RG 8 AIRFOIL (rg8-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: RG 8 AIRFOIL (rg8-il) Reynolds number: 1,000,000 Max Cl/Cd: 107.47 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-rg8-il-1000000.txt Download as CSV file: xf-rg8-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: RG 8 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
------ -------- --------- --------- -------- -------- --------
-11.750 -0.6952 0.06223 0.06036 -0.0514 1.0000 0.0089
-11.500 -0.7359 0.05086 0.04882 -0.0602 1.0000 0.0087
-11.250 -0.7652 0.04452 0.04232 -0.0638 1.0000 0.0086
-11.000 -0.7820 0.04144 0.03915 -0.0639 1.0000 0.0087
-10.750 -0.8159 0.03883 0.03644 -0.0605 1.0000 0.0086
-10.500 -0.8329 0.03571 0.03311 -0.0580 1.0000 0.0086
-10.250 -0.8390 0.03312 0.03031 -0.0558 1.0000 0.0087
-10.000 -0.8178 0.02991 0.02676 -0.0588 0.9979 0.0090
-9.750 -0.7920 0.02769 0.02426 -0.0612 0.9960 0.0092
-9.500 -0.7625 0.02637 0.02273 -0.0632 0.9947 0.0093
-9.250 -0.7469 0.02149 0.01735 -0.0648 0.9919 0.0098
-9.000 -0.7191 0.02029 0.01607 -0.0660 0.9898 0.0102
-8.750 -0.6886 0.01952 0.01523 -0.0674 0.9882 0.0106
-8.500 -0.6574 0.01864 0.01425 -0.0689 0.9868 0.0110
-8.250 -0.6255 0.01772 0.01321 -0.0704 0.9857 0.0115
-8.000 -0.5932 0.01672 0.01208 -0.0719 0.9847 0.0118
-7.750 -0.5601 0.01583 0.01108 -0.0736 0.9840 0.0122
-7.500 -0.5349 0.01504 0.01021 -0.0734 0.9805 0.0124
-7.250 -0.5044 0.01447 0.00957 -0.0742 0.9780 0.0127
-7.000 -0.4740 0.01323 0.00819 -0.0753 0.9761 0.0132
-6.750 -0.4420 0.01222 0.00712 -0.0768 0.9746 0.0142
-6.500 -0.4081 0.01165 0.00651 -0.0783 0.9734 0.0148
-6.250 -0.3736 0.01114 0.00595 -0.0800 0.9725 0.0154
-6.000 -0.3384 0.01066 0.00541 -0.0818 0.9717 0.0160
-5.750 -0.3150 0.01024 0.00495 -0.0808 0.9661 0.0166
-5.500 -0.2824 0.00985 0.00452 -0.0819 0.9638 0.0171
-5.250 -0.2484 0.00935 0.00396 -0.0833 0.9620 0.0184
-5.000 -0.2134 0.00894 0.00353 -0.0850 0.9606 0.0208
-4.750 -0.1776 0.00861 0.00318 -0.0867 0.9595 0.0231
-4.500 -0.1495 0.00810 0.00280 -0.0868 0.9551 0.0462
-4.250 -0.1192 0.00768 0.00251 -0.0875 0.9509 0.0770
-4.000 -0.0846 0.00733 0.00227 -0.0890 0.9481 0.1059
-3.750 -0.0486 0.00696 0.00204 -0.0910 0.9456 0.1426
-3.500 -0.0204 0.00665 0.00185 -0.0911 0.9380 0.1802
-3.250 0.0151 0.00625 0.00165 -0.0930 0.9331 0.2366
-3.000 0.0469 0.00590 0.00148 -0.0940 0.9250 0.2959
-2.750 0.0810 0.00549 0.00129 -0.0955 0.9171 0.3752
-2.500 0.1104 0.00512 0.00120 -0.0961 0.9053 0.4706
-2.250 0.1404 0.00502 0.00114 -0.0965 0.8927 0.5094
-2.000 0.1697 0.00497 0.00110 -0.0966 0.8788 0.5390
-1.750 0.1982 0.00497 0.00107 -0.0967 0.8638 0.5597
-1.500 0.2261 0.00499 0.00105 -0.0965 0.8478 0.5731
-1.250 0.2535 0.00502 0.00103 -0.0963 0.8310 0.5842
-1.000 0.2805 0.00507 0.00102 -0.0960 0.8135 0.5945
-0.750 0.3073 0.00513 0.00101 -0.0956 0.7950 0.6047
-0.500 0.3338 0.00518 0.00102 -0.0952 0.7760 0.6146
0.000 0.3866 0.00534 0.00105 -0.0944 0.7368 0.6329
0.250 0.4128 0.00542 0.00108 -0.0939 0.7162 0.6414
0.500 0.4390 0.00552 0.00111 -0.0935 0.6961 0.6503
0.750 0.4652 0.00561 0.00115 -0.0931 0.6748 0.6598
1.000 0.4911 0.00572 0.00120 -0.0926 0.6532 0.6689
1.250 0.5175 0.00583 0.00125 -0.0922 0.6312 0.6784
1.500 0.5433 0.00595 0.00132 -0.0917 0.6086 0.6881
1.750 0.5694 0.00606 0.00139 -0.0913 0.5852 0.6983
2.000 0.5954 0.00621 0.00146 -0.0909 0.5625 0.7085
2.250 0.6213 0.00633 0.00156 -0.0904 0.5390 0.7179
2.500 0.6472 0.00648 0.00165 -0.0900 0.5155 0.7277
