WORTMANN FX 05-H-126 AIRFOIL (fx05h126-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: WORTMANN FX 05-H-126 AIRFOIL (fx05h126-il) Reynolds number: 1,000,000 Max Cl/Cd: 158.29 at α=7.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx05h126-il-1000000.txt Download as CSV file: xf-fx05h126-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.3667 0.08525 0.08257 0.0062 0.5773 0.0141
-8.500 -0.4381 0.08465 0.08182 -0.0008 0.5791 0.0139
-8.250 -0.4395 0.08122 0.07840 -0.0028 0.5783 0.0140
-8.000 -0.4459 0.07782 0.07503 -0.0049 0.5775 0.0141
-7.750 -0.4475 0.07446 0.07166 -0.0072 0.5767 0.0142
-7.500 -0.4448 0.07043 0.06760 -0.0102 0.5760 0.0143
-7.250 -0.4391 0.06656 0.06369 -0.0128 0.5753 0.0145
-6.250 -0.3937 0.04606 0.04258 -0.0201 0.5717 0.0174
-6.000 -0.3955 0.03606 0.03211 -0.0197 0.5713 0.0177
-5.750 -0.3778 0.03372 0.02965 -0.0196 0.5708 0.0180
-5.500 -0.3567 0.03219 0.02803 -0.0194 0.5703 0.0183
-5.250 -0.3351 0.03044 0.02616 -0.0192 0.5696 0.0186
-5.000 -0.3128 0.02870 0.02427 -0.0188 0.5689 0.0191
-4.750 -0.2898 0.02676 0.02214 -0.0183 0.5682 0.0204
-4.500 -0.2625 0.02567 0.02064 -0.0170 0.5674 0.0221
-4.250 -0.2472 0.02052 0.01509 -0.0158 0.5667 0.0232
-4.000 -0.2214 0.01966 0.01418 -0.0156 0.5658 0.0238
-3.750 -0.1979 0.01580 0.00976 -0.0139 0.5650 0.0195
-3.500 -0.1715 0.01426 0.00797 -0.0132 0.5641 0.0191
-3.250 -0.1442 0.01364 0.00728 -0.0130 0.5632 0.0195
-3.000 -0.1167 0.01309 0.00666 -0.0129 0.5624 0.0201
-2.750 -0.0894 0.01246 0.00595 -0.0126 0.5616 0.0204
-2.500 -0.0620 0.01197 0.00541 -0.0124 0.5608 0.0208
-2.250 -0.0345 0.01158 0.00497 -0.0122 0.5600 0.0212
-2.000 -0.0071 0.01125 0.00459 -0.0120 0.5592 0.0216
-1.750 0.0205 0.01098 0.00430 -0.0119 0.5583 0.0218
-1.500 0.0481 0.01083 0.00411 -0.0118 0.5572 0.0221
-1.250 0.0742 0.01034 0.00358 -0.0114 0.5564 0.0229
-1.000 0.1016 0.01005 0.00329 -0.0113 0.5559 0.0242
-0.750 0.1296 0.00985 0.00310 -0.0112 0.5552 0.0253
-0.500 0.1577 0.00970 0.00294 -0.0112 0.5544 0.0264
-0.250 0.1860 0.00959 0.00282 -0.0113 0.5536 0.0275
0.000 0.2142 0.00946 0.00268 -0.0113 0.5527 0.0294
0.250 0.2425 0.00933 0.00257 -0.0113 0.5515 0.0340
0.500 0.2698 0.00905 0.00249 -0.0112 0.5501 0.0914
0.750 0.2923 0.00820 0.00242 -0.0105 0.5488 0.3674
1.000 0.3078 0.00708 0.00237 -0.0083 0.5476 0.7113
1.250 0.3916 0.00646 0.00246 -0.0202 0.5462 0.9792
1.500 0.4392 0.00657 0.00252 -0.0244 0.5452 0.9920
1.750 0.4997 0.00665 0.00254 -0.0315 0.5441 1.0000
2.000 0.5264 0.00673 0.00259 -0.0313 0.5428 1.0000
2.250 0.5532 0.00683 0.00267 -0.0312 0.5416 1.0000
2.500 0.5801 0.00685 0.00269 -0.0311 0.5409 1.0000
2.750 0.6072 0.00687 0.00272 -0.0310 0.5399 1.0000
3.000 0.6342 0.00688 0.00275 -0.0309 0.5387 1.0000
3.250 0.6613 0.00691 0.00279 -0.0308 0.5375 1.0000
3.500 0.6885 0.00695 0.00283 -0.0308 0.5362 1.0000
