RG 8 AIRFOIL (rg8-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: RG 8 AIRFOIL (rg8-il) Reynolds number: 500,000 Max Cl/Cd: 83.34 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-rg8-il-500000-n5.txt Download as CSV file: xf-rg8-il-500000-n5.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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.750 -0.7381 0.05348 0.05076 -0.0601 1.0000 0.0082
-11.500 -0.7685 0.04622 0.04331 -0.0647 1.0000 0.0082
-11.250 -0.7862 0.04238 0.03935 -0.0657 1.0000 0.0082
-11.000 -0.8199 0.03900 0.03582 -0.0635 1.0000 0.0081
-10.750 -0.8302 0.03683 0.03351 -0.0614 1.0000 0.0082
-10.500 -0.8344 0.03462 0.03113 -0.0594 1.0000 0.0083
-10.250 -0.8218 0.03277 0.02910 -0.0597 0.9990 0.0086
-10.000 -0.8001 0.03046 0.02654 -0.0619 0.9967 0.0089
-9.750 -0.7769 0.02808 0.02388 -0.0639 0.9947 0.0091
-9.500 -0.7538 0.02607 0.02160 -0.0651 0.9925 0.0094
-9.250 -0.7295 0.02434 0.01962 -0.0661 0.9900 0.0097
-9.000 -0.7029 0.02284 0.01789 -0.0672 0.9877 0.0100
-8.750 -0.6745 0.02155 0.01639 -0.0685 0.9858 0.0103
-8.500 -0.6447 0.02039 0.01505 -0.0698 0.9843 0.0105
-8.250 -0.6129 0.01968 0.01420 -0.0713 0.9831 0.0108
-8.000 -0.5920 0.01807 0.01243 -0.0709 0.9790 0.0113
-7.750 -0.5646 0.01696 0.01120 -0.0716 0.9762 0.0118
-7.500 -0.5347 0.01613 0.01029 -0.0726 0.9740 0.0121
-7.250 -0.5034 0.01539 0.00947 -0.0738 0.9723 0.0125
-7.000 -0.4711 0.01470 0.00871 -0.0752 0.9709 0.0130
-6.750 -0.4477 0.01412 0.00806 -0.0746 0.9657 0.0133
-6.500 -0.4178 0.01352 0.00738 -0.0753 0.9626 0.0138
-6.250 -0.3858 0.01296 0.00675 -0.0764 0.9603 0.0142
-6.000 -0.3526 0.01247 0.00620 -0.0778 0.9585 0.0148
-5.750 -0.3271 0.01209 0.00576 -0.0774 0.9531 0.0153
-5.500 -0.2971 0.01155 0.00516 -0.0781 0.9494 0.0163
-5.250 -0.2648 0.01109 0.00464 -0.0792 0.9467 0.0175
-5.000 -0.2311 0.01070 0.00422 -0.0805 0.9447 0.0189
-4.750 -0.2055 0.01040 0.00389 -0.0800 0.9377 0.0206
-4.500 -0.1725 0.01003 0.00354 -0.0812 0.9340 0.0266
-4.250 -0.1364 0.00960 0.00319 -0.0831 0.9313 0.0489
-4.000 -0.1066 0.00926 0.00294 -0.0837 0.9243 0.0702
-3.750 -0.0709 0.00886 0.00267 -0.0856 0.9194 0.1050
-3.500 -0.0368 0.00855 0.00245 -0.0871 0.9130 0.1338
-3.250 -0.0020 0.00822 0.00223 -0.0887 0.9053 0.1730
-3.000 0.0315 0.00793 0.00204 -0.0901 0.8960 0.2104
-2.750 0.0650 0.00755 0.00184 -0.0915 0.8855 0.2744
-2.500 0.0964 0.00710 0.00166 -0.0926 0.8730 0.3630
-2.250 0.1262 0.00676 0.00156 -0.0932 0.8590 0.4508
-2.000 0.1554 0.00664 0.00152 -0.0934 0.8438 0.5008
-1.750 0.1840 0.00662 0.00148 -0.0934 0.8278 0.5261
-1.500 0.2120 0.00663 0.00144 -0.0933 0.8107 0.5450
-1.250 0.2395 0.00666 0.00142 -0.0931 0.7928 0.5620
-1.000 0.2666 0.00670 0.00140 -0.0928 0.7746 0.5767
-0.750 0.2934 0.00676 0.00140 -0.0925 0.7556 0.5899
-0.500 0.3199 0.00682 0.00141 -0.0921 0.7359 0.6013
0.000 0.3725 0.00699 0.00144 -0.0912 0.6960 0.6230
0.250 0.3984 0.00708 0.00147 -0.0907 0.6753 0.6340
0.500 0.4244 0.00718 0.00152 -0.0902 0.6548 0.6441
0.750 0.4503 0.00729 0.00156 -0.0898 0.6336 0.6544
1.000 0.4760 0.00741 0.00162 -0.0892 0.6122 0.6649
1.250 0.5018 0.00753 0.00170 -0.0887 0.5903 0.6743
1.750 0.5531 0.00780 0.00185 -0.0878 0.5462 0.6907
