RAF 6 AIRFOIL (raf6-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: RAF 6 AIRFOIL (raf6-il) Reynolds number: 1,000,000 Max Cl/Cd: 104.8 at α=7.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-raf6-il-1000000.txt Download as CSV file: xf-raf6-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: RAF 6 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.3935 0.11517 0.11354 -0.0234 1.0000 0.0104
-10.000 -0.3946 0.11196 0.11034 -0.0238 1.0000 0.0104
-9.750 -0.3956 0.10887 0.10727 -0.0240 1.0000 0.0105
-9.500 -0.3971 0.10579 0.10421 -0.0240 1.0000 0.0105
-9.250 -0.3914 0.10181 0.10024 -0.0264 0.9994 0.0105
-9.000 -0.3867 0.09644 0.09488 -0.0300 0.9982 0.0106
-8.750 -0.3753 0.09293 0.09137 -0.0324 0.9971 0.0107
-8.500 -0.3632 0.08931 0.08775 -0.0358 0.9959 0.0108
-8.250 -0.3505 0.08548 0.08393 -0.0401 0.9947 0.0110
-8.000 -0.3429 0.08174 0.08020 -0.0438 0.9915 0.0111
-7.750 -0.3271 0.07691 0.07537 -0.0511 0.9881 0.0113
-7.500 -0.3047 0.07147 0.06989 -0.0599 0.9862 0.0117
-7.250 -0.2797 0.06566 0.06403 -0.0689 0.9848 0.0124
-7.000 -0.2578 0.05711 0.05532 -0.0779 0.9778 0.0134
-6.750 -0.2315 0.05132 0.04939 -0.0833 0.9758 0.0135
-6.500 -0.2100 0.04448 0.04238 -0.0886 0.9742 0.0138
-6.250 -0.1805 0.04151 0.03932 -0.0921 0.9734 0.0140
-6.000 -0.1644 0.03913 0.03685 -0.0916 0.9665 0.0142
-5.750 -0.1342 0.03620 0.03379 -0.0942 0.9645 0.0147
-5.500 -0.1007 0.03259 0.02997 -0.0969 0.9630 0.0161
-5.000 -0.0521 0.02231 0.01885 -0.0964 0.9536 0.0176
-4.750 -0.0220 0.02114 0.01760 -0.0976 0.9496 0.0180
-4.500 -0.0046 0.01307 0.00853 -0.0944 0.9426 0.0149
-4.250 0.0243 0.01216 0.00748 -0.0945 0.9354 0.0157
-4.000 0.0521 0.01124 0.00639 -0.0942 0.9250 0.0166
-3.750 0.0832 0.01051 0.00550 -0.0947 0.9111 0.0171
-3.500 0.1139 0.00944 0.00430 -0.0952 0.8912 0.0181
-3.250 0.1431 0.00917 0.00392 -0.0954 0.8687 0.0189
-3.000 0.1703 0.00893 0.00356 -0.0951 0.8504 0.0199
-2.750 0.1971 0.00877 0.00329 -0.0947 0.8360 0.0209
-2.500 0.2228 0.00836 0.00280 -0.0941 0.8243 0.0223
-2.250 0.2493 0.00820 0.00260 -0.0937 0.8135 0.0236
-2.000 0.2759 0.00808 0.00242 -0.0934 0.8037 0.0251
-1.750 0.3030 0.00796 0.00227 -0.0931 0.7944 0.0264
-1.500 0.3291 0.00771 0.00197 -0.0926 0.7849 0.0290
-1.250 0.3558 0.00764 0.00187 -0.0923 0.7735 0.0313
-1.000 0.3824 0.00758 0.00177 -0.0919 0.7601 0.0333
-0.750 0.4085 0.00744 0.00158 -0.0914 0.7450 0.0378
-0.500 0.4344 0.00743 0.00151 -0.0908 0.7266 0.0418
-0.250 0.4595 0.00740 0.00140 -0.0901 0.6991 0.0500
0.000 0.4823 0.00750 0.00135 -0.0889 0.6530 0.0669
0.250 0.4932 0.00603 0.00146 -0.0863 0.5910 0.7332
0.500 0.5031 0.00600 0.00172 -0.0819 0.5175 0.9415
0.750 0.5425 0.00652 0.00192 -0.0844 0.4488 0.9883
1.000 0.5910 0.00690 0.00206 -0.0892 0.4077 0.9968
1.250 0.6301 0.00717 0.00214 -0.0918 0.3774 1.0000
1.500 0.6513 0.00735 0.00220 -0.0904 0.3523 1.0000
1.750 0.6724 0.00756 0.00226 -0.0891 0.3266 1.0000
2.250 0.7151 0.00798 0.00242 -0.0864 0.2822 1.0000
2.500 0.7372 0.00817 0.00252 -0.0852 0.2658 1.0000
2.750 0.7596 0.00836 0.00262 -0.0841 0.2531 1.0000
3.000 0.7824 0.00855 0.00273 -0.0831 0.2428 1.0000
