WORTMANN FX 05-H-126 AIRFOIL (fx05h126-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: WORTMANN FX 05-H-126 AIRFOIL (fx05h126-il) Reynolds number: 200,000 Max Cl/Cd: 70.81 at α=8.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx05h126-il-200000-n5.txt Download as CSV file: xf-fx05h126-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: WORTMANN FX 05-H-126 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
------ -------- --------- --------- -------- -------- --------
-8.250 -0.3896 0.09178 0.08729 -0.0022 0.6089 0.0312
-8.000 -0.3969 0.08730 0.08286 -0.0073 0.6081 0.0328
-7.750 -0.4072 0.08283 0.07841 -0.0126 0.6072 0.0331
-7.500 -0.4079 0.07779 0.07329 -0.0176 0.6064 0.0333
-7.000 -0.3981 0.06866 0.06386 -0.0226 0.6047 0.0335
-6.750 -0.3929 0.06404 0.05924 -0.0231 0.6039 0.0342
-6.500 -0.3792 0.06209 0.05732 -0.0229 0.6028 0.0351
-6.250 -0.3712 0.05319 0.04801 -0.0251 0.6020 0.0255
-6.000 -0.3573 0.04987 0.04458 -0.0256 0.6009 0.0249
-5.750 -0.3420 0.04605 0.04054 -0.0260 0.5998 0.0244
-5.500 -0.3252 0.04208 0.03628 -0.0260 0.5988 0.0239
-5.250 -0.3071 0.03817 0.03202 -0.0256 0.5977 0.0236
-5.000 -0.2875 0.03460 0.02805 -0.0250 0.5967 0.0235
-4.750 -0.2659 0.03172 0.02476 -0.0243 0.5956 0.0243
-4.500 -0.2431 0.02920 0.02180 -0.0236 0.5946 0.0249
-4.250 -0.2193 0.02705 0.01927 -0.0229 0.5936 0.0249
-4.000 -0.1944 0.02525 0.01710 -0.0223 0.5927 0.0249
-3.750 -0.1686 0.02376 0.01527 -0.0218 0.5917 0.0252
-3.500 -0.1421 0.02256 0.01378 -0.0214 0.5907 0.0254
-3.250 -0.1152 0.02159 0.01256 -0.0211 0.5897 0.0258
-3.000 -0.0881 0.02074 0.01154 -0.0208 0.5889 0.0261
-2.750 -0.0615 0.01976 0.01051 -0.0207 0.5880 0.0274
-2.500 -0.0340 0.01928 0.01005 -0.0209 0.5867 0.0288
-2.250 -0.0066 0.01877 0.00952 -0.0209 0.5854 0.0296
-2.000 0.0204 0.01831 0.00903 -0.0208 0.5842 0.0303
-1.750 0.0472 0.01792 0.00862 -0.0206 0.5829 0.0312
-1.500 0.0740 0.01761 0.00828 -0.0205 0.5816 0.0322
-1.250 0.1009 0.01735 0.00798 -0.0204 0.5802 0.0333
-1.000 0.1275 0.01708 0.00768 -0.0202 0.5790 0.0354
-0.750 0.1546 0.01694 0.00753 -0.0201 0.5779 0.0395
-0.500 0.1816 0.01681 0.00739 -0.0200 0.5769 0.0448
-0.250 0.2085 0.01666 0.00727 -0.0198 0.5761 0.0603
0.000 0.2343 0.01637 0.00718 -0.0196 0.5752 0.1213
0.250 0.2492 0.01490 0.00714 -0.0177 0.5743 0.5407
1.250 0.4578 0.01465 0.00785 -0.0382 0.5669 1.0000
1.500 0.4837 0.01477 0.00791 -0.0380 0.5648 1.0000
1.750 0.5095 0.01486 0.00794 -0.0377 0.5631 1.0000
2.000 0.5353 0.01497 0.00799 -0.0374 0.5618 1.0000
2.250 0.5611 0.01506 0.00803 -0.0370 0.5606 1.0000
2.500 0.5869 0.01516 0.00807 -0.0367 0.5595 1.0000
2.750 0.6128 0.01530 0.00817 -0.0364 0.5583 1.0000
3.000 0.6395 0.01582 0.00880 -0.0370 0.5550 1.0000
3.250 0.6656 0.01616 0.00918 -0.0372 0.5524 1.0000
3.500 0.6916 0.01638 0.00941 -0.0371 0.5502 1.0000
3.750 0.7175 0.01654 0.00957 -0.0370 0.5485 1.0000
4.000 0.7434 0.01665 0.00970 -0.0367 0.5470 1.0000
