RAF 15 AIRFOIL (raf15-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: RAF 15 AIRFOIL (raf15-il) Reynolds number: 1,000,000 Max Cl/Cd: 89.58 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-raf15-il-1000000-n5.txt Download as CSV file: xf-raf15-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.500 -0.4285 0.14607 0.14442 0.0008 1.0000 0.0049
-13.250 -0.4266 0.14334 0.14169 0.0002 1.0000 0.0048
-12.750 -0.5563 0.15026 0.14849 0.0121 1.0000 0.0045
-12.500 -0.5524 0.14660 0.14483 0.0110 1.0000 0.0046
-12.250 -0.5494 0.14265 0.14089 0.0100 1.0000 0.0044
-12.000 -0.5465 0.13877 0.13702 0.0089 1.0000 0.0042
-11.750 -0.5511 0.13180 0.13005 0.0073 1.0000 0.0035
-9.250 -0.8507 0.02514 0.02212 -0.0235 1.0000 0.0042
-9.000 -0.8374 0.02303 0.01978 -0.0217 1.0000 0.0043
-8.750 -0.8204 0.02097 0.01744 -0.0204 0.9996 0.0044
-8.500 -0.7970 0.01945 0.01568 -0.0202 0.9987 0.0045
-8.250 -0.7729 0.01805 0.01404 -0.0199 0.9975 0.0047
-8.000 -0.7476 0.01698 0.01279 -0.0198 0.9965 0.0048
-7.750 -0.7208 0.01628 0.01195 -0.0198 0.9957 0.0050
-7.500 -0.6945 0.01536 0.01085 -0.0196 0.9949 0.0051
-7.250 -0.6687 0.01484 0.01023 -0.0193 0.9938 0.0053
-7.000 -0.6444 0.01377 0.00897 -0.0187 0.9923 0.0056
-6.750 -0.6174 0.01319 0.00827 -0.0186 0.9910 0.0058
-6.500 -0.5898 0.01263 0.00763 -0.0185 0.9899 0.0061
-6.250 -0.5607 0.01227 0.00721 -0.0188 0.9889 0.0064
-6.000 -0.5312 0.01184 0.00670 -0.0191 0.9880 0.0067
-5.750 -0.4994 0.01143 0.00621 -0.0199 0.9871 0.0072
-5.500 -0.4694 0.01100 0.00570 -0.0203 0.9838 0.0075
-5.250 -0.4332 0.01049 0.00513 -0.0220 0.9803 0.0082
-5.000 -0.3936 0.01002 0.00462 -0.0245 0.9780 0.0090
-4.750 -0.3689 0.00967 0.00424 -0.0236 0.9716 0.0098
-4.250 -0.3166 0.00903 0.00353 -0.0225 0.9589 0.0118
-3.750 -0.2678 0.00849 0.00299 -0.0205 0.9347 0.0146
-3.500 -0.2321 0.00818 0.00267 -0.0220 0.9273 0.0169
-3.250 -0.1896 0.00786 0.00237 -0.0252 0.9199 0.0201
-3.000 -0.1292 0.00759 0.00206 -0.0325 0.9096 0.0226
-2.750 -0.0590 0.00729 0.00170 -0.0422 0.8948 0.0265
-2.500 -0.0078 0.00720 0.00150 -0.0476 0.8645 0.0295
-2.250 0.0208 0.00724 0.00137 -0.0475 0.8206 0.0313
-2.000 0.0404 0.00739 0.00127 -0.0454 0.7583 0.0324
-1.750 0.0593 0.00754 0.00119 -0.0432 0.7000 0.0350
-1.500 0.0794 0.00764 0.00111 -0.0413 0.6477 0.0417
-1.250 0.0998 0.00763 0.00104 -0.0396 0.5992 0.0731
-1.000 0.1211 0.00765 0.00101 -0.0381 0.5534 0.1036
-0.750 0.1438 0.00772 0.00098 -0.0369 0.5151 0.1202
-0.500 0.1669 0.00778 0.00097 -0.0357 0.4788 0.1393
-0.250 0.1903 0.00786 0.00098 -0.0347 0.4430 0.1591
0.000 0.2139 0.00798 0.00099 -0.0337 0.4060 0.1734
0.250 0.2383 0.00807 0.00100 -0.0328 0.3797 0.1837
0.500 0.2628 0.00814 0.00103 -0.0320 0.3585 0.1927
0.750 0.2875 0.00821 0.00105 -0.0312 0.3407 0.2037
1.000 0.3123 0.00827 0.00108 -0.0304 0.3261 0.2148
1.250 0.3372 0.00832 0.00112 -0.0297 0.3143 0.2237
1.500 0.3624 0.00837 0.00115 -0.0290 0.3052 0.2298
1.750 0.3874 0.00843 0.00119 -0.0283 0.2921 0.2383
2.000 0.4122 0.00850 0.00124 -0.0275 0.2789 0.2475
2.250 0.4368 0.00855 0.00130 -0.0268 0.2653 0.2669
