RAF 15 AIRFOIL (raf15-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: RAF 15 AIRFOIL (raf15-il) Reynolds number: 200,000 Max Cl/Cd: 59.91 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-raf15-il-200000-n5.txt Download as CSV file: xf-raf15-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: RAF 15 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.5009 0.09786 0.09417 -0.0091 1.0000 0.0153
-8.750 -0.5009 0.09439 0.09074 -0.0096 1.0000 0.0151
-8.500 -0.5017 0.09104 0.08743 -0.0104 1.0000 0.0149
-8.250 -0.5052 0.08754 0.08398 -0.0112 1.0000 0.0148
-8.000 -0.5107 0.08443 0.08091 -0.0116 1.0000 0.0145
-7.750 -0.5161 0.08093 0.07745 -0.0122 1.0000 0.0144
-7.500 -0.5175 0.07672 0.07326 -0.0138 1.0000 0.0144
-7.250 -0.5176 0.07237 0.06891 -0.0153 1.0000 0.0143
-7.000 -0.5159 0.06776 0.06428 -0.0167 1.0000 0.0142
-6.750 -0.5126 0.06286 0.05933 -0.0181 1.0000 0.0143
-6.500 -0.5078 0.05768 0.05407 -0.0190 1.0000 0.0143
-6.250 -0.5028 0.05078 0.04700 -0.0200 1.0000 0.0150
-6.000 -0.4999 0.04210 0.03801 -0.0199 1.0000 0.0152
-5.750 -0.4995 0.03274 0.02795 -0.0182 1.0000 0.0153
-5.500 -0.4915 0.02822 0.02278 -0.0155 1.0000 0.0154
-5.250 -0.4793 0.02505 0.01902 -0.0128 1.0000 0.0158
-5.000 -0.4651 0.02258 0.01616 -0.0104 1.0000 0.0163
-4.750 -0.4472 0.02118 0.01454 -0.0086 1.0000 0.0169
-4.500 -0.4274 0.02049 0.01371 -0.0071 1.0000 0.0184
-4.250 -0.4074 0.01947 0.01244 -0.0054 1.0000 0.0200
-4.000 -0.3867 0.01844 0.01113 -0.0037 1.0000 0.0214
-3.750 -0.3651 0.01754 0.00997 -0.0020 1.0000 0.0227
-3.500 -0.3447 0.01638 0.00870 -0.0005 1.0000 0.0248
-3.250 -0.3140 0.01582 0.00808 -0.0011 0.9977 0.0278
-3.000 -0.2743 0.01511 0.00721 -0.0034 0.9928 0.0311
-2.750 -0.2344 0.01436 0.00640 -0.0059 0.9873 0.0361
-2.500 -0.1962 0.01379 0.00576 -0.0080 0.9801 0.0406
-2.250 -0.1608 0.01328 0.00518 -0.0094 0.9723 0.0467
-2.000 -0.1278 0.01283 0.00472 -0.0104 0.9658 0.0533
-1.500 -0.0701 0.01192 0.00409 -0.0105 0.9482 0.1151
-1.250 -0.0404 0.01165 0.00393 -0.0107 0.9382 0.1496
-1.000 -0.0078 0.01143 0.00376 -0.0115 0.9284 0.1753
-0.750 0.0256 0.01124 0.00358 -0.0124 0.9173 0.1997
-0.500 0.0613 0.01099 0.00337 -0.0138 0.9055 0.2178
-0.250 0.1009 0.01072 0.00314 -0.0161 0.8923 0.2386
0.000 0.1469 0.01044 0.00288 -0.0198 0.8745 0.2569
0.250 0.2015 0.01019 0.00263 -0.0254 0.8463 0.2739
0.500 0.2607 0.00997 0.00239 -0.0321 0.7912 0.2994
0.750 0.3024 0.00997 0.00220 -0.0348 0.7081 0.3445
1.250 0.4909 0.01007 0.00279 -0.0643 0.4981 1.0000
1.500 0.5117 0.01032 0.00285 -0.0627 0.4616 1.0000
1.750 0.5328 0.01056 0.00292 -0.0612 0.4296 1.0000
2.000 0.5543 0.01079 0.00300 -0.0598 0.4029 1.0000
2.250 0.5762 0.01101 0.00310 -0.0584 0.3812 1.0000
2.500 0.5983 0.01123 0.00323 -0.0571 0.3632 1.0000
2.750 0.6207 0.01144 0.00337 -0.0559 0.3480 1.0000
