RAF 25 AIRFOIL (raf25-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: RAF 25 AIRFOIL (raf25-il) Reynolds number: 100,000 Max Cl/Cd: 40.21 at α=3° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-raf25-il-100000-n5.txt Download as CSV file: xf-raf25-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.5722 0.08628 0.08139 -0.0121 1.0000 0.0219
-8.250 -0.5764 0.08149 0.07669 -0.0149 1.0000 0.0216
-8.000 -0.5819 0.07660 0.07187 -0.0185 1.0000 0.0210
-7.750 -0.5839 0.07061 0.06588 -0.0235 1.0000 0.0205
-7.500 -0.5844 0.06436 0.05957 -0.0276 1.0000 0.0201
-7.250 -0.5835 0.05805 0.05310 -0.0305 1.0000 0.0195
-7.000 -0.5802 0.05190 0.04668 -0.0322 1.0000 0.0190
-6.750 -0.5739 0.04627 0.04068 -0.0327 1.0000 0.0188
-6.500 -0.5642 0.04151 0.03551 -0.0325 1.0000 0.0188
-6.250 -0.5513 0.03758 0.03116 -0.0318 1.0000 0.0192
-6.000 -0.5353 0.03500 0.02827 -0.0310 1.0000 0.0209
-5.750 -0.5182 0.03189 0.02468 -0.0298 1.0000 0.0227
-5.500 -0.4996 0.02868 0.02084 -0.0284 1.0000 0.0237
-5.250 -0.4791 0.02577 0.01737 -0.0270 1.0000 0.0249
-5.000 -0.4565 0.02360 0.01466 -0.0255 1.0000 0.0272
-4.750 -0.4353 0.02181 0.01274 -0.0246 1.0000 0.0311
-4.500 -0.4127 0.02019 0.01090 -0.0233 1.0000 0.0350
-4.250 -0.3908 0.01888 0.00948 -0.0222 1.0000 0.0416
-4.000 -0.3685 0.01782 0.00826 -0.0210 1.0000 0.0488
-3.750 -0.3471 0.01689 0.00729 -0.0199 1.0000 0.0599
-3.500 -0.3255 0.01604 0.00636 -0.0187 1.0000 0.0681
-3.250 -0.3035 0.01538 0.00564 -0.0177 1.0000 0.0799
-3.000 -0.2814 0.01469 0.00493 -0.0166 1.0000 0.0942
-2.750 -0.2597 0.01390 0.00434 -0.0156 1.0000 0.1478
-2.500 -0.2389 0.01295 0.00397 -0.0147 1.0000 0.2843
-2.250 -0.2176 0.01225 0.00377 -0.0138 1.0000 0.4190
-2.000 -0.1986 0.01152 0.00374 -0.0119 1.0000 0.5987
-1.750 -0.1412 0.01065 0.00379 -0.0160 1.0000 0.9298
-1.500 -0.0934 0.01063 0.00354 -0.0204 1.0000 1.0000
-1.250 -0.0752 0.01065 0.00342 -0.0188 1.0000 1.0000
-1.000 -0.0567 0.01071 0.00332 -0.0173 1.0000 1.0000
-0.750 -0.0381 0.01078 0.00328 -0.0159 1.0000 1.0000
-0.500 -0.0194 0.01089 0.00330 -0.0145 1.0000 1.0000
-0.250 0.0152 0.01101 0.00333 -0.0164 0.9936 1.0000
0.000 0.0547 0.01112 0.00337 -0.0192 0.9844 1.0000
0.250 0.0935 0.01121 0.00343 -0.0218 0.9747 1.0000
0.500 0.1325 0.01129 0.00351 -0.0244 0.9648 1.0000
0.750 0.1715 0.01133 0.00357 -0.0269 0.9542 1.0000
1.000 0.2110 0.01134 0.00363 -0.0294 0.9419 1.0000
1.250 0.2515 0.01132 0.00370 -0.0319 0.9278 1.0000
1.500 0.2911 0.01131 0.00377 -0.0341 0.9127 1.0000
1.750 0.3276 0.01132 0.00389 -0.0357 0.8971 1.0000
2.000 0.3631 0.01130 0.00400 -0.0369 0.8739 1.0000
2.250 0.3970 0.01125 0.00400 -0.0372 0.8353 1.0000
2.500 0.4252 0.01127 0.00399 -0.0361 0.7804 1.0000
2.750 0.4498 0.01142 0.00404 -0.0344 0.7113 1.0000
3.000 0.4721 0.01174 0.00410 -0.0324 0.6164 1.0000
3.250 0.4916 0.01238 0.00426 -0.0302 0.4941 1.0000
3.500 0.5084 0.01344 0.00463 -0.0280 0.3301 1.0000
3.750 0.5226 0.01532 0.00540 -0.0262 0.1197 1.0000
4.000 0.5438 0.01631 0.00623 -0.0250 0.0815 1.0000
4.250 0.5651 0.01728 0.00717 -0.0238 0.0604 1.0000
4.500 0.5852 0.01845 0.00840 -0.0224 0.0459 1.0000
4.750 0.6050 0.01985 0.00991 -0.0208 0.0381 1.0000
5.000 0.6261 0.02113 0.01123 -0.0197 0.0316 1.0000
5.250 0.6492 0.02266 0.01296 -0.0184 0.0277 1.0000
5.500 0.6724 0.02429 0.01471 -0.0174 0.0247 1.0000
5.750 0.6950 0.02626 0.01686 -0.0165 0.0221 1.0000
6.000 0.7186 0.02871 0.01975 -0.0152 0.0207 1.0000
6.250 0.7400 0.03167 0.02320 -0.0136 0.0200 1.0000
6.500 0.7587 0.03493 0.02699 -0.0119 0.0196 1.0000
6.750 0.7746 0.03843 0.03103 -0.0101 0.0192 1.0000
7.000 0.7879 0.04199 0.03517 -0.0083 0.0179 1.0000
7.250 0.7986 0.04568 0.03929 -0.0068 0.0171 1.0000
7.500 0.8061 0.04972 0.04373 -0.0053 0.0167 1.0000
7.750 0.8097 0.05425 0.04862 -0.0039 0.0168 1.0000
8.000 0.8094 0.05898 0.05367 -0.0030 0.0170 1.0000
8.250 0.8059 0.06367 0.05859 -0.0024 0.0172 1.0000
8.500 0.7984 0.06839 0.06350 -0.0024 0.0174 1.0000
8.750 0.7857 0.07304 0.06825 -0.0026 0.0176 1.0000
9.000 0.7716 0.07794 0.07322 -0.0045 0.0179 1.0000
9.250 0.7588 0.08454 0.07984 -0.0096 0.0182 1.0000
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Polar data table (+)
Polar graphs
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