RAF 27 AIRFOIL (raf27-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: RAF 27 AIRFOIL (raf27-il) Reynolds number: 1,000,000 Max Cl/Cd: 71.45 at α=7.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-raf27-il-1000000-n5.txt Download as CSV file: xf-raf27-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: RAF 27 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
------ -------- --------- --------- -------- -------- --------
-17.250 -0.8749 0.14575 0.14389 0.0166 1.0000 0.0037
-17.000 -0.9352 0.12715 0.12515 0.0076 1.0000 0.0036
-16.750 -1.0152 0.10604 0.10383 -0.0030 1.0000 0.0034
-16.500 -1.0682 0.09158 0.08921 -0.0104 1.0000 0.0033
-16.250 -1.1259 0.07639 0.07379 -0.0188 1.0000 0.0032
-16.000 -1.1570 0.06645 0.06369 -0.0248 1.0000 0.0032
-15.750 -1.1805 0.05827 0.05533 -0.0300 1.0000 0.0031
-15.500 -1.1983 0.05157 0.04848 -0.0343 1.0000 0.0031
-15.250 -1.2122 0.04603 0.04277 -0.0375 1.0000 0.0032
-15.000 -1.2212 0.04174 0.03834 -0.0394 1.0000 0.0032
-14.750 -1.2309 0.03785 0.03430 -0.0406 1.0000 0.0032
-14.500 -1.2336 0.03512 0.03143 -0.0407 1.0000 0.0032
-14.250 -1.2344 0.03286 0.02907 -0.0402 1.0000 0.0033
-14.000 -1.2348 0.03088 0.02696 -0.0390 1.0000 0.0033
-13.750 -1.2317 0.02936 0.02534 -0.0375 1.0000 0.0034
-13.500 -1.2309 0.02781 0.02367 -0.0353 1.0000 0.0035
-13.250 -1.2256 0.02669 0.02244 -0.0330 1.0000 0.0035
-13.000 -1.2218 0.02557 0.02121 -0.0302 1.0000 0.0036
-12.750 -1.2157 0.02469 0.02025 -0.0273 1.0000 0.0037
-12.500 -1.2094 0.02373 0.01918 -0.0244 1.0000 0.0037
-12.250 -1.1986 0.02281 0.01816 -0.0222 1.0000 0.0038
-12.000 -1.1860 0.02197 0.01723 -0.0201 1.0000 0.0039
-11.750 -1.1720 0.02119 0.01635 -0.0182 1.0000 0.0040
-11.500 -1.1576 0.02039 0.01546 -0.0164 1.0000 0.0041
-11.250 -1.1416 0.01969 0.01467 -0.0146 1.0000 0.0042
-11.000 -1.1246 0.01907 0.01394 -0.0131 1.0000 0.0043
-10.750 -1.1078 0.01839 0.01318 -0.0114 1.0000 0.0044
-10.500 -1.0921 0.01759 0.01229 -0.0095 1.0000 0.0046
-10.250 -1.0754 0.01686 0.01149 -0.0078 1.0000 0.0048
-10.000 -1.0569 0.01630 0.01088 -0.0063 1.0000 0.0051
-9.750 -1.0380 0.01578 0.01031 -0.0049 1.0000 0.0053
-9.500 -1.0185 0.01531 0.00979 -0.0035 1.0000 0.0056
-9.250 -0.9987 0.01487 0.00930 -0.0021 1.0000 0.0059
-9.000 -0.9789 0.01443 0.00880 -0.0007 1.0000 0.0062
-8.750 -0.9587 0.01402 0.00832 0.0006 1.0000 0.0065
-8.500 -0.9394 0.01352 0.00776 0.0021 1.0000 0.0069
-8.250 -0.9197 0.01306 0.00727 0.0036 1.0000 0.0074
-8.000 -0.8995 0.01266 0.00685 0.0050 1.0000 0.0080
-7.750 -0.8789 0.01231 0.00646 0.0063 1.0000 0.0085