3.250 0.8063 0.00869 0.00284 -0.0823 0.2361 1.0000
3.500 0.8299 0.00888 0.00297 -0.0814 0.2286 1.0000
3.750 0.8546 0.00902 0.00309 -0.0808 0.2235 1.0000
4.000 0.8792 0.00918 0.00321 -0.0802 0.2185 1.0000
4.250 0.9033 0.00939 0.00338 -0.0795 0.2127 1.0000
4.500 0.9288 0.00951 0.00350 -0.0790 0.2093 1.0000
4.750 0.9539 0.00966 0.00364 -0.0785 0.2054 1.0000
5.000 0.9786 0.00985 0.00381 -0.0780 0.2013 1.0000
5.250 1.0031 0.01007 0.00401 -0.0774 0.1970 1.0000
5.500 1.0287 0.01019 0.00415 -0.0770 0.1942 1.0000
5.750 1.0538 0.01035 0.00431 -0.0766 0.1905 1.0000
6.000 1.0784 0.01056 0.00450 -0.0761 0.1868 1.0000
6.250 1.1024 0.01080 0.00473 -0.0754 0.1827 1.0000
6.500 1.1279 0.01094 0.00490 -0.0751 0.1805 1.0000
6.750 1.1528 0.01111 0.00509 -0.0746 0.1772 1.0000
7.000 1.1771 0.01132 0.00529 -0.0741 0.1729 1.0000
7.250 1.2013 0.01154 0.00550 -0.0735 0.1675 1.0000
7.500 1.2261 0.01170 0.00568 -0.0731 0.1625 1.0000
7.750 1.2496 0.01196 0.00591 -0.0724 0.1572 1.0000
8.000 1.2737 0.01217 0.00615 -0.0719 0.1530 1.0000
8.250 1.2975 0.01239 0.00637 -0.0713 0.1478 1.0000
8.500 1.3201 0.01269 0.00664 -0.0705 0.1413 1.0000
8.750 1.3435 0.01291 0.00690 -0.0699 0.1361 1.0000
9.000 1.3653 0.01326 0.00721 -0.0690 0.1290 1.0000
9.250 1.3877 0.01353 0.00750 -0.0682 0.1227 1.0000
9.500 1.4083 0.01391 0.00785 -0.0671 0.1143 1.0000
9.750 1.4272 0.01436 0.00825 -0.0657 0.1042 1.0000
10.000 1.4448 0.01489 0.00872 -0.0641 0.0913 1.0000
10.250 1.4570 0.01581 0.00946 -0.0617 0.0666 1.0000
10.500 1.4557 0.01776 0.01109 -0.0571 0.0239 1.0000
10.750 1.4696 0.01854 0.01190 -0.0550 0.0191 1.0000
11.000 1.4840 0.01928 0.01268 -0.0530 0.0165 1.0000
11.250 1.4992 0.01993 0.01339 -0.0512 0.0151 1.0000
11.500 1.5119 0.02075 0.01426 -0.0490 0.0137 1.0000
11.750 1.5243 0.02158 0.01517 -0.0469 0.0127 1.0000
12.000 1.5382 0.02228 0.01595 -0.0451 0.0121 1.0000
12.250 1.5508 0.02308 0.01681 -0.0431 0.0113 1.0000
12.500 1.5610 0.02403 0.01782 -0.0409 0.0106 1.0000
12.750 1.5642 0.02550 0.01941 -0.0379 0.0098 1.0000
13.000 1.5758 0.02638 0.02036 -0.0362 0.0096 1.0000
13.250 1.5851 0.02743 0.02149 -0.0342 0.0092 1.0000
13.500 1.5930 0.02862 0.02277 -0.0322 0.0088 1.0000
13.750 1.5994 0.02996 0.02420 -0.0303 0.0085 1.0000
14.000 1.6045 0.03144 0.02576 -0.0284 0.0082 1.0000
14.250 1.6067 0.03324 0.02766 -0.0265 0.0079 1.0000
14.500 1.6038 0.03556 0.03009 -0.0245 0.0077 1.0000
14.750 1.5932 0.03876 0.03344 -0.0225 0.0074 1.0000
15.000 1.5848 0.04196 0.03678 -0.0212 0.0073 1.0000
15.250 1.5832 0.04464 0.03958 -0.0204 0.0072 1.0000
15.500 1.5794 0.04775 0.04281 -0.0200 0.0071 1.0000
15.750 1.5728 0.05141 0.04659 -0.0200 0.0069 1.0000
16.000 1.5631 0.05574 0.05106 -0.0206 0.0068 1.0000
16.250 1.5504 0.06086 0.05632 -0.0218 0.0068 1.0000
16.500 1.5330 0.06715 0.06277 -0.0240 0.0067 1.0000
16.750 1.5116 0.07448 0.07027 -0.0269 0.0067 1.0000
17.000 1.4845 0.08310 0.07907 -0.0306 0.0067 1.0000
17.250 1.4531 0.09240 0.08854 -0.0344 0.0068 1.0000
17.500 1.4186 0.10217 0.09846 -0.0384 0.0069 1.0000
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