WORTMANN FX 77-W-153 AIRFOIL (fx77w153-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: WORTMANN FX 77-W-153 AIRFOIL (fx77w153-il) Reynolds number: 100,000 Max Cl/Cd: 33.83 at α=8.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx77w153-il-100000-n5.txt Download as CSV file: xf-fx77w153-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.2452 0.10582 0.10005 -0.0122 0.5333 0.0623
-9.250 -0.2623 0.09685 0.09106 -0.0170 0.5338 0.0423
-8.750 -0.3632 0.09022 0.08429 -0.0177 0.5419 0.0368
-8.500 -0.3557 0.08750 0.08155 -0.0182 0.5358 0.0364
-8.250 -0.3521 0.08378 0.07782 -0.0204 0.5311 0.0358
-8.000 -0.3528 0.07893 0.07295 -0.0246 0.5276 0.0351
-7.750 -0.3589 0.07376 0.06771 -0.0284 0.5251 0.0343
-7.500 -0.3892 0.06020 0.05371 -0.0360 0.5265 0.0314
-7.250 -0.3840 0.05659 0.04990 -0.0363 0.5225 0.0312
-7.000 -0.3777 0.05277 0.04583 -0.0363 0.5184 0.0311
-6.750 -0.3700 0.04892 0.04165 -0.0360 0.5146 0.0309
-6.500 -0.3604 0.04517 0.03749 -0.0353 0.5112 0.0308
-6.000 -0.3338 0.03849 0.02983 -0.0332 0.5045 0.0310
-5.750 -0.3170 0.03558 0.02634 -0.0319 0.5010 0.0316
-5.500 -0.2949 0.03447 0.02515 -0.0315 0.4972 0.0325
-5.250 -0.2728 0.03319 0.02361 -0.0309 0.4939 0.0338
-5.000 -0.2504 0.03150 0.02150 -0.0300 0.4911 0.0351
-4.750 -0.2265 0.02967 0.01922 -0.0291 0.4875 0.0362
-4.500 -0.2014 0.02817 0.01744 -0.0285 0.4841 0.0372
-4.250 -0.1759 0.02718 0.01632 -0.0281 0.4810 0.0384
-4.000 -0.1497 0.02619 0.01514 -0.0276 0.4784 0.0402
-3.750 -0.1229 0.02519 0.01383 -0.0270 0.4762 0.0427
-3.500 -0.0970 0.02457 0.01321 -0.0267 0.4740 0.0458
-3.250 -0.0704 0.02401 0.01255 -0.0264 0.4715 0.0507
-3.000 -0.0439 0.02366 0.01215 -0.0261 0.4691 0.0572
-2.750 -0.0182 0.02313 0.01169 -0.0258 0.4669 0.0621
-2.500 0.0079 0.02266 0.01113 -0.0253 0.4649 0.0656
-2.250 0.0335 0.02228 0.01075 -0.0249 0.4630 0.0702
-2.000 0.0594 0.02198 0.01035 -0.0243 0.4613 0.0750
-1.750 0.0851 0.02168 0.00998 -0.0238 0.4597 0.0803
-1.500 0.1112 0.02144 0.00967 -0.0233 0.4578 0.0895
-1.250 0.1370 0.02112 0.00951 -0.0230 0.4550 0.1089
-1.000 0.1624 0.02063 0.00939 -0.0227 0.4524 0.1852
-0.750 0.1868 0.01972 0.00935 -0.0225 0.4500 0.4081
-0.500 0.2767 0.01863 0.00979 -0.0330 0.4465 0.9162
-0.250 0.3635 0.01903 0.00985 -0.0440 0.4436 0.9996
0.000 0.3890 0.01921 0.00981 -0.0437 0.4421 1.0000
0.250 0.4136 0.01945 0.00999 -0.0434 0.4401 1.0000
0.500 0.4382 0.01973 0.01020 -0.0431 0.4382 1.0000
0.750 0.4627 0.02001 0.01041 -0.0427 0.4363 1.0000
1.000 0.4871 0.02030 0.01063 -0.0423 0.4344 1.0000
1.250 0.5115 0.02060 0.01084 -0.0419 0.4326 1.0000
1.500 0.5359 0.02090 0.01106 -0.0414 0.4309 1.0000
1.750 0.5604 0.02119 0.01126 -0.0410 0.4293 1.0000
2.000 0.5848 0.02149 0.01146 -0.0405 0.4278 1.0000
2.250 0.6095 0.02177 0.01162 -0.0400 0.4263 1.0000
2.500 0.6328 0.02221 0.01208 -0.0395 0.4237 1.0000
2.750 0.6557 0.02266 0.01257 -0.0390 0.4205 1.0000
3.000 0.6790 0.02306 0.01296 -0.0384 0.4176 1.0000
3.250 0.7026 0.02340 0.01327 -0.0379 0.4152 1.0000
3.500 0.7267 0.02370 0.01351 -0.0373 0.4131 1.0000
3.750 0.7510 0.02398 0.01372 -0.0368 0.4112 1.0000
4.000 0.7758 0.02426 0.01390 -0.0362 0.4095 1.0000
4.250 0.7957 0.02500 0.01480 -0.0355 0.4061 1.0000
4.500 0.8164 0.02564 0.01552 -0.0348 0.4028 1.0000
4.750 0.8383 0.02613 0.01605 -0.0341 0.4000 1.0000
5.000 0.8613 0.02652 0.01642 -0.0335 0.3977 1.0000
5.250 0.8849 0.02687 0.01674 -0.0329 0.3958 1.0000
5.500 0.9091 0.02719 0.01702 -0.0324 0.3941 1.0000
5.750 0.9289 0.02792 0.01784 -0.0316 0.3916 1.0000
6.000 0.9434 0.02907 0.01919 -0.0304 0.3877 1.0000
6.250 0.9614 0.02987 0.02008 -0.0295 0.3846 1.0000
6.500 0.9821 0.03040 0.02063 -0.0287 0.3821 1.0000
6.750 1.0058 0.03064 0.02088 -0.0281 0.3799 1.0000
7.000 1.0319 0.03067 0.02084 -0.0276 0.3780 1.0000
7.250 1.0381 0.03221 0.02263 -0.0258 0.3726 1.0000
7.500 1.0529 0.03301 0.02352 -0.0245 0.3683 1.0000
7.750 1.0750 0.03324 0.02378 -0.0238 0.3656 1.0000
8.000 1.1003 0.03328 0.02381 -0.0232 0.3636 1.0000
8.250 1.1269 0.03331 0.02381 -0.0229 0.3621 1.0000
8.500 1.1071 0.03673 0.02760 -0.0195 0.3550 1.0000
8.750 1.1169 0.03788 0.02885 -0.0181 0.3516 1.0000
9.000 1.1370 0.03826 0.02928 -0.0173 0.3493 1.0000
9.250 1.1625 0.03829 0.02931 -0.0168 0.3477 1.0000
9.500 1.1912 0.03814 0.02916 -0.0166 0.3463 1.0000
10.000 1.0923 0.04958 0.04098 -0.0113 0.3309 1.0000
11.500 0.9175 0.09081 0.08253 -0.0209 0.2761 1.0000
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Polar data table (+)
Polar graphs
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