WORTMANN FX 05-H-126 AIRFOIL (fx05h126-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: WORTMANN FX 05-H-126 AIRFOIL (fx05h126-il) Reynolds number: 500,000 Max Cl/Cd: 116.29 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx05h126-il-500000-n5.txt Download as CSV file: xf-fx05h126-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.750 -0.4367 0.07595 0.07241 -0.0065 0.5730 0.0129
-7.500 -0.4392 0.07070 0.06715 -0.0107 0.5723 0.0129
-7.250 -0.4385 0.06515 0.06154 -0.0145 0.5716 0.0129
-7.000 -0.4338 0.05971 0.05600 -0.0174 0.5708 0.0130
-6.750 -0.4263 0.05422 0.05036 -0.0195 0.5700 0.0131
-6.500 -0.4165 0.04867 0.04461 -0.0208 0.5693 0.0132
-6.250 -0.4044 0.04312 0.03880 -0.0214 0.5686 0.0134
-6.000 -0.3930 0.03603 0.03128 -0.0209 0.5679 0.0140
-5.750 -0.3844 0.02752 0.02201 -0.0190 0.5672 0.0144
-5.500 -0.3654 0.02401 0.01795 -0.0179 0.5664 0.0147
-5.250 -0.3421 0.02219 0.01578 -0.0172 0.5656 0.0149
-5.000 -0.3178 0.02072 0.01401 -0.0166 0.5647 0.0151
-4.750 -0.2941 0.01889 0.01191 -0.0161 0.5639 0.0154
-4.500 -0.2682 0.01798 0.01089 -0.0159 0.5631 0.0158
-4.250 -0.2416 0.01736 0.01017 -0.0157 0.5623 0.0162
-4.000 -0.2148 0.01671 0.00941 -0.0155 0.5615 0.0167
-3.750 -0.1879 0.01599 0.00854 -0.0153 0.5608 0.0170
-3.500 -0.1608 0.01532 0.00777 -0.0151 0.5600 0.0173
-3.250 -0.1337 0.01475 0.00710 -0.0149 0.5592 0.0177
-3.000 -0.1065 0.01424 0.00650 -0.0147 0.5583 0.0181
-2.750 -0.0791 0.01377 0.00598 -0.0145 0.5575 0.0185
-2.500 -0.0517 0.01337 0.00554 -0.0144 0.5566 0.0190
-2.250 -0.0243 0.01302 0.00516 -0.0142 0.5558 0.0193
-2.000 0.0032 0.01272 0.00483 -0.0141 0.5549 0.0197
-1.750 0.0302 0.01234 0.00443 -0.0140 0.5541 0.0204
-1.500 0.0572 0.01200 0.00408 -0.0138 0.5532 0.0214
-1.250 0.0848 0.01176 0.00384 -0.0137 0.5523 0.0221
-1.000 0.1125 0.01157 0.00363 -0.0137 0.5515 0.0229
-0.750 0.1404 0.01142 0.00346 -0.0136 0.5506 0.0238
-0.500 0.1684 0.01129 0.00331 -0.0136 0.5498 0.0248
-0.250 0.1965 0.01119 0.00318 -0.0137 0.5489 0.0258
0.000 0.2245 0.01107 0.00305 -0.0137 0.5479 0.0281
0.250 0.2526 0.01097 0.00297 -0.0137 0.5470 0.0336
0.500 0.2801 0.01081 0.00293 -0.0137 0.5463 0.0690
0.750 0.3070 0.01055 0.00290 -0.0136 0.5455 0.1503
1.000 0.3301 0.00984 0.00287 -0.0131 0.5445 0.3898
1.250 0.3432 0.00866 0.00288 -0.0103 0.5433 0.7449
1.500 0.4502 0.00827 0.00305 -0.0269 0.5412 0.9895
1.750 0.5020 0.00831 0.00306 -0.0322 0.5394 1.0000
2.000 0.5288 0.00834 0.00308 -0.0320 0.5378 1.0000
2.250 0.5557 0.00839 0.00311 -0.0319 0.5365 1.0000
2.500 0.5826 0.00844 0.00314 -0.0318 0.5353 1.0000
2.750 0.6095 0.00848 0.00317 -0.0317 0.5340 1.0000
3.000 0.6365 0.00853 0.00320 -0.0316 0.5328 1.0000
3.250 0.6635 0.00859 0.00325 -0.0315 0.5318 1.0000
3.500 0.6905 0.00866 0.00330 -0.0314 0.5306 1.0000
