WORTMANN FX 77-W-153 AIRFOIL (fx77w153-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: WORTMANN FX 77-W-153 AIRFOIL (fx77w153-il) Reynolds number: 200,000 Max Cl/Cd: 61.47 at α=11.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx77w153-il-200000-n5.txt Download as CSV file: xf-fx77w153-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: WORTMANN FX 77-W-153 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.3865 0.08469 0.07956 -0.0140 0.4758 0.0222
-8.500 -0.3857 0.08051 0.07538 -0.0170 0.4730 0.0220
-8.250 -0.3887 0.07511 0.07000 -0.0223 0.4707 0.0217
-8.000 -0.3974 0.06927 0.06411 -0.0272 0.4690 0.0214
-7.750 -0.4030 0.06292 0.05764 -0.0311 0.4672 0.0210
-7.500 -0.4083 0.05613 0.05063 -0.0336 0.4655 0.0206
-7.250 -0.4137 0.04867 0.04280 -0.0345 0.4641 0.0201
-7.000 -0.4210 0.04008 0.03356 -0.0335 0.4629 0.0196
-6.750 -0.4154 0.03481 0.02765 -0.0319 0.4607 0.0195
-6.500 -0.4007 0.03174 0.02410 -0.0305 0.4582 0.0196
-6.250 -0.3821 0.02943 0.02140 -0.0294 0.4552 0.0197
-6.000 -0.3613 0.02753 0.01916 -0.0284 0.4521 0.0200
-5.750 -0.3390 0.02591 0.01720 -0.0276 0.4490 0.0204
-5.500 -0.3154 0.02448 0.01545 -0.0268 0.4461 0.0209
-5.250 -0.2910 0.02321 0.01385 -0.0260 0.4435 0.0215
-5.000 -0.2657 0.02209 0.01242 -0.0254 0.4412 0.0222
-4.750 -0.2400 0.02129 0.01152 -0.0249 0.4389 0.0228
-4.500 -0.2140 0.02067 0.01084 -0.0245 0.4366 0.0236
-4.250 -0.1878 0.02004 0.01009 -0.0241 0.4345 0.0248
-4.000 -0.1613 0.01948 0.00935 -0.0236 0.4326 0.0268
-3.750 -0.1356 0.01897 0.00886 -0.0233 0.4308 0.0287
-3.500 -0.1092 0.01852 0.00827 -0.0228 0.4291 0.0314
-3.250 -0.0835 0.01807 0.00782 -0.0224 0.4276 0.0337
-3.000 -0.0571 0.01776 0.00742 -0.0220 0.4262 0.0363
-2.750 -0.0304 0.01751 0.00715 -0.0217 0.4248 0.0387
-2.500 -0.0033 0.01733 0.00693 -0.0215 0.4234 0.0418
-2.250 0.0238 0.01714 0.00674 -0.0213 0.4220 0.0453
-2.000 0.0511 0.01702 0.00656 -0.0211 0.4206 0.0493
-1.750 0.0777 0.01678 0.00633 -0.0208 0.4188 0.0535
-1.500 0.1048 0.01662 0.00611 -0.0205 0.4167 0.0572
-1.250 0.1316 0.01642 0.00589 -0.0202 0.4147 0.0609
-1.000 0.1586 0.01626 0.00572 -0.0200 0.4129 0.0673
-0.750 0.1855 0.01613 0.00559 -0.0197 0.4113 0.0855
-0.500 0.2116 0.01591 0.00550 -0.0194 0.4101 0.1326
-0.250 0.2368 0.01558 0.00547 -0.0190 0.4090 0.2257
0.000 0.2593 0.01498 0.00548 -0.0183 0.4079 0.3898
0.250 0.2777 0.01421 0.00552 -0.0165 0.4068 0.6056
0.750 0.4036 0.01412 0.00625 -0.0293 0.4034 0.9670
1.000 0.4610 0.01435 0.00638 -0.0353 0.4017 0.9893
1.250 0.5165 0.01446 0.00639 -0.0411 0.4000 1.0000
1.500 0.5421 0.01458 0.00643 -0.0407 0.3984 1.0000
1.750 0.5677 0.01470 0.00647 -0.0403 0.3968 1.0000
2.000 0.5933 0.01484 0.00652 -0.0400 0.3953 1.0000
2.250 0.6189 0.01502 0.00661 -0.0396 0.3939 1.0000
2.500 0.6444 0.01520 0.00675 -0.0393 0.3924 1.0000
2.750 0.6698 0.01535 0.00692 -0.0389 0.3905 1.0000
3.000 0.6951 0.01552 0.00709 -0.0385 0.3886 1.0000
3.250 0.7204 0.01569 0.00727 -0.0381 0.3866 1.0000
3.500 0.7457 0.01586 0.00743 -0.0377 0.3847 1.0000