3.000 0.6988 0.00680 0.00187 -0.0892 0.4665 0.7496
3.250 0.7243 0.00698 0.00199 -0.0887 0.4411 0.7618
3.500 0.7496 0.00717 0.00213 -0.0882 0.4163 0.7750
3.750 0.7750 0.00735 0.00227 -0.0877 0.3912 0.7896
4.000 0.8002 0.00754 0.00243 -0.0872 0.3679 0.8061
4.250 0.8248 0.00775 0.00260 -0.0866 0.3427 0.8247
4.500 0.8489 0.00798 0.00279 -0.0858 0.3155 0.8454
4.750 0.8722 0.00821 0.00298 -0.0849 0.2883 0.8706
5.000 0.8937 0.00837 0.00318 -0.0836 0.2664 0.9048
5.250 0.9167 0.00853 0.00334 -0.0825 0.2409 1.0000
5.500 0.9411 0.00891 0.00358 -0.0820 0.2122 1.0000
5.750 0.9651 0.00932 0.00384 -0.0814 0.1830 1.0000
6.000 0.9889 0.00974 0.00413 -0.0808 0.1566 1.0000
6.250 1.0122 0.01020 0.00445 -0.0801 0.1290 1.0000
6.500 1.0355 0.01065 0.00478 -0.0794 0.1059 1.0000
6.750 1.0588 0.01109 0.00512 -0.0787 0.0866 1.0000
7.000 1.0821 0.01152 0.00547 -0.0780 0.0709 1.0000
7.250 1.1050 0.01198 0.00585 -0.0772 0.0568 1.0000
7.500 1.1276 0.01245 0.00625 -0.0764 0.0445 1.0000
7.750 1.1497 0.01296 0.00669 -0.0755 0.0328 1.0000
8.000 1.1700 0.01362 0.00725 -0.0743 0.0191 1.0000
8.250 1.1899 0.01431 0.00790 -0.0730 0.0114 1.0000
8.500 1.2112 0.01486 0.00847 -0.0720 0.0095 1.0000
8.750 1.2327 0.01537 0.00902 -0.0709 0.0086 1.0000
9.000 1.2526 0.01599 0.00969 -0.0696 0.0078 1.0000
9.250 1.2703 0.01679 0.01057 -0.0680 0.0072 1.0000
9.500 1.2902 0.01734 0.01118 -0.0667 0.0070 1.0000
9.750 1.3089 0.01795 0.01187 -0.0653 0.0068 1.0000
10.000 1.3264 0.01862 0.01261 -0.0637 0.0065 1.0000
10.250 1.3423 0.01930 0.01335 -0.0618 0.0063 1.0000
10.500 1.3558 0.02001 0.01413 -0.0595 0.0061 1.0000
10.750 1.3682 0.02075 0.01493 -0.0571 0.0059 1.0000
11.000 1.3788 0.02161 0.01586 -0.0545 0.0057 1.0000
11.250 1.3868 0.02262 0.01695 -0.0516 0.0055 1.0000
11.500 1.3923 0.02379 0.01823 -0.0485 0.0054 1.0000
11.750 1.3927 0.02532 0.01988 -0.0449 0.0052 1.0000
12.000 1.3921 0.02699 0.02167 -0.0415 0.0052 1.0000
12.250 1.3859 0.02918 0.02403 -0.0379 0.0050 1.0000
12.500 1.3926 0.03048 0.02542 -0.0359 0.0050 1.0000
12.750 1.3967 0.03206 0.02710 -0.0339 0.0049 1.0000
13.000 1.4002 0.03376 0.02890 -0.0322 0.0048 1.0000
13.250 1.4032 0.03558 0.03084 -0.0306 0.0047 1.0000
13.500 1.4021 0.03792 0.03329 -0.0292 0.0047 1.0000
13.750 1.4020 0.04029 0.03578 -0.0281 0.0046 1.0000
14.000 1.3995 0.04308 0.03869 -0.0274 0.0046 1.0000
14.250 1.3950 0.04628 0.04202 -0.0270 0.0046 1.0000
14.500 1.3896 0.04978 0.04566 -0.0271 0.0045 1.0000
14.750 1.3818 0.05383 0.04985 -0.0276 0.0045 1.0000
15.000 1.3755 0.05794 0.05410 -0.0285 0.0045 1.0000
15.250 1.3663 0.06269 0.05899 -0.0300 0.0044 1.0000
15.500 1.3566 0.06782 0.06426 -0.0319 0.0044 1.0000
15.750 1.3456 0.07342 0.07000 -0.0343 0.0044 1.0000
16.000 1.3315 0.07983 0.07656 -0.0373 0.0044 1.0000
16.250 1.3195 0.08621 0.08308 -0.0405 0.0044 1.0000
16.500 1.3045 0.09338 0.09040 -0.0443 0.0044 1.0000
16.750 1.2898 0.10078 0.09794 -0.0484 0.0044 1.0000
17.000 1.2738 0.10872 0.10603 -0.0529 0.0044 1.0000
17.250 1.2572 0.11699 0.11444 -0.0577 0.0044 1.0000
17.500 1.2414 0.12536 0.12294 -0.0627 0.0045 1.0000
17.750 1.2255 0.13400 0.13172 -0.0679 0.0045 1.0000
18.000 1.2079 0.14326 0.14111 -0.0736 0.0045 1.0000
18.250 1.1911 0.15259 0.15057 -0.0795 0.0045 1.0000
18.500 1.1739 0.16236 0.16045 -0.0856 0.0046 1.0000
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Polar data table (+)
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