4.250 0.7694 0.01671 0.00975 -0.0364 0.5457 1.0000
4.500 0.7954 0.01674 0.00977 -0.0360 0.5445 1.0000
4.750 0.8207 0.01731 0.01047 -0.0364 0.5410 1.0000
5.000 0.8459 0.01778 0.01104 -0.0366 0.5373 1.0000
5.250 0.8715 0.01795 0.01126 -0.0365 0.5347 1.0000
5.500 0.8975 0.01799 0.01133 -0.0362 0.5328 1.0000
5.750 0.9238 0.01793 0.01132 -0.0358 0.5312 1.0000
6.000 0.9506 0.01771 0.01110 -0.0353 0.5297 1.0000
6.250 0.9742 0.01824 0.01182 -0.0357 0.5215 1.0000
6.500 1.0023 0.01753 0.01112 -0.0350 0.5173 1.0000
6.750 1.0276 0.01756 0.01127 -0.0349 0.5099 1.0000
7.000 1.0545 0.01725 0.01101 -0.0346 0.5039 1.0000
7.250 1.0797 0.01729 0.01118 -0.0346 0.4944 1.0000
7.500 1.1065 0.01698 0.01094 -0.0343 0.4862 1.0000
7.750 1.1312 0.01714 0.01122 -0.0343 0.4752 1.0000
8.000 1.1558 0.01724 0.01141 -0.0342 0.4611 1.0000
8.250 1.1801 0.01733 0.01155 -0.0340 0.4415 1.0000
8.500 1.2053 0.01707 0.01122 -0.0334 0.4176 1.0000
8.750 1.2257 0.01731 0.01127 -0.0326 0.3862 1.0000
9.000 1.2384 0.01837 0.01214 -0.0317 0.3512 1.0000
9.250 1.2416 0.02031 0.01393 -0.0311 0.3131 1.0000
9.500 1.2294 0.02316 0.01662 -0.0295 0.2813 1.0000
9.750 1.2148 0.02592 0.01921 -0.0272 0.2536 1.0000
10.000 1.2031 0.02871 0.02183 -0.0254 0.2251 1.0000
10.250 1.1924 0.03152 0.02447 -0.0239 0.1973 1.0000
10.500 1.1844 0.03419 0.02701 -0.0225 0.1741 1.0000
10.750 1.1807 0.03657 0.02929 -0.0214 0.1543 1.0000
11.000 1.1780 0.03891 0.03155 -0.0204 0.1353 1.0000
11.250 1.1770 0.04118 0.03373 -0.0195 0.1179 1.0000
11.500 1.1769 0.04346 0.03592 -0.0188 0.1025 1.0000
11.750 1.1786 0.04568 0.03809 -0.0182 0.0927 1.0000
12.000 1.1818 0.04780 0.04019 -0.0176 0.0845 1.0000
12.250 1.1860 0.04987 0.04227 -0.0172 0.0779 1.0000
12.500 1.1908 0.05192 0.04434 -0.0168 0.0724 1.0000
12.750 1.1960 0.05397 0.04643 -0.0165 0.0669 1.0000
13.000 1.2032 0.05584 0.04838 -0.0162 0.0623 1.0000
13.250 1.2071 0.05809 0.05063 -0.0160 0.0577 1.0000
13.500 1.2156 0.05988 0.05252 -0.0158 0.0535 1.0000
13.750 1.2218 0.06194 0.05463 -0.0156 0.0488 1.0000
14.000 1.2270 0.06413 0.05686 -0.0156 0.0444 1.0000
14.250 1.2334 0.06624 0.05903 -0.0155 0.0391 1.0000
14.500 1.2378 0.06860 0.06144 -0.0155 0.0338 1.0000
14.750 1.2410 0.07113 0.06399 -0.0155 0.0282 1.0000
15.000 1.2431 0.07382 0.06671 -0.0156 0.0241 1.0000
15.250 1.2441 0.07671 0.06964 -0.0157 0.0204 1.0000
15.500 1.2438 0.07982 0.07277 -0.0160 0.0182 1.0000
15.750 1.2443 0.08286 0.07591 -0.0163 0.0164 1.0000
16.000 1.2431 0.08619 0.07930 -0.0167 0.0150 1.0000
16.250 1.2416 0.08963 0.08281 -0.0172 0.0140 1.0000
16.500 1.2409 0.09304 0.08635 -0.0178 0.0133 1.0000
16.750 1.2398 0.09653 0.08996 -0.0185 0.0126 1.0000
17.000 1.2380 0.10017 0.09372 -0.0193 0.0121 1.0000
17.250 1.2351 0.10407 0.09775 -0.0203 0.0117 1.0000
17.500 1.2315 0.10816 0.10195 -0.0214 0.0113 1.0000
17.750 1.2267 0.11248 0.10639 -0.0228 0.0110 1.0000
18.000 1.2204 0.11710 0.11111 -0.0243 0.0107 1.0000
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