WORTMANN FX 05-H-126 AIRFOIL (fx05h126-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: WORTMANN FX 05-H-126 AIRFOIL (fx05h126-il) Reynolds number: 500,000 Max Cl/Cd: 121.31 at α=8.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx05h126-il-500000.txt Download as CSV file: xf-fx05h126-il-500000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.4114 0.08770 0.08435 -0.0036 0.6055 0.0219
-8.000 -0.4194 0.08311 0.07980 -0.0080 0.6047 0.0220
-7.750 -0.4241 0.07858 0.07524 -0.0119 0.6040 0.0220
-7.500 -0.4224 0.07348 0.07007 -0.0156 0.6032 0.0221
-7.250 -0.4280 0.06691 0.06344 -0.0181 0.6025 0.0224
-7.000 -0.4202 0.06395 0.06044 -0.0187 0.6017 0.0227
-6.750 -0.4090 0.06128 0.05774 -0.0194 0.6010 0.0231
-6.500 -0.3964 0.05835 0.05476 -0.0204 0.6002 0.0235
-6.250 -0.3827 0.05513 0.05145 -0.0214 0.5994 0.0241
-6.000 -0.3677 0.05163 0.04783 -0.0223 0.5985 0.0250
-5.750 -0.3457 0.04657 0.04232 -0.0229 0.5977 0.0278
-5.500 -0.3384 0.04003 0.03545 -0.0229 0.5969 0.0286
-5.250 -0.3184 0.03827 0.03368 -0.0230 0.5960 0.0292
-5.000 -0.2971 0.03678 0.03213 -0.0230 0.5950 0.0301
-4.750 -0.2753 0.03483 0.03003 -0.0228 0.5940 0.0315
-4.500 -0.2534 0.03166 0.02618 -0.0212 0.5930 0.0358
-4.250 -0.2322 0.02911 0.02361 -0.0212 0.5919 0.0369
-4.000 -0.2081 0.02786 0.02230 -0.0211 0.5910 0.0383
-3.750 -0.1830 0.02670 0.02097 -0.0207 0.5901 0.0410
-3.500 -0.1593 0.02481 0.01866 -0.0197 0.5893 0.0460
-3.250 -0.1339 0.02363 0.01745 -0.0197 0.5885 0.0477
-3.000 -0.1076 0.02289 0.01659 -0.0194 0.5876 0.0510
-2.750 -0.0791 0.01712 0.00977 -0.0165 0.5868 0.0287
-2.500 -0.0515 0.01626 0.00883 -0.0163 0.5861 0.0287
-2.250 -0.0241 0.01546 0.00800 -0.0161 0.5852 0.0289
-2.000 0.0029 0.01484 0.00738 -0.0159 0.5843 0.0294
-1.750 0.0300 0.01440 0.00694 -0.0158 0.5832 0.0303
-1.500 0.0573 0.01408 0.00663 -0.0157 0.5820 0.0317
-1.250 0.0843 0.01377 0.00630 -0.0155 0.5809 0.0325
-1.000 0.1115 0.01351 0.00603 -0.0153 0.5799 0.0336
-0.750 0.1390 0.01333 0.00582 -0.0152 0.5788 0.0348
-0.500 0.1662 0.01311 0.00558 -0.0150 0.5779 0.0369
-0.250 0.1938 0.01297 0.00545 -0.0149 0.5768 0.0412
0.000 0.2214 0.01282 0.00534 -0.0148 0.5757 0.0558
0.250 0.2442 0.01199 0.00523 -0.0142 0.5747 0.2790
0.500 0.3175 0.00996 0.00530 -0.0240 0.5735 0.9714
0.750 0.3964 0.01018 0.00537 -0.0346 0.5717 0.9998
1.000 0.4240 0.01023 0.00539 -0.0347 0.5702 1.0000
1.250 0.4505 0.01031 0.00547 -0.0346 0.5687 1.0000
1.500 0.4770 0.01041 0.00554 -0.0345 0.5672 1.0000
1.750 0.5035 0.01051 0.00563 -0.0344 0.5657 1.0000
2.000 0.5300 0.01062 0.00572 -0.0342 0.5644 1.0000
2.250 0.5564 0.01070 0.00578 -0.0341 0.5630 1.0000
2.500 0.5828 0.01076 0.00582 -0.0338 0.5616 1.0000
2.750 0.6093 0.01082 0.00585 -0.0336 0.5603 1.0000
3.000 0.6357 0.01090 0.00591 -0.0334 0.5592 1.0000
3.250 0.6622 0.01100 0.00598 -0.0332 0.5581 1.0000