3.750 0.7174 0.00874 0.00336 -0.0313 0.5294 1.0000
4.000 0.7448 0.00882 0.00350 -0.0314 0.5279 1.0000
4.250 0.7721 0.00890 0.00362 -0.0314 0.5262 1.0000
4.500 0.7993 0.00898 0.00374 -0.0315 0.5243 1.0000
4.750 0.8266 0.00902 0.00382 -0.0315 0.5218 1.0000
5.000 0.8538 0.00902 0.00383 -0.0314 0.5191 1.0000
5.250 0.8810 0.00895 0.00373 -0.0313 0.5149 1.0000
5.500 0.9086 0.00894 0.00382 -0.0315 0.5082 1.0000
5.750 0.9359 0.00893 0.00383 -0.0315 0.5036 1.0000
6.000 0.9633 0.00897 0.00391 -0.0315 0.4989 1.0000
6.250 0.9907 0.00900 0.00399 -0.0316 0.4913 1.0000
6.500 1.0180 0.00904 0.00408 -0.0317 0.4829 1.0000
6.750 1.0453 0.00909 0.00414 -0.0318 0.4688 1.0000
7.000 1.0722 0.00922 0.00423 -0.0319 0.4480 1.0000
7.250 1.0984 0.00951 0.00445 -0.0321 0.4219 1.0000
7.500 1.1227 0.01020 0.00495 -0.0324 0.3848 1.0000
7.750 1.1454 0.01115 0.00573 -0.0328 0.3460 1.0000
8.000 1.1661 0.01229 0.00668 -0.0331 0.3005 1.0000
8.250 1.1829 0.01380 0.00796 -0.0333 0.2512 1.0000
8.500 1.1929 0.01588 0.00979 -0.0336 0.1984 1.0000
9.000 1.1924 0.02131 0.01498 -0.0338 0.1399 1.0000
9.250 1.1875 0.02339 0.01699 -0.0317 0.1227 1.0000
9.500 1.1809 0.02580 0.01926 -0.0301 0.0986 1.0000
9.750 1.1834 0.02762 0.02103 -0.0289 0.0873 1.0000
10.000 1.1880 0.02930 0.02268 -0.0280 0.0793 1.0000
10.250 1.1939 0.03090 0.02428 -0.0271 0.0732 1.0000
10.500 1.2009 0.03243 0.02583 -0.0263 0.0681 1.0000
10.750 1.2090 0.03390 0.02732 -0.0257 0.0633 1.0000
11.000 1.2154 0.03550 0.02891 -0.0249 0.0586 1.0000
11.250 1.2241 0.03695 0.03039 -0.0243 0.0550 1.0000
11.500 1.2329 0.03841 0.03188 -0.0238 0.0516 1.0000
11.750 1.2405 0.04003 0.03350 -0.0233 0.0471 1.0000
12.000 1.2493 0.04159 0.03510 -0.0228 0.0435 1.0000
12.250 1.2568 0.04329 0.03680 -0.0224 0.0386 1.0000
12.500 1.2653 0.04491 0.03844 -0.0220 0.0351 1.0000
12.750 1.2710 0.04686 0.04036 -0.0216 0.0294 1.0000
13.000 1.2757 0.04890 0.04238 -0.0212 0.0224 1.0000
13.250 1.2793 0.05109 0.04453 -0.0209 0.0159 1.0000
13.500 1.2817 0.05346 0.04690 -0.0205 0.0119 1.0000
13.750 1.2865 0.05559 0.04906 -0.0202 0.0102 1.0000
14.000 1.2924 0.05766 0.05120 -0.0200 0.0093 1.0000
14.250 1.2970 0.05991 0.05351 -0.0199 0.0085 1.0000
14.500 1.3014 0.06219 0.05585 -0.0197 0.0079 1.0000
14.750 1.3055 0.06457 0.05829 -0.0196 0.0074 1.0000
15.000 1.3110 0.06679 0.06060 -0.0196 0.0073 1.0000
15.250 1.3153 0.06921 0.06310 -0.0196 0.0070 1.0000
15.500 1.3188 0.07174 0.06572 -0.0197 0.0068 1.0000
15.750 1.3220 0.07432 0.06838 -0.0198 0.0064 1.0000
16.000 1.3239 0.07713 0.07126 -0.0201 0.0061 1.0000
16.250 1.3253 0.08002 0.07426 -0.0203 0.0060 1.0000
16.500 1.3251 0.08321 0.07752 -0.0207 0.0058 1.0000
16.750 1.3233 0.08661 0.08101 -0.0212 0.0056 1.0000
17.000 1.3203 0.09027 0.08476 -0.0218 0.0054 1.0000
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