3.750 0.7157 0.00698 0.00286 -0.0307 0.5348 1.0000
4.000 0.7428 0.00698 0.00286 -0.0306 0.5332 1.0000
4.250 0.7700 0.00696 0.00282 -0.0305 0.5312 1.0000
4.500 0.7971 0.00698 0.00281 -0.0304 0.5280 1.0000
4.750 0.8246 0.00691 0.00279 -0.0304 0.5249 1.0000
5.000 0.8521 0.00685 0.00275 -0.0304 0.5214 1.0000
5.250 0.8796 0.00683 0.00275 -0.0304 0.5186 1.0000
5.500 0.9070 0.00680 0.00272 -0.0304 0.5152 1.0000
5.750 0.9345 0.00680 0.00274 -0.0304 0.5109 1.0000
6.000 0.9622 0.00678 0.00278 -0.0305 0.5067 1.0000
6.250 0.9897 0.00677 0.00279 -0.0306 0.5018 1.0000
6.500 1.0173 0.00679 0.00284 -0.0307 0.4959 1.0000
6.750 1.0449 0.00682 0.00291 -0.0308 0.4897 1.0000
7.000 1.0724 0.00687 0.00298 -0.0309 0.4819 1.0000
7.250 1.0998 0.00696 0.00307 -0.0311 0.4696 1.0000
7.500 1.1270 0.00712 0.00321 -0.0313 0.4486 1.0000
7.750 1.1531 0.00763 0.00355 -0.0316 0.4096 1.0000
8.000 1.1776 0.00850 0.00421 -0.0321 0.3637 1.0000
8.250 1.1996 0.00975 0.00516 -0.0326 0.3009 1.0000
8.500 1.2167 0.01159 0.00657 -0.0331 0.2216 1.0000
8.750 1.2314 0.01331 0.00798 -0.0332 0.1663 1.0000
9.000 1.2458 0.01479 0.00931 -0.0333 0.1329 1.0000
9.250 1.2540 0.01747 0.01182 -0.0350 0.0970 1.0000
9.500 1.2573 0.01964 0.01395 -0.0347 0.0843 1.0000
9.750 1.2561 0.02142 0.01572 -0.0328 0.0772 1.0000
10.000 1.2621 0.02292 0.01723 -0.0317 0.0725 1.0000
10.250 1.2659 0.02465 0.01894 -0.0307 0.0658 1.0000
10.500 1.2760 0.02592 0.02025 -0.0300 0.0628 1.0000
10.750 1.2837 0.02740 0.02173 -0.0293 0.0589 1.0000
11.000 1.2900 0.02898 0.02331 -0.0285 0.0541 1.0000
11.250 1.3004 0.03026 0.02463 -0.0279 0.0516 1.0000
11.500 1.3082 0.03174 0.02610 -0.0272 0.0478 1.0000
11.750 1.3151 0.03332 0.02768 -0.0266 0.0434 1.0000
12.000 1.3236 0.03476 0.02915 -0.0260 0.0398 1.0000
12.250 1.3279 0.03658 0.03092 -0.0253 0.0326 1.0000
12.500 1.3299 0.03868 0.03297 -0.0246 0.0240 1.0000
12.750 1.3296 0.04105 0.03526 -0.0239 0.0156 1.0000
13.000 1.3319 0.04326 0.03746 -0.0234 0.0121 1.0000
13.250 1.3358 0.04534 0.03957 -0.0229 0.0102 1.0000
13.500 1.3426 0.04721 0.04149 -0.0225 0.0096 1.0000
13.750 1.3490 0.04913 0.04346 -0.0222 0.0090 1.0000
14.000 1.3554 0.05106 0.04544 -0.0219 0.0086 1.0000
14.250 1.3572 0.05352 0.04795 -0.0216 0.0080 1.0000
14.500 1.3610 0.05578 0.05028 -0.0213 0.0076 1.0000
14.750 1.3666 0.05792 0.05248 -0.0212 0.0074 1.0000
15.000 1.3707 0.06024 0.05487 -0.0211 0.0073 1.0000
15.250 1.3762 0.06241 0.05711 -0.0210 0.0070 1.0000
15.500 1.3792 0.06492 0.05968 -0.0210 0.0067 1.0000
15.750 1.3811 0.06759 0.06242 -0.0210 0.0066 1.0000
16.000 1.3837 0.07023 0.06513 -0.0211 0.0065 1.0000
16.250 1.3840 0.07316 0.06813 -0.0212 0.0062 1.0000
16.500 1.3840 0.07618 0.07122 -0.0215 0.0061 1.0000
16.750 1.3821 0.07951 0.07464 -0.0218 0.0060 1.0000
17.000 1.3782 0.08317 0.07838 -0.0223 0.0059 1.0000
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