3.500 0.6884 0.01119 0.00614 -0.0330 0.5568 1.0000
3.750 0.7155 0.01133 0.00634 -0.0331 0.5550 1.0000
4.000 0.7425 0.01148 0.00654 -0.0332 0.5529 1.0000
4.250 0.7694 0.01158 0.00668 -0.0332 0.5509 1.0000
4.500 0.7962 0.01164 0.00676 -0.0331 0.5488 1.0000
4.750 0.8230 0.01164 0.00677 -0.0330 0.5470 1.0000
5.000 0.8498 0.01147 0.00657 -0.0326 0.5448 1.0000
5.250 0.8764 0.01128 0.00629 -0.0321 0.5421 1.0000
5.500 0.9037 0.01117 0.00630 -0.0322 0.5374 1.0000
5.750 0.9310 0.01099 0.00615 -0.0321 0.5335 1.0000
6.000 0.9582 0.01074 0.00588 -0.0318 0.5303 1.0000
6.250 0.9854 0.01055 0.00567 -0.0315 0.5264 1.0000
6.500 1.0128 0.01046 0.00569 -0.0316 0.5211 1.0000
6.750 1.0402 0.01030 0.00556 -0.0315 0.5169 1.0000
7.000 1.0675 0.01014 0.00540 -0.0314 0.5125 1.0000
7.250 1.0950 0.01005 0.00544 -0.0315 0.5049 1.0000
7.500 1.1223 0.00993 0.00533 -0.0315 0.4995 1.0000
7.750 1.1498 0.00994 0.00547 -0.0317 0.4901 1.0000
8.000 1.1770 0.00993 0.00553 -0.0318 0.4790 1.0000
8.250 1.2040 0.00997 0.00561 -0.0319 0.4638 1.0000
8.500 1.2301 0.01014 0.00573 -0.0320 0.4356 1.0000
8.750 1.2516 0.01108 0.00637 -0.0321 0.3813 1.0000
9.000 1.2680 0.01270 0.00770 -0.0323 0.3194 1.0000
9.250 1.2739 0.01531 0.00992 -0.0325 0.2458 1.0000
9.500 1.2697 0.01909 0.01347 -0.0340 0.1948 1.0000
9.750 1.2535 0.02217 0.01642 -0.0317 0.1708 1.0000
10.000 1.2410 0.02501 0.01911 -0.0297 0.1456 1.0000
10.250 1.2352 0.02746 0.02145 -0.0282 0.1232 1.0000
10.500 1.2291 0.02998 0.02381 -0.0269 0.1015 1.0000
10.750 1.2291 0.03205 0.02582 -0.0258 0.0899 1.0000
11.000 1.2328 0.03388 0.02765 -0.0250 0.0828 1.0000
11.250 1.2363 0.03572 0.02949 -0.0241 0.0767 1.0000
11.500 1.2432 0.03731 0.03111 -0.0235 0.0723 1.0000
11.750 1.2476 0.03918 0.03297 -0.0228 0.0677 1.0000
12.000 1.2554 0.04081 0.03465 -0.0223 0.0642 1.0000
12.250 1.2645 0.04235 0.03625 -0.0219 0.0603 1.0000
12.500 1.2708 0.04418 0.03807 -0.0214 0.0556 1.0000
12.750 1.2807 0.04569 0.03963 -0.0211 0.0515 1.0000
13.000 1.2880 0.04748 0.04142 -0.0208 0.0463 1.0000
13.250 1.2959 0.04923 0.04318 -0.0205 0.0400 1.0000
13.500 1.2990 0.05146 0.04533 -0.0201 0.0299 1.0000
13.750 1.2978 0.05421 0.04800 -0.0197 0.0215 1.0000
14.000 1.2993 0.05671 0.05050 -0.0194 0.0181 1.0000
14.250 1.3007 0.05932 0.05316 -0.0191 0.0160 1.0000
14.500 1.3044 0.06167 0.05557 -0.0190 0.0147 1.0000
14.750 1.3021 0.06478 0.05873 -0.0188 0.0135 1.0000
15.000 1.3035 0.06751 0.06154 -0.0188 0.0130 1.0000
15.250 1.3074 0.07001 0.06412 -0.0189 0.0124 1.0000
15.500 1.3086 0.07285 0.06704 -0.0189 0.0117 1.0000
15.750 1.3085 0.07587 0.07014 -0.0191 0.0114 1.0000
16.000 1.3089 0.07891 0.07326 -0.0194 0.0111 1.0000
16.250 1.3053 0.08251 0.07693 -0.0198 0.0107 1.0000
16.500 1.3012 0.08619 0.08067 -0.0202 0.0104 1.0000
16.750 1.2956 0.09010 0.08467 -0.0207 0.0102 1.0000
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