RAF 25 AIRFOIL (raf25-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: RAF 25 AIRFOIL (raf25-il) Reynolds number: 50,000 Max Cl/Cd: 30.55 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-raf25-il-50000-n5.txt Download as CSV file: xf-raf25-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: RAF 25 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.5729 0.09123 0.08438 -0.0124 1.0000 0.0443
-8.250 -0.5757 0.08659 0.07982 -0.0152 1.0000 0.0432
-8.000 -0.5789 0.08160 0.07491 -0.0189 1.0000 0.0421
-7.750 -0.5809 0.07571 0.06903 -0.0235 1.0000 0.0406
-7.250 -0.5830 0.06374 0.05660 -0.0309 1.0000 0.0378
-7.000 -0.5770 0.05920 0.05188 -0.0316 1.0000 0.0375
-6.750 -0.5692 0.05469 0.04709 -0.0322 1.0000 0.0374
-6.500 -0.5594 0.05023 0.04218 -0.0324 1.0000 0.0378
-6.250 -0.5475 0.04664 0.03852 -0.0321 1.0000 0.0399
-6.000 -0.5327 0.04346 0.03506 -0.0317 1.0000 0.0425
-5.750 -0.5163 0.03978 0.03079 -0.0311 1.0000 0.0439
-5.500 -0.4977 0.03627 0.02672 -0.0302 1.0000 0.0451
-5.250 -0.4769 0.03315 0.02294 -0.0290 1.0000 0.0475
-5.000 -0.4563 0.03058 0.02004 -0.0281 1.0000 0.0529
-4.750 -0.4334 0.02829 0.01739 -0.0270 1.0000 0.0578
-4.500 -0.4100 0.02622 0.01498 -0.0258 1.0000 0.0656
-4.250 -0.3864 0.02462 0.01308 -0.0246 1.0000 0.0761
-4.000 -0.3636 0.02297 0.01134 -0.0234 1.0000 0.0857
-3.750 -0.3403 0.02181 0.01002 -0.0224 1.0000 0.1036
-3.500 -0.3161 0.02059 0.00869 -0.0216 1.0000 0.1184
-3.250 -0.2936 0.01933 0.00752 -0.0207 1.0000 0.1498
-3.000 -0.2730 0.01765 0.00663 -0.0200 1.0000 0.2869
-2.750 -0.2585 0.01622 0.00632 -0.0173 1.0000 0.5345
-2.500 -0.2336 0.01511 0.00630 -0.0137 1.0000 0.8264
-2.250 -0.1449 0.01487 0.00549 -0.0251 1.0000 1.0000
-2.000 -0.1279 0.01476 0.00504 -0.0236 1.0000 1.0000
-1.750 -0.1099 0.01469 0.00471 -0.0221 1.0000 1.0000
-1.500 -0.0912 0.01466 0.00445 -0.0208 1.0000 1.0000
-1.250 -0.0720 0.01465 0.00425 -0.0195 1.0000 1.0000
-1.000 -0.0526 0.01467 0.00407 -0.0182 1.0000 1.0000
-0.750 -0.0330 0.01472 0.00397 -0.0170 1.0000 1.0000
-0.500 -0.0133 0.01479 0.00392 -0.0158 1.0000 1.0000
-0.250 0.0064 0.01489 0.00392 -0.0147 1.0000 1.0000
0.000 0.0261 0.01501 0.00395 -0.0135 1.0000 1.0000
0.250 0.0456 0.01517 0.00404 -0.0124 1.0000 1.0000
0.500 0.0651 0.01535 0.00418 -0.0114 1.0000 1.0000
0.750 0.0844 0.01556 0.00437 -0.0104 1.0000 1.0000
1.000 0.1036 0.01580 0.00462 -0.0094 1.0000 1.0000
1.250 0.1226 0.01608 0.00492 -0.0085 1.0000 1.0000
1.500 0.1522 0.01643 0.00533 -0.0098 0.9940 1.0000
1.750 0.1964 0.01682 0.00588 -0.0138 0.9793 1.0000
2.000 0.2407 0.01715 0.00638 -0.0177 0.9631 1.0000
2.250 0.2852 0.01741 0.00686 -0.0214 0.9448 1.0000
2.500 0.3326 0.01760 0.00738 -0.0254 0.9272 1.0000
2.750 0.3774 0.01776 0.00787 -0.0287 0.9083 1.0000
3.000 0.4204 0.01788 0.00841 -0.0313 0.8880 1.0000
3.250 0.4707 0.01739 0.00833 -0.0330 0.8340 1.0000
3.500 0.5039 0.01694 0.00796 -0.0305 0.7357 1.0000
3.750 0.5240 0.01715 0.00769 -0.0260 0.5667 1.0000
4.000 0.5363 0.01850 0.00800 -0.0220 0.3392 1.0000
4.250 0.5479 0.02128 0.00933 -0.0201 0.1369 1.0000
4.500 0.5688 0.02296 0.01092 -0.0189 0.1020 1.0000
4.750 0.5902 0.02449 0.01244 -0.0179 0.0787 1.0000
5.000 0.6123 0.02627 0.01429 -0.0166 0.0669 1.0000
5.250 0.6357 0.02825 0.01639 -0.0155 0.0555 1.0000
5.500 0.6631 0.03047 0.01897 -0.0144 0.0498 1.0000
5.750 0.6881 0.03284 0.02158 -0.0135 0.0450 1.0000
6.000 0.7106 0.03566 0.02472 -0.0125 0.0406 1.0000
6.250 0.7328 0.03864 0.02828 -0.0112 0.0388 1.0000
6.500 0.7520 0.04197 0.03216 -0.0097 0.0378 1.0000
6.750 0.7681 0.04549 0.03620 -0.0083 0.0370 1.0000
7.000 0.7814 0.04897 0.04013 -0.0070 0.0354 1.0000
7.250 0.7939 0.05215 0.04354 -0.0062 0.0333 1.0000
7.500 0.8017 0.05625 0.04793 -0.0051 0.0323 1.0000
7.750 0.8064 0.06038 0.05251 -0.0040 0.0321 1.0000
8.000 0.8087 0.06468 0.05712 -0.0032 0.0322 1.0000
8.250 0.8095 0.06896 0.06163 -0.0027 0.0324 1.0000
8.500 0.8086 0.07331 0.06615 -0.0023 0.0326 1.0000
9.000 0.7729 0.08307 0.07643 -0.0046 0.0346 1.0000
9.250 0.7578 0.08904 0.08242 -0.0085 0.0354 1.0000
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