.01574 0.00811 -0.1129 0.0666 1.0000
7.250 1.2787 0.01627 0.00856 -0.1120 0.0600 1.0000
7.500 1.3010 0.01668 0.00898 -0.1112 0.0560 1.0000
7.750 1.3229 0.01711 0.00941 -0.1103 0.0520 1.0000
8.000 1.3433 0.01763 0.00992 -0.1092 0.0475 1.0000
8.250 1.3650 0.01802 0.01034 -0.1083 0.0389 1.0000
8.500 1.3805 0.01883 0.01105 -0.1065 0.0312 1.0000
8.750 1.3970 0.01945 0.01167 -0.1048 0.0282 1.0000
9.000 1.4129 0.02003 0.01227 -0.1030 0.0264 1.0000
9.250 1.4289 0.02057 0.01284 -0.1012 0.0251 1.0000
9.500 1.4455 0.02107 0.01340 -0.0996 0.0242 1.0000
9.750 1.4612 0.02163 0.01401 -0.0978 0.0227 1.0000
10.000 1.4752 0.02230 0.01472 -0.0960 0.0191 1.0000
10.500 1.4820 0.02511 0.01749 -0.0900 0.0030 1.0000
10.750 1.4923 0.02614 0.01858 -0.0881 0.0028 1.0000
11.000 1.5021 0.02725 0.01978 -0.0863 0.0026 1.0000
11.250 1.5118 0.02841 0.02102 -0.0846 0.0025 1.0000
11.500 1.5206 0.02970 0.02240 -0.0830 0.0024 1.0000
11.750 1.5292 0.03105 0.02384 -0.0815 0.0024 1.0000
12.000 1.5370 0.03254 0.02542 -0.0801 0.0023 1.0000
12.250 1.5441 0.03413 0.02711 -0.0788 0.0023 1.0000
12.500 1.5499 0.03592 0.02901 -0.0776 0.0022 1.0000
12.750 1.5550 0.03784 0.03104 -0.0764 0.0022 1.0000
13.000 1.5587 0.03997 0.03328 -0.0754 0.0021 1.0000
13.250 1.5616 0.04227 0.03570 -0.0746 0.0020 1.0000
13.500 1.5630 0.04482 0.03838 -0.0738 0.0019 1.0000
13.750 1.5636 0.04755 0.04123 -0.0733 0.0019 1.0000
14.000 1.5632 0.05051 0.04432 -0.0730 0.0019 1.0000
14.250 1.5617 0.05373 0.04767 -0.0728 0.0018 1.0000
14.500 1.5592 0.05722 0.05129 -0.0730 0.0018 1.0000
14.750 1.5552 0.06105 0.05527 -0.0733 0.0018 1.0000
15.000 1.5500 0.06523 0.05961 -0.0740 0.0017 1.0000
15.250 1.5440 0.06968 0.06421 -0.0750 0.0017 1.0000
15.500 1.5355 0.07471 0.06939 -0.0763 0.0017 1.0000
15.750 1.5257 0.08016 0.07499 -0.0780 0.0017 1.0000
16.000 1.5180 0.08543 0.08040 -0.0799 0.0017 1.0000
16.250 1.5094 0.09099 0.08611 -0.0820 0.0017 1.0000
16.500 1.4996 0.09694 0.09220 -0.0844 0.0016 1.0000
16.750 1.4891 0.10318 0.09859 -0.0871 0.0016 1.0000
17.000 1.4770 0.10987 0.10543 -0.0902 0.0016 1.0000
17.250 1.4649 0.11670 0.11241 -0.0935 0.0016 1.0000
17.500 1.4520 0.12387 0.11973 -0.0972 0.0016 1.0000
17.750 1.4387 0.13124 0.12723 -0.1011 0.0016 1.0000
18.000 1.4252 0.13877 0.13491 -0.1053 0.0016 1.0000
18.250 1.4119 0.14640 0.14268 -0.1097 0.0016 1.0000
|
Polar data table (+)
Polar graphs
<< Back to WORTMANN FX 60-126/1 AIRFOIL (fx601261-il)