3.250 0.6658 0.01187 0.00371 -0.0536 0.3198 1.0000
3.500 0.6885 0.01209 0.00390 -0.0524 0.3057 1.0000
3.750 0.7107 0.01234 0.00409 -0.0512 0.2888 1.0000
4.000 0.7332 0.01256 0.00427 -0.0500 0.2667 1.0000
4.250 0.7551 0.01283 0.00446 -0.0488 0.2416 1.0000
4.500 0.7773 0.01310 0.00468 -0.0476 0.2200 1.0000
5.000 0.8213 0.01371 0.00520 -0.0452 0.1836 1.0000
5.250 0.8430 0.01407 0.00554 -0.0440 0.1648 1.0000
5.500 0.8643 0.01446 0.00589 -0.0427 0.1473 1.0000
5.750 0.8854 0.01490 0.00629 -0.0414 0.1302 1.0000
6.000 0.9064 0.01534 0.00671 -0.0400 0.1123 1.0000
6.250 0.9267 0.01588 0.00722 -0.0386 0.0933 1.0000
6.500 0.9467 0.01645 0.00774 -0.0371 0.0788 1.0000
6.750 0.9666 0.01701 0.00832 -0.0356 0.0698 1.0000
7.000 0.9859 0.01762 0.00895 -0.0340 0.0641 1.0000
7.250 1.0050 0.01823 0.00963 -0.0324 0.0605 1.0000
7.500 1.0244 0.01881 0.01036 -0.0307 0.0579 1.0000
7.750 1.0431 0.01945 0.01110 -0.0290 0.0555 1.0000
8.000 1.0611 0.02015 0.01189 -0.0272 0.0533 1.0000
8.250 1.0769 0.02105 0.01284 -0.0252 0.0504 1.0000
8.500 1.0954 0.02169 0.01360 -0.0236 0.0474 1.0000
8.750 1.1141 0.02227 0.01431 -0.0220 0.0441 1.0000
9.000 1.1312 0.02296 0.01511 -0.0203 0.0411 1.0000
9.250 1.1452 0.02396 0.01618 -0.0181 0.0381 1.0000
9.500 1.1631 0.02457 0.01698 -0.0165 0.0355 1.0000
9.750 1.1798 0.02523 0.01777 -0.0148 0.0323 1.0000
10.000 1.1918 0.02627 0.01887 -0.0125 0.0296 1.0000
10.250 1.2074 0.02704 0.01986 -0.0105 0.0266 1.0000
10.500 1.2218 0.02781 0.02077 -0.0086 0.0232 1.0000
10.750 1.2327 0.02883 0.02186 -0.0062 0.0207 1.0000
11.000 1.2423 0.02998 0.02321 -0.0036 0.0187 1.0000
11.250 1.2508 0.03110 0.02451 -0.0009 0.0168 1.0000
11.500 1.2544 0.03227 0.02575 0.0024 0.0155 1.0000
11.750 1.2525 0.03379 0.02740 0.0063 0.0149 1.0000
12.000 1.2515 0.03541 0.02921 0.0097 0.0140 1.0000
12.250 1.2507 0.03710 0.03108 0.0127 0.0131 1.0000
12.500 1.2475 0.03907 0.03323 0.0152 0.0126 1.0000
12.750 1.2428 0.04134 0.03568 0.0172 0.0120 1.0000
13.000 1.2355 0.04415 0.03865 0.0183 0.0118 1.0000
13.250 1.2254 0.04769 0.04238 0.0184 0.0116 1.0000
13.500 1.2140 0.05203 0.04691 0.0171 0.0113 1.0000
13.750 1.2012 0.05729 0.05236 0.0144 0.0112 1.0000
14.000 1.1854 0.06372 0.05898 0.0107 0.0112 1.0000
14.250 1.1694 0.07046 0.06589 0.0067 0.0112 1.0000
14.500 1.1497 0.07798 0.07359 0.0025 0.0113 1.0000
14.750 1.1289 0.08575 0.08152 -0.0017 0.0114 1.0000
15.000 1.1056 0.09407 0.09000 -0.0060 0.0116 1.0000
15.250 1.0793 0.10322 0.09928 -0.0107 0.0116 1.0000
15.500 1.0493 0.11360 0.10981 -0.0160 0.0120 1.0000
15.750 1.0128 0.12635 0.12270 -0.0225 0.0123 1.0000
16.000 0.9450 0.14864 0.14508 -0.0333 0.0139 1.0000
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Polar data table (+)
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