3.750 0.7709 0.01603 0.00757 -0.0374 0.3829 1.0000
4.000 0.7962 0.01620 0.00771 -0.0369 0.3812 1.0000
4.250 0.8215 0.01637 0.00785 -0.0366 0.3797 1.0000
4.500 0.8468 0.01657 0.00800 -0.0362 0.3782 1.0000
4.750 0.8717 0.01680 0.00824 -0.0357 0.3764 1.0000
5.000 0.8960 0.01703 0.00855 -0.0353 0.3741 1.0000
5.250 0.9204 0.01725 0.00881 -0.0348 0.3717 1.0000
5.500 0.9449 0.01745 0.00905 -0.0343 0.3694 1.0000
5.750 0.9695 0.01764 0.00925 -0.0339 0.3674 1.0000
6.000 0.9943 0.01783 0.00944 -0.0334 0.3655 1.0000
6.250 1.0191 0.01801 0.00961 -0.0330 0.3638 1.0000
6.500 1.0441 0.01821 0.00978 -0.0326 0.3621 1.0000
6.750 1.0670 0.01852 0.01019 -0.0320 0.3595 1.0000
7.000 1.0899 0.01880 0.01057 -0.0314 0.3566 1.0000
7.250 1.1132 0.01905 0.01090 -0.0308 0.3540 1.0000
7.500 1.1369 0.01927 0.01116 -0.0302 0.3517 1.0000
7.750 1.1607 0.01948 0.01139 -0.0297 0.3496 1.0000
8.000 1.1848 0.01968 0.01159 -0.0292 0.3477 1.0000
8.250 1.2090 0.01993 0.01184 -0.0287 0.3458 1.0000
8.500 1.2289 0.02036 0.01247 -0.0278 0.3427 1.0000
8.750 1.2498 0.02074 0.01297 -0.0270 0.3396 1.0000
9.000 1.2715 0.02104 0.01337 -0.0263 0.3367 1.0000
9.250 1.2937 0.02128 0.01366 -0.0256 0.3342 1.0000
9.500 1.3164 0.02148 0.01389 -0.0249 0.3320 1.0000
9.750 1.3371 0.02182 0.01432 -0.0241 0.3292 1.0000
10.000 1.3540 0.02235 0.01506 -0.0228 0.3248 1.0000
10.250 1.3732 0.02266 0.01548 -0.0218 0.3207 1.0000
10.500 1.3943 0.02273 0.01560 -0.0210 0.3169 1.0000
10.750 1.4105 0.02318 0.01622 -0.0197 0.3107 1.0000
11.000 1.4293 0.02331 0.01641 -0.0187 0.3048 1.0000
11.250 1.4470 0.02354 0.01669 -0.0175 0.2993 1.0000
11.500 1.4628 0.02391 0.01711 -0.0162 0.2937 1.0000
11.750 1.4785 0.02420 0.01741 -0.0149 0.2892 1.0000
12.000 1.4891 0.02485 0.01814 -0.0131 0.2843 1.0000
12.250 1.4946 0.02569 0.01906 -0.0108 0.2787 1.0000
12.500 1.5004 0.02657 0.01993 -0.0089 0.2734 1.0000
12.750 1.5019 0.02808 0.02158 -0.0074 0.2674 1.0000
13.000 1.5011 0.03002 0.02362 -0.0066 0.2608 1.0000
13.250 1.4986 0.03243 0.02611 -0.0063 0.2547 1.0000
13.500 1.4909 0.03575 0.02953 -0.0067 0.2482 1.0000
13.750 1.4838 0.03908 0.03288 -0.0072 0.2423 1.0000
14.000 1.4702 0.04339 0.03731 -0.0081 0.2370 1.0000
14.250 1.4584 0.04739 0.04136 -0.0087 0.2319 1.0000
14.500 1.4531 0.05051 0.04447 -0.0089 0.2273 1.0000
14.750 1.4328 0.05571 0.04984 -0.0099 0.2229 1.0000
15.000 1.4160 0.06042 0.05464 -0.0107 0.2179 1.0000
15.250 1.4110 0.06360 0.05782 -0.0110 0.2130 1.0000
15.500 1.3921 0.06893 0.06330 -0.0122 0.2083 1.0000
15.750 1.3754 0.07406 0.06854 -0.0134 0.2028 1.0000
16.000 1.3725 0.07732 0.07182 -0.0140 0.1972 1.0000
16.250 1.3568 0.08249 0.07710 -0.0153 0.1917 1.0000
16.500 1.3529 0.08598 0.08061 -0.0161 0.1857 1.0000
16.750 1.3456 0.09006 0.08473 -0.0171 0.1798 1.0000
17.000 1.3367 0.09439 0.08912 -0.0182 0.1733 1.0000
17.250 1.3320 0.09813 0.09287 -0.0192 0.1670 1.0000
17.500 1.3157 0.10379 0.09868 -0.0208 0.1603 1.0000
17.750 1.3068 0.10832 0.10325 -0.0222 0.1526 1.0000
|
Polar data table (+)
Polar graphs
<< Back to WORTMANN FX 77-W-153 AIRFOIL (fx77w153-il)