-7.500 -0.8555 0.01197 0.00609 0.0071 0.9997 0.0091
-7.250 -0.8252 0.01159 0.00567 0.0063 0.9985 0.0102
-7.000 -0.7951 0.01121 0.00528 0.0055 0.9969 0.0121
-6.750 -0.7643 0.01090 0.00496 0.0047 0.9953 0.0135
-6.500 -0.7344 0.01056 0.00465 0.0040 0.9934 0.0171
-6.250 -0.7047 0.01029 0.00437 0.0035 0.9911 0.0199
-6.000 -0.6737 0.01000 0.00409 0.0026 0.9886 0.0235
-5.750 -0.6407 0.00974 0.00383 0.0013 0.9862 0.0272
-5.500 -0.6098 0.00953 0.00360 0.0005 0.9815 0.0290
-5.250 -0.5775 0.00928 0.00334 -0.0005 0.9768 0.0317
-5.000 -0.5476 0.00903 0.00310 -0.0010 0.9712 0.0350
-4.750 -0.5160 0.00880 0.00286 -0.0019 0.9660 0.0387
-4.250 -0.4500 0.00819 0.00241 -0.0045 0.9537 0.0711
-4.000 -0.4151 0.00794 0.00221 -0.0061 0.9455 0.0851
-3.750 -0.3798 0.00770 0.00200 -0.0079 0.9337 0.1022
-3.500 -0.3483 0.00740 0.00179 -0.0088 0.9173 0.1331
-3.250 -0.3213 0.00705 0.00159 -0.0088 0.8979 0.1855
-3.000 -0.2952 0.00686 0.00146 -0.0084 0.8777 0.2179
-2.750 -0.2700 0.00671 0.00134 -0.0079 0.8572 0.2464
-2.500 -0.2452 0.00661 0.00123 -0.0072 0.8344 0.2705
-2.250 -0.2208 0.00652 0.00114 -0.0064 0.8075 0.2950
-2.000 -0.1970 0.00643 0.00105 -0.0055 0.7798 0.3264
-1.750 -0.1737 0.00625 0.00096 -0.0046 0.7561 0.3767
-1.500 -0.1498 0.00609 0.00090 -0.0038 0.7350 0.4239
-1.250 -0.1262 0.00593 0.00085 -0.0029 0.7139 0.4766
-1.000 -0.1011 0.00586 0.00081 -0.0023 0.6934 0.5051
-0.750 -0.0756 0.00581 0.00078 -0.0018 0.6756 0.5291
-0.500 -0.0506 0.00573 0.00075 -0.0012 0.6577 0.5618
-0.250 -0.0254 0.00568 0.00074 -0.0006 0.6376 0.5898
0.000 0.0000 0.00566 0.00073 0.0000 0.6153 0.6158
0.250 0.0253 0.00568 0.00074 0.0006 0.5897 0.6375
0.500 0.0504 0.00574 0.00075 0.0012 0.5580 0.6574
0.750 0.0755 0.00582 0.00078 0.0018 0.5277 0.6753
1.000 0.1010 0.00586 0.00081 0.0023 0.5047 0.6938
1.250 0.1262 0.00592 0.00085 0.0029 0.4786 0.7140
1.500 0.1500 0.00606 0.00090 0.0038 0.4293 0.7352
1.750 0.1737 0.00624 0.00096 0.0046 0.3779 0.7563
2.000 0.1969 0.00642 0.00105 0.0056 0.3266 0.7800
2.250 0.2208 0.00652 0.00114 0.0064 0.2952 0.8076
2.500 0.2453 0.00660 0.00123 0.0072 0.2714 0.8345
2.750 0.2701 0.00671 0.00134 0.0079 0.2472 0.8570
3.000 0.2954 0.00685 0.00145 0.0084 0.2198 0.8778
3.250 0.3211 0.00707 0.00160 0.0088 0.1824 0.8981
3.500 0.3484 0.00739 0.00179 0.0088 0.1339 0.9177
3.750 0.3798 0.00769 0.00200 0.0079 0.1028 0.9336
4.000 0.4150 0.00794 0.00221 0.0062 0.0848 0.9452
4.250 0.4500 0.00819 0.00241 0.0045 0.0709 0.9537
4.750 0.5161 0.00880 0.00286 0.0019 0.0387 0.9661
5.000 0.5477 0.00903 0.00310 0.0010 0.0348 0.9713