2.000 0.5788 0.00796 0.00194 -0.0873 0.5239 0.6988
2.250 0.6042 0.00812 0.00205 -0.0868 0.5007 0.7071
2.500 0.6297 0.00829 0.00216 -0.0863 0.4777 0.7154
2.750 0.6550 0.00848 0.00229 -0.0858 0.4548 0.7250
3.000 0.6804 0.00865 0.00243 -0.0853 0.4317 0.7347
3.250 0.7055 0.00885 0.00259 -0.0847 0.4088 0.7447
3.500 0.7306 0.00906 0.00275 -0.0842 0.3855 0.7561
3.750 0.7554 0.00927 0.00292 -0.0836 0.3619 0.7687
4.000 0.7798 0.00951 0.00312 -0.0830 0.3378 0.7819
4.250 0.8042 0.00974 0.00333 -0.0823 0.3143 0.7961
4.500 0.8283 0.00998 0.00355 -0.0816 0.2920 0.8125
4.750 0.8516 0.01024 0.00378 -0.0808 0.2691 0.8314
5.000 0.8742 0.01049 0.00402 -0.0797 0.2449 0.8537
5.250 0.8951 0.01077 0.00429 -0.0783 0.2202 0.8815
5.500 0.9137 0.01102 0.00453 -0.0764 0.1966 0.9263
5.750 0.9411 0.01134 0.00479 -0.0765 0.1732 1.0000
6.000 0.9647 0.01178 0.00512 -0.0759 0.1495 1.0000
6.250 0.9875 0.01227 0.00549 -0.0751 0.1244 1.0000
6.500 1.0099 0.01280 0.00590 -0.0744 0.1010 1.0000
6.750 1.0328 0.01327 0.00629 -0.0736 0.0831 1.0000
7.000 1.0551 0.01377 0.00672 -0.0728 0.0671 1.0000
7.250 1.0766 0.01434 0.00719 -0.0719 0.0511 1.0000
7.500 1.0985 0.01487 0.00766 -0.0710 0.0397 1.0000
7.750 1.1200 0.01540 0.00817 -0.0701 0.0308 1.0000
8.000 1.1412 0.01595 0.00870 -0.0691 0.0232 1.0000
8.250 1.1614 0.01657 0.00929 -0.0679 0.0156 1.0000
8.500 1.1810 0.01722 0.00994 -0.0667 0.0109 1.0000
8.750 1.2004 0.01786 0.01061 -0.0654 0.0089 1.0000
9.000 1.2198 0.01848 0.01128 -0.0641 0.0079 1.0000
9.250 1.2387 0.01909 0.01196 -0.0627 0.0072 1.0000
9.500 1.2566 0.01975 0.01270 -0.0612 0.0066 1.0000
9.750 1.2723 0.02046 0.01349 -0.0594 0.0061 1.0000
10.000 1.2854 0.02129 0.01440 -0.0571 0.0057 1.0000
10.250 1.2967 0.02223 0.01544 -0.0546 0.0055 1.0000
10.500 1.3098 0.02301 0.01631 -0.0524 0.0054 1.0000
10.750 1.3213 0.02389 0.01729 -0.0502 0.0052 1.0000
11.000 1.3317 0.02485 0.01835 -0.0478 0.0051 1.0000
11.250 1.3408 0.02589 0.01949 -0.0454 0.0050 1.0000
11.500 1.3487 0.02703 0.02076 -0.0430 0.0048 1.0000
11.750 1.3555 0.02826 0.02210 -0.0407 0.0047 1.0000
12.000 1.3608 0.02964 0.02360 -0.0384 0.0046 1.0000
12.250 1.3649 0.03117 0.02525 -0.0362 0.0045 1.0000
12.500 1.3679 0.03286 0.02705 -0.0341 0.0044 1.0000
12.750 1.3698 0.03471 0.02903 -0.0323 0.0043 1.0000
13.000 1.3703 0.03681 0.03125 -0.0307 0.0042 1.0000
13.250 1.3697 0.03913 0.03370 -0.0294 0.0042 1.0000
13.500 1.3683 0.04169 0.03639 -0.0284 0.0041 1.0000
13.750 1.3664 0.04447 0.03930 -0.0278 0.0040 1.0000
14.000 1.3621 0.04771 0.04268 -0.0276 0.0040 1.0000
14.250 1.3573 0.05121 0.04631 -0.0278 0.0039 1.0000
14.500 1.3523 0.05497 0.05020 -0.0285 0.0039 1.0000
14.750 1.3448 0.05930 0.05468 -0.0296 0.0038 1.0000
15.000 1.3363 0.06404 0.05956 -0.0312 0.0038 1.0000
15.250 1.3257 0.06938 0.06508 -0.0333 0.0038 1.0000
15.500 1.3163 0.07482 0.07066 -0.0357 0.0037 1.0000
15.750 1.3032 0.08115 0.07713 -0.0387 0.0037 1.0000
16.000 1.2908 0.08761 0.08374 -0.0420 0.0037 1.0000
16.250 1.2776 0.09448 0.09076 -0.0456 0.0037 1.0000
16.500 1.2630 0.10184 0.09826 -0.0496 0.0036 1.0000
16.750 1.2493 0.10924 0.10580 -0.0536 0.0037 1.0000
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