2.500 0.4612 0.00856 0.00137 -0.0260 0.2578 0.2961
2.750 0.4831 0.00842 0.00145 -0.0247 0.2448 0.4032
3.250 0.6243 0.00784 0.00210 -0.0451 0.1857 0.9782
3.500 0.6544 0.00815 0.00229 -0.0456 0.1604 0.9835
3.750 0.6862 0.00842 0.00248 -0.0465 0.1447 0.9878
4.000 0.7222 0.00866 0.00265 -0.0484 0.1290 0.9903
4.250 0.7536 0.00891 0.00283 -0.0493 0.1137 0.9924
4.500 0.7849 0.00920 0.00304 -0.0502 0.0958 0.9947
4.750 0.8176 0.00951 0.00324 -0.0514 0.0755 0.9961
5.000 0.8538 0.00982 0.00346 -0.0535 0.0576 0.9981
5.250 0.8902 0.01011 0.00369 -0.0556 0.0466 0.9999
5.500 0.9138 0.01034 0.00390 -0.0547 0.0429 1.0000
5.750 0.9365 0.01057 0.00414 -0.0536 0.0397 1.0000
6.000 0.9594 0.01079 0.00438 -0.0525 0.0382 1.0000
6.250 0.9823 0.01100 0.00463 -0.0514 0.0375 1.0000
6.500 1.0051 0.01122 0.00488 -0.0503 0.0367 1.0000
6.750 1.0275 0.01147 0.00514 -0.0492 0.0347 1.0000
7.000 1.0497 0.01174 0.00544 -0.0481 0.0331 1.0000
7.250 1.0714 0.01206 0.00576 -0.0468 0.0310 1.0000
7.500 1.0929 0.01239 0.00613 -0.0455 0.0293 1.0000
7.750 1.1156 0.01258 0.00636 -0.0445 0.0287 1.0000
8.000 1.1380 0.01281 0.00663 -0.0435 0.0276 1.0000
8.250 1.1599 0.01308 0.00694 -0.0423 0.0262 1.0000
8.500 1.1810 0.01342 0.00727 -0.0411 0.0224 1.0000
8.750 1.2020 0.01376 0.00765 -0.0398 0.0203 1.0000
9.000 1.2217 0.01421 0.00805 -0.0383 0.0147 1.0000
9.250 1.2403 0.01477 0.00859 -0.0366 0.0107 1.0000
9.500 1.2596 0.01524 0.00911 -0.0351 0.0092 1.0000
9.750 1.2778 0.01581 0.00971 -0.0333 0.0078 1.0000
10.000 1.2967 0.01630 0.01027 -0.0317 0.0070 1.0000
10.250 1.3146 0.01685 0.01090 -0.0300 0.0062 1.0000
10.500 1.3320 0.01743 0.01153 -0.0282 0.0057 1.0000
10.750 1.3482 0.01810 0.01227 -0.0262 0.0052 1.0000
11.000 1.3655 0.01864 0.01290 -0.0244 0.0049 1.0000
11.250 1.3816 0.01926 0.01359 -0.0225 0.0046 1.0000
11.500 1.3969 0.01992 0.01434 -0.0204 0.0043 1.0000
11.750 1.4121 0.02055 0.01504 -0.0184 0.0041 1.0000
12.000 1.4251 0.02133 0.01589 -0.0160 0.0038 1.0000
12.250 1.4363 0.02222 0.01689 -0.0134 0.0037 1.0000
12.500 1.4465 0.02315 0.01794 -0.0107 0.0035 1.0000
12.750 1.4580 0.02392 0.01880 -0.0082 0.0033 1.0000
13.000 1.4656 0.02471 0.01968 -0.0050 0.0032 1.0000
13.250 1.4698 0.02549 0.02055 -0.0012 0.0032 1.0000
13.500 1.4730 0.02638 0.02155 0.0025 0.0030 1.0000
13.750 1.4751 0.02742 0.02269 0.0060 0.0030 1.0000
14.000 1.4778 0.02851 0.02388 0.0092 0.0028 1.0000
14.250 1.4794 0.02974 0.02521 0.0122 0.0028 1.0000
14.500 1.4779 0.03128 0.02687 0.0151 0.0027 1.0000
14.750 1.4764 0.03298 0.02867 0.0175 0.0026 1.0000
15.000 1.4715 0.03516 0.03099 0.0193 0.0026 1.0000
15.250 1.4644 0.03785 0.03380 0.0205 0.0025 1.0000
15.500 1.4533 0.04150 0.03761 0.0205 0.0025 1.0000
15.750 1.4392 0.04633 0.04260 0.0187 0.0026 1.0000
16.000 1.4222 0.05256 0.04900 0.0152 0.0024 1.0000
16.250 1.3991 0.06058 0.05722 0.0102 0.0025 1.0000
16.500 1.3730 0.06918 0.06599 0.0054 0.0025 1.0000
16.750 1.3339 0.07988 0.07685 -0.0002 0.0025 1.0000
17.000 1.2956 0.09024 0.08737 -0.0053 0.0027 1.0000
17.250 1.2539 0.10135 0.09862 -0.0107 0.0027 1.0000
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