RAF 15 AIRFOIL (raf15-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: RAF 15 AIRFOIL (raf15-il) Reynolds number: 50,000 Max Cl/Cd: 33.93 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-raf15-il-50000-n5.txt Download as CSV file: xf-raf15-il-50000-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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.750 -0.4857 0.09277 0.08581 -0.0127 1.0000 0.0641
-7.500 -0.4945 0.08768 0.08076 -0.0180 1.0000 0.0562
-7.250 -0.4888 0.08409 0.07720 -0.0170 1.0000 0.0548
-7.000 -0.4853 0.08031 0.07344 -0.0174 1.0000 0.0535
-6.750 -0.4812 0.07647 0.06961 -0.0182 1.0000 0.0523
-6.500 -0.4764 0.07240 0.06553 -0.0191 1.0000 0.0514
-6.250 -0.4701 0.06834 0.06141 -0.0199 1.0000 0.0512
-6.000 -0.4623 0.06424 0.05720 -0.0205 1.0000 0.0515
-5.750 -0.4532 0.06003 0.05287 -0.0210 1.0000 0.0523
-5.500 -0.4427 0.05583 0.04851 -0.0211 1.0000 0.0526
-5.250 -0.4312 0.05144 0.04389 -0.0208 1.0000 0.0527
-5.000 -0.4189 0.04701 0.03916 -0.0202 1.0000 0.0525
-4.750 -0.4056 0.04274 0.03453 -0.0191 1.0000 0.0528
-4.500 -0.3912 0.03870 0.02999 -0.0177 1.0000 0.0539
-4.250 -0.3749 0.03474 0.02525 -0.0159 1.0000 0.0566
-4.000 -0.3576 0.03253 0.02285 -0.0144 1.0000 0.0594
-3.750 -0.3379 0.03022 0.02017 -0.0127 1.0000 0.0619
-3.500 -0.3166 0.02815 0.01764 -0.0112 1.0000 0.0667
-3.250 -0.2940 0.02646 0.01559 -0.0100 1.0000 0.0727
-3.000 -0.2696 0.02498 0.01385 -0.0089 1.0000 0.0783
-2.750 -0.2441 0.02380 0.01246 -0.0082 1.0000 0.0877
-2.500 -0.2141 0.02273 0.01116 -0.0081 1.0000 0.0999
-2.250 -0.1815 0.02177 0.01008 -0.0086 1.0000 0.1167
-2.000 -0.1553 0.02126 0.00965 -0.0081 1.0000 0.1485
-1.750 -0.1314 0.02098 0.00936 -0.0071 1.0000 0.1910
-1.500 -0.1098 0.02086 0.00920 -0.0059 1.0000 0.2331
-1.250 -0.0876 0.02063 0.00899 -0.0050 1.0000 0.2747
-1.000 -0.0623 0.02023 0.00854 -0.0045 1.0000 0.3010
-0.750 -0.0377 0.01982 0.00816 -0.0039 1.0000 0.3233
-0.500 -0.0144 0.01946 0.00784 -0.0031 1.0000 0.3483
-0.250 0.0877 0.01717 0.00746 -0.0183 1.0000 1.0000
0.000 0.1081 0.01734 0.00739 -0.0169 1.0000 1.0000
0.250 0.1275 0.01752 0.00740 -0.0154 1.0000 1.0000
0.500 0.1463 0.01775 0.00749 -0.0139 1.0000 1.0000
0.750 0.1727 0.01799 0.00763 -0.0141 0.9960 1.0000
1.000 0.2269 0.01809 0.00766 -0.0199 0.9728 1.0000
1.250 0.2738 0.01802 0.00757 -0.0238 0.9438 1.0000
1.500 0.3196 0.01788 0.00742 -0.0271 0.9122 1.0000
1.750 0.3690 0.01767 0.00725 -0.0308 0.8766 1.0000
2.000 0.4238 0.01745 0.00705 -0.0355 0.8281 1.0000
2.250 0.4829 0.01728 0.00680 -0.0406 0.7568 1.0000
2.500 0.5338 0.01744 0.00662 -0.0441 0.6771 1.0000
2.750 0.5646 0.01791 0.00677 -0.0439 0.6142 1.0000
3.000 0.5896 0.01845 0.00704 -0.0429 0.5658 1.0000
3.250 0.6132 0.01901 0.00738 -0.0417 0.5278 1.0000
3.500 0.6365 0.01956 0.00779 -0.0406 0.4952 1.0000
3.750 0.6604 0.02011 0.00827 -0.0396 0.4668 1.0000
4.000 0.6843 0.02066 0.00878 -0.0387 0.4409 1.0000
4.250 0.7082 0.02121 0.00931 -0.0378 0.4169 1.0000
4.500 0.7321 0.02179 0.00989 -0.0369 0.3945 1.0000
4.750 0.7558 0.02237 0.01052 -0.0361 0.3724 1.0000
5.000 0.7788 0.02298 0.01115 -0.0350 0.3513 1.0000
5.250 0.8010 0.02361 0.01184 -0.0339 0.3297 1.0000
5.500 0.8220 0.02425 0.01257 -0.0325 0.3075 1.0000
5.750 0.8414 0.02486 0.01325 -0.0308 0.2834 1.0000
6.000 0.8591 0.02543 0.01381 -0.0289 0.2586 1.0000
6.250 0.8762 0.02599 0.01445 -0.0270 0.2319 1.0000
6.500 0.8940 0.02667 0.01524 -0.0252 0.2070 1.0000
6.750 0.9112 0.02750 0.01606 -0.0234 0.1844 1.0000
7.000 0.9285 0.02850 0.01709 -0.0216 0.1633 1.0000
7.250 0.9448 0.02962 0.01818 -0.0198 0.1457 1.0000
7.500 0.9622 0.03095 0.01959 -0.0181 0.1324 1.0000
7.750 0.9802 0.03245 0.02125 -0.0165 0.1223 1.0000
8.000 0.9978 0.03401 0.02290 -0.0149 0.1151 1.0000
8.250 1.0155 0.03576 0.02497 -0.0132 0.1081 1.0000
8.500 1.0314 0.03732 0.02656 -0.0116 0.1020 1.0000
8.750 1.0452 0.03916 0.02880 -0.0097 0.0951 1.0000
9.000 1.0604 0.04101 0.03077 -0.0080 0.0911 1.0000
9.250 1.0734 0.04351 0.03358 -0.0062 0.0878 1.0000
9.500 1.0803 0.04643 0.03702 -0.0037 0.0844 1.0000
9.750 1.0864 0.04873 0.03961 -0.0014 0.0799 1.0000
10.000 1.0969 0.05057 0.04145 0.0003 0.0755 1.0000
10.250 1.0893 0.05416 0.04563 0.0035 0.0732 1.0000
10.500 1.0780 0.05774 0.04962 0.0065 0.0709 1.0000
10.750 1.0641 0.06116 0.05332 0.0094 0.0690 1.0000
11.000 1.0458 0.06471 0.05708 0.0120 0.0679 1.0000
11.250 1.0214 0.06934 0.06191 0.0130 0.0678 1.0000
11.500 0.9838 0.07682 0.06959 0.0103 0.0699 1.0000
11.750 0.9487 0.08623 0.07900 0.0044 0.0723 1.0000
12.000 0.9165 0.09718 0.08993 -0.0029 0.0736 1.0000
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Polar data table (+)
Polar graphs
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