RG 8 AIRFOIL (rg8-il) Xfoil prediction polar at RE=100,000 Ncrit=9
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Airfoil: RG 8 AIRFOIL (rg8-il) Reynolds number: 100,000 Max Cl/Cd: 54.77 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-rg8-il-100000.txt Download as CSV file: xf-rg8-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.4409 0.10342 0.09836 -0.0304 1.0000 0.1224
-9.250 -0.4407 0.10032 0.09529 -0.0307 1.0000 0.1269
-9.000 -0.4865 0.09736 0.09258 -0.0373 1.0000 0.1315
-8.750 -0.4617 0.09296 0.08813 -0.0336 1.0000 0.1340
-8.500 -0.4491 0.09055 0.08572 -0.0314 1.0000 0.1399
-8.250 -0.4730 0.08733 0.08263 -0.0334 1.0000 0.1444
-8.000 -0.5405 0.08285 0.07834 -0.0414 1.0000 0.1460
-7.750 -0.4748 0.08138 0.07680 -0.0304 1.0000 0.1534
-7.500 -0.4977 0.07819 0.07374 -0.0311 1.0000 0.1573
-7.250 -0.5439 0.07168 0.06726 -0.0392 1.0000 0.1615
-7.000 -0.5647 0.05475 0.04977 -0.0469 1.0000 0.0935
-6.750 -0.5733 0.04150 0.03493 -0.0492 1.0000 0.0641
-6.500 -0.5590 0.03799 0.03105 -0.0486 1.0000 0.0644
-6.250 -0.5417 0.03481 0.02744 -0.0480 1.0000 0.0644
-6.000 -0.5212 0.03212 0.02423 -0.0473 1.0000 0.0637
-5.750 -0.4997 0.02935 0.02109 -0.0467 1.0000 0.0640
-5.500 -0.4775 0.02701 0.01850 -0.0461 1.0000 0.0653
-5.250 -0.4546 0.02532 0.01666 -0.0454 1.0000 0.0677
-5.000 -0.4313 0.02414 0.01529 -0.0447 1.0000 0.0730
-4.750 -0.4075 0.02261 0.01363 -0.0440 1.0000 0.0782
-4.500 -0.3843 0.02142 0.01246 -0.0432 1.0000 0.0859
-4.250 -0.3610 0.02020 0.01127 -0.0425 1.0000 0.1010
-4.000 -0.3375 0.01888 0.01023 -0.0422 1.0000 0.1385
-3.750 -0.3137 0.01779 0.00949 -0.0421 1.0000 0.2031
-3.500 -0.2902 0.01673 0.00904 -0.0424 1.0000 0.2992
-3.250 -0.2688 0.01577 0.00906 -0.0417 1.0000 0.4647
-3.000 -0.2502 0.01591 0.00942 -0.0397 1.0000 0.5746
-2.750 -0.2331 0.01618 0.00974 -0.0374 1.0000 0.6295
-2.500 -0.2168 0.01647 0.01005 -0.0349 1.0000 0.6698
-2.250 -0.2013 0.01674 0.01032 -0.0324 1.0000 0.7035
-2.000 -0.1866 0.01698 0.01055 -0.0299 1.0000 0.7326
-1.750 -0.1724 0.01720 0.01076 -0.0273 1.0000 0.7588
-1.500 -0.1451 0.01763 0.01116 -0.0272 0.9947 0.7870
-1.000 -0.0758 0.01830 0.01174 -0.0294 0.9739 0.8430
-0.750 -0.0442 0.01842 0.01183 -0.0299 0.9627 0.8691
-0.500 -0.0131 0.01845 0.01182 -0.0302 0.9516 0.8965
-0.250 0.0238 0.01843 0.01179 -0.0317 0.9415 0.9275
0.000 0.0798 0.01845 0.01177 -0.0371 0.9331 0.9589
0.250 0.1443 0.01841 0.01166 -0.0447 0.9239 0.9895
0.500 0.1943 0.01831 0.01149 -0.0500 0.9140 1.0000
0.750 0.2416 0.01815 0.01126 -0.0545 0.9038 1.0000
1.000 0.2832 0.01798 0.01104 -0.0578 0.8914 1.0000
1.250 0.3268 0.01778 0.01081 -0.0612 0.8796 1.0000