5.250 0.5776 0.00929 0.00334 0.0005 0.0311 0.9768
5.500 0.6099 0.00952 0.00359 -0.0006 0.0289 0.9815
5.750 0.6408 0.00974 0.00383 -0.0013 0.0270 0.9862
6.000 0.6739 0.01000 0.00410 -0.0027 0.0234 0.9887
6.250 0.7049 0.01029 0.00438 -0.0035 0.0201 0.9912
6.500 0.7345 0.01056 0.00465 -0.0041 0.0172 0.9935
6.750 0.7645 0.01090 0.00496 -0.0047 0.0136 0.9953
7.000 0.7953 0.01121 0.00528 -0.0056 0.0118 0.9970
7.250 0.8255 0.01159 0.00567 -0.0064 0.0102 0.9986
7.500 0.8560 0.01198 0.00609 -0.0072 0.0091 0.9998
7.750 0.8786 0.01230 0.00645 -0.0063 0.0086 1.0000
8.000 0.8992 0.01266 0.00685 -0.0049 0.0080 1.0000
8.250 0.9195 0.01305 0.00726 -0.0036 0.0075 1.0000
8.500 0.9392 0.01351 0.00775 -0.0021 0.0069 1.0000
8.750 0.9584 0.01403 0.00833 -0.0006 0.0064 1.0000
9.000 0.9787 0.01443 0.00880 0.0008 0.0062 1.0000
9.250 0.9986 0.01486 0.00929 0.0021 0.0060 1.0000
9.500 1.0186 0.01530 0.00977 0.0035 0.0056 1.0000
9.750 1.0379 0.01579 0.01032 0.0049 0.0054 1.0000
10.000 1.0569 0.01630 0.01088 0.0063 0.0051 1.0000
10.250 1.0754 0.01687 0.01150 0.0078 0.0049 1.0000
10.500 1.0926 0.01754 0.01224 0.0095 0.0047 1.0000
10.750 1.1079 0.01839 0.01318 0.0114 0.0044 1.0000
11.000 1.1251 0.01903 0.01391 0.0130 0.0044 1.0000
11.250 1.1421 0.01967 0.01464 0.0145 0.0042 1.0000
11.500 1.1578 0.02040 0.01547 0.0163 0.0041 1.0000
11.750 1.1716 0.02125 0.01642 0.0183 0.0041 1.0000
12.000 1.1861 0.02200 0.01726 0.0201 0.0039 1.0000
12.250 1.1984 0.02287 0.01823 0.0221 0.0038 1.0000
12.500 1.2089 0.02383 0.01929 0.0244 0.0038 1.0000
12.750 1.2174 0.02466 0.02021 0.0270 0.0036 1.0000
13.000 1.2205 0.02572 0.02138 0.0303 0.0036 1.0000
13.250 1.2270 0.02668 0.02243 0.0328 0.0035 1.0000
13.500 1.2314 0.02787 0.02373 0.0351 0.0035 1.0000
13.750 1.2351 0.02921 0.02518 0.0371 0.0034 1.0000
14.000 1.2365 0.03087 0.02696 0.0387 0.0033 1.0000
14.250 1.2370 0.03278 0.02897 0.0399 0.0033 1.0000
14.500 1.2344 0.03522 0.03155 0.0404 0.0032 1.0000
14.750 1.2311 0.03803 0.03449 0.0402 0.0032 1.0000
15.000 1.2233 0.04173 0.03833 0.0391 0.0032 1.0000
15.250 1.2200 0.04524 0.04195 0.0376 0.0031 1.0000
15.500 1.1995 0.05175 0.04867 0.0338 0.0031 1.0000
15.750 1.1857 0.05779 0.05484 0.0300 0.0031 1.0000
16.000 1.1637 0.06571 0.06292 0.0249 0.0031 1.0000
16.250 1.1202 0.07802 0.07546 0.0174 0.0032 1.0000
16.500 1.0530 0.09511 0.09281 0.0080 0.0034 1.0000
16.750 1.0053 0.10869 0.10651 0.0011 0.0034 1.0000
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Polar data table (+)
Polar graphs
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