RAF 25 AIRFOIL (raf25-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: RAF 25 AIRFOIL (raf25-il) Reynolds number: 1,000,000 Max Cl/Cd: 68.14 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-raf25-il-1000000-n5.txt Download as CSV file: xf-raf25-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.6163 0.08311 0.08154 -0.0097 1.0000 0.0026
-8.750 -0.7915 0.02629 0.02345 -0.0333 1.0000 0.0020
-8.500 -0.7810 0.02296 0.01971 -0.0317 1.0000 0.0020
-8.250 -0.7722 0.01917 0.01536 -0.0296 1.0000 0.0021
-8.000 -0.7541 0.01761 0.01357 -0.0283 1.0000 0.0023
-7.750 -0.7333 0.01669 0.01252 -0.0274 1.0000 0.0024
-7.500 -0.7125 0.01574 0.01142 -0.0263 1.0000 0.0025
-7.250 -0.6906 0.01504 0.01061 -0.0254 1.0000 0.0027
-7.000 -0.6693 0.01418 0.00960 -0.0243 1.0000 0.0029
-6.750 -0.6480 0.01326 0.00849 -0.0232 1.0000 0.0030
-6.500 -0.6263 0.01245 0.00753 -0.0220 1.0000 0.0032
-6.250 -0.6041 0.01180 0.00676 -0.0210 1.0000 0.0034
-6.000 -0.5749 0.01119 0.00603 -0.0215 0.9990 0.0036
-5.750 -0.5448 0.01040 0.00512 -0.0222 0.9973 0.0041
-5.500 -0.5136 0.00994 0.00461 -0.0232 0.9956 0.0045
-5.250 -0.4832 0.00952 0.00413 -0.0239 0.9936 0.0050
-5.000 -0.4524 0.00922 0.00377 -0.0247 0.9910 0.0057
-4.750 -0.4212 0.00874 0.00322 -0.0255 0.9883 0.0070
-4.500 -0.3898 0.00842 0.00286 -0.0264 0.9850 0.0084
-4.250 -0.3588 0.00813 0.00253 -0.0271 0.9798 0.0101
-4.000 -0.3279 0.00784 0.00228 -0.0278 0.9738 0.0167
-3.750 -0.2955 0.00764 0.00210 -0.0289 0.9675 0.0253
-3.500 -0.2622 0.00753 0.00197 -0.0302 0.9607 0.0274
-3.250 -0.2263 0.00738 0.00181 -0.0321 0.9530 0.0284
-3.000 -0.1909 0.00716 0.00153 -0.0338 0.9412 0.0319
-2.750 -0.1564 0.00699 0.00134 -0.0353 0.9266 0.0346
-2.500 -0.1258 0.00689 0.00117 -0.0359 0.9090 0.0362
-2.250 -0.0979 0.00682 0.00103 -0.0358 0.8924 0.0406
-2.000 -0.0713 0.00667 0.00091 -0.0355 0.8769 0.0621
-1.750 -0.0456 0.00648 0.00081 -0.0351 0.8608 0.1037
-1.500 -0.0201 0.00634 0.00072 -0.0346 0.8415 0.1464
-1.250 0.0050 0.00622 0.00064 -0.0340 0.8182 0.1849
-1.000 0.0297 0.00598 0.00057 -0.0335 0.7980 0.2618
-0.750 0.0550 0.00578 0.00053 -0.0330 0.7819 0.3272
-0.500 0.0799 0.00562 0.00049 -0.0325 0.7605 0.3883
-0.250 0.1036 0.00554 0.00047 -0.0316 0.7190 0.4574
0.000 0.1265 0.00560 0.00046 -0.0306 0.6565 0.5118
0.250 0.1506 0.00560 0.00048 -0.0298 0.6098 0.5648
0.500 0.1745 0.00564 0.00051 -0.0291 0.5609 0.6172
0.750 0.1978 0.00563 0.00056 -0.0282 0.5145 0.6880
1.000 0.2174 0.00544 0.00063 -0.0264 0.4656 0.8101
1.250 0.2386 0.00553 0.00074 -0.0249 0.3836 0.9012
1.500 0.2891 0.00597 0.00092 -0.0303 0.2856 0.9646
1.750 0.3253 0.00661 0.00110 -0.0327 0.1598 0.9814
2.000 0.3577 0.00696 0.00126 -0.0338 0.1086 0.9920
2.250 0.3915 0.00732 0.00143 -0.0354 0.0543 0.9984
2.500 0.4217 0.00748 0.00157 -0.0360 0.0490 1.0000
2.750 0.4463 0.00766 0.00174 -0.0353 0.0422 1.0000
3.000 0.4713 0.00778 0.00187 -0.0347 0.0399 1.0000
3.250 0.4960 0.00796 0.00203 -0.0341 0.0350 1.0000
3.500 0.5209 0.00812 0.00219 -0.0334 0.0317 1.0000
3.750 0.5454 0.00833 0.00236 -0.0328 0.0216 1.0000
4.000 0.5698 0.00858 0.00257 -0.0321 0.0122 1.0000
4.250 0.5941 0.00885 0.00284 -0.0313 0.0096 1.0000
4.500 0.6180 0.00919 0.00321 -0.0305 0.0071 1.0000
4.750 0.6423 0.00946 0.00353 -0.0298 0.0062 1.0000
5.000 0.6664 0.00978 0.00388 -0.0290 0.0055 1.0000
5.250 0.6898 0.01019 0.00433 -0.0282 0.0048 1.0000
5.500 0.7126 0.01074 0.00495 -0.0271 0.0043 1.0000
5.750 0.7360 0.01118 0.00547 -0.0263 0.0040 1.0000
6.000 0.7595 0.01161 0.00598 -0.0254 0.0036 1.0000
6.250 0.7830 0.01204 0.00646 -0.0247 0.0033 1.0000
6.500 0.8064 0.01250 0.00696 -0.0239 0.0030 1.0000
6.750 0.8291 0.01309 0.00761 -0.0230 0.0029 1.0000
7.000 0.8488 0.01428 0.00896 -0.0216 0.0026 1.0000
7.250 0.8713 0.01497 0.00976 -0.0207 0.0025 1.0000
7.500 0.8930 0.01585 0.01078 -0.0196 0.0024 1.0000
7.750 0.9145 0.01678 0.01187 -0.0186 0.0023 1.0000
8.000 0.9351 0.01795 0.01323 -0.0174 0.0021 1.0000
8.250 0.9539 0.01949 0.01501 -0.0161 0.0020 1.0000
8.500 0.9715 0.02128 0.01707 -0.0146 0.0019 1.0000
8.750 0.9872 0.02342 0.01955 -0.0129 0.0018 1.0000
9.000 0.9963 0.02696 0.02354 -0.0105 0.0018 1.0000
10.500 0.7808 0.09566 0.09411 -0.0204 0.0020 1.0000
10.750 0.7721 0.10246 0.10090 -0.0240 0.0021 1.0000
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Polar data table (+)
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