1.500 0.3760 0.01744 0.01046 -0.0652 0.8699 1.0000
1.750 0.4283 0.01696 0.00999 -0.0695 0.8608 1.0000
2.000 0.4718 0.01661 0.00966 -0.0722 0.8481 1.0000
2.250 0.5152 0.01622 0.00928 -0.0746 0.8350 1.0000
2.500 0.5579 0.01583 0.00891 -0.0769 0.8208 1.0000
2.750 0.5991 0.01547 0.00858 -0.0787 0.8050 1.0000
3.000 0.6391 0.01515 0.00826 -0.0802 0.7876 1.0000
3.250 0.6719 0.01503 0.00814 -0.0806 0.7665 1.0000
3.500 0.7053 0.01493 0.00803 -0.0809 0.7443 1.0000
3.750 0.7345 0.01496 0.00804 -0.0806 0.7198 1.0000
4.000 0.7641 0.01502 0.00804 -0.0803 0.6947 1.0000
4.250 0.7923 0.01515 0.00812 -0.0798 0.6683 1.0000
4.500 0.8174 0.01536 0.00828 -0.0788 0.6401 1.0000
4.750 0.8421 0.01561 0.00847 -0.0778 0.6112 1.0000
5.000 0.8660 0.01591 0.00869 -0.0766 0.5815 1.0000
5.250 0.8892 0.01625 0.00897 -0.0754 0.5511 1.0000
5.500 0.9114 0.01664 0.00927 -0.0740 0.5198 1.0000
5.750 0.9325 0.01707 0.00964 -0.0725 0.4874 1.0000
6.000 0.9530 0.01754 0.01004 -0.0709 0.4546 1.0000
6.250 0.9729 0.01806 0.01050 -0.0693 0.4216 1.0000
6.500 0.9921 0.01865 0.01096 -0.0676 0.3886 1.0000
6.750 1.0100 0.01927 0.01153 -0.0658 0.3538 1.0000
7.000 1.0272 0.01997 0.01213 -0.0639 0.3192 1.0000
7.250 1.0434 0.02079 0.01281 -0.0620 0.2852 1.0000
7.500 1.0588 0.02168 0.01363 -0.0599 0.2501 1.0000
7.750 1.0731 0.02272 0.01453 -0.0578 0.2170 1.0000
8.000 1.0867 0.02393 0.01556 -0.0557 0.1864 1.0000
8.250 1.0999 0.02525 0.01675 -0.0536 0.1583 1.0000
8.500 1.1121 0.02659 0.01802 -0.0513 0.1327 1.0000
8.750 1.1229 0.02801 0.01939 -0.0490 0.1100 1.0000
9.000 1.1324 0.02956 0.02085 -0.0467 0.0912 1.0000
9.250 1.1440 0.03165 0.02289 -0.0445 0.0753 1.0000
9.500 1.1573 0.03382 0.02503 -0.0427 0.0635 1.0000
9.750 1.1716 0.03569 0.02704 -0.0409 0.0558 1.0000
10.000 1.1956 0.03903 0.03051 -0.0406 0.0509 1.0000
10.250 1.2117 0.04149 0.03327 -0.0391 0.0474 1.0000
10.500 1.2248 0.04371 0.03558 -0.0377 0.0443 1.0000
10.750 1.2386 0.04788 0.03996 -0.0368 0.0420 1.0000
11.000 1.2400 0.05067 0.04318 -0.0339 0.0413 1.0000
11.250 1.2361 0.05377 0.04667 -0.0306 0.0409 1.0000
11.500 1.2278 0.05704 0.05030 -0.0273 0.0407 1.0000
11.750 1.2158 0.06049 0.05407 -0.0244 0.0407 1.0000
12.000 1.2008 0.06419 0.05808 -0.0220 0.0407 1.0000
12.250 1.1829 0.06828 0.06245 -0.0204 0.0408 1.0000
12.500 1.1637 0.07278 0.06720 -0.0197 0.0410 1.0000
12.750 1.1428 0.07782 0.07247 -0.0201 0.0412 1.0000
13.000 1.1217 0.08341 0.07826 -0.0216 0.0414 1.0000
13.250 1.0994 0.08971 0.08475 -0.0241 0.0417 1.0000
13.500 1.0772 0.09672 0.09191 -0.0276 0.0420 1.0000
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Polar data table (+)
Polar graphs
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