RG 8 AIRFOIL (rg8-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: RG 8 AIRFOIL (rg8-il) Reynolds number: 50,000 Max Cl/Cd: 37.8 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-rg8-il-50000-n5.txt Download as CSV file: xf-rg8-il-50000-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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.4860 0.09620 0.08895 -0.0426 1.0000 0.0499
-9.750 -0.4891 0.09169 0.08450 -0.0438 1.0000 0.0496
-9.500 -0.4947 0.08679 0.07967 -0.0456 1.0000 0.0492
-9.250 -0.5045 0.08143 0.07438 -0.0479 1.0000 0.0489
-9.000 -0.5184 0.07655 0.06956 -0.0499 1.0000 0.0485
-8.750 -0.5384 0.07215 0.06522 -0.0511 1.0000 0.0481
-8.500 -0.5552 0.06777 0.06084 -0.0521 1.0000 0.0478
-8.250 -0.5689 0.06349 0.05647 -0.0525 1.0000 0.0475
-8.000 -0.5790 0.05924 0.05205 -0.0526 1.0000 0.0474
-7.750 -0.5845 0.05500 0.04754 -0.0523 1.0000 0.0474
-7.500 -0.5845 0.05096 0.04318 -0.0520 1.0000 0.0475
-7.250 -0.5798 0.04706 0.03886 -0.0515 1.0000 0.0478
-7.000 -0.5705 0.04342 0.03473 -0.0509 1.0000 0.0483
-6.750 -0.5570 0.04021 0.03101 -0.0502 1.0000 0.0491
-6.500 -0.5413 0.03756 0.02804 -0.0495 1.0000 0.0510
-6.250 -0.5241 0.03583 0.02616 -0.0487 1.0000 0.0543
-6.000 -0.5051 0.03391 0.02395 -0.0478 1.0000 0.0576
-5.750 -0.4844 0.03192 0.02158 -0.0468 1.0000 0.0605
-5.500 -0.4638 0.03016 0.01960 -0.0455 1.0000 0.0635
-5.250 -0.4440 0.02879 0.01820 -0.0443 1.0000 0.0678
-5.000 -0.4232 0.02756 0.01675 -0.0430 1.0000 0.0758
-4.750 -0.4029 0.02646 0.01557 -0.0421 1.0000 0.0882
-4.500 -0.3824 0.02529 0.01450 -0.0414 1.0000 0.1065
-4.250 -0.3610 0.02423 0.01357 -0.0410 1.0000 0.1411
-4.000 -0.3391 0.02316 0.01271 -0.0408 1.0000 0.1882
-3.750 -0.3164 0.02210 0.01192 -0.0409 1.0000 0.2466
-3.500 -0.2938 0.02112 0.01138 -0.0408 1.0000 0.3302
-3.250 -0.2747 0.02053 0.01139 -0.0394 1.0000 0.4404
-3.000 -0.2567 0.02051 0.01156 -0.0373 1.0000 0.5345
-2.750 -0.2387 0.02062 0.01166 -0.0352 1.0000 0.5953
-2.500 -0.2217 0.02074 0.01175 -0.0329 1.0000 0.6404
-2.250 -0.2056 0.02087 0.01183 -0.0304 1.0000 0.6781
-2.000 -0.1832 0.02107 0.01195 -0.0292 0.9962 0.7144
-1.750 -0.1526 0.02132 0.01212 -0.0294 0.9870 0.7495
-1.500 -0.1227 0.02150 0.01221 -0.0295 0.9775 0.7821
-1.250 -0.0927 0.02161 0.01222 -0.0296 0.9679 0.8132
-1.000 -0.0620 0.02166 0.01221 -0.0298 0.9583 0.8434
-0.750 -0.0328 0.02159 0.01210 -0.0299 0.9475 0.8731
-0.500 0.0025 0.02153 0.01196 -0.0312 0.9373 0.9037
-0.250 0.0504 0.02152 0.01186 -0.0353 0.9288 0.9344
0.000 0.1032 0.02148 0.01173 -0.0408 0.9191 0.9678
0.250 0.1459 0.02141 0.01154 -0.0447 0.9070 1.0000
0.500 0.1823 0.02143 0.01145 -0.0473 0.8949 1.0000
0.750 0.2202 0.02146 0.01137 -0.0499 0.8831 1.0000
1.000 0.2604 0.02146 0.01129 -0.0527 0.8720 1.0000
1.250 0.3002 0.02143 0.01120 -0.0553 0.8606 1.0000
1.500 0.3363 0.02141 0.01115 -0.0570 0.8475 1.0000
2.000 0.4095 0.02135 0.01107 -0.0603 0.8207 1.0000
2.250 0.4454 0.02130 0.01104 -0.0617 0.8065 1.0000
2.500 0.4810 0.02124 0.01100 -0.0629 0.7918 1.0000
2.750 0.5166 0.02117 0.01096 -0.0639 0.7764 1.0000
3.000 0.5521 0.02108 0.01093 -0.0649 0.7604 1.0000
3.250 0.5847 0.02107 0.01096 -0.0653 0.7423 1.0000
3.500 0.6157 0.02110 0.01103 -0.0655 0.7226 1.0000
3.750 0.6494 0.02107 0.01108 -0.0659 0.7031 1.0000
4.000 0.6788 0.02117 0.01122 -0.0657 0.6811 1.0000
4.250 0.7101 0.02124 0.01131 -0.0658 0.6591 1.0000
4.500 0.7373 0.02143 0.01155 -0.0652 0.6346 1.0000
4.750 0.7651 0.02164 0.01182 -0.0647 0.6098 1.0000
5.000 0.7925 0.02188 0.01207 -0.0641 0.5842 1.0000
5.250 0.8178 0.02219 0.01240 -0.0633 0.5573 1.0000
5.500 0.8418 0.02258 0.01281 -0.0623 0.5295 1.0000
5.750 0.8650 0.02301 0.01330 -0.0612 0.5011 1.0000
6.000 0.8873 0.02350 0.01379 -0.0599 0.4722 1.0000
6.250 0.9086 0.02404 0.01433 -0.0586 0.4430 1.0000
6.500 0.9289 0.02464 0.01493 -0.0572 0.4133 1.0000
6.750 0.9480 0.02531 0.01558 -0.0556 0.3834 1.0000
7.000 0.9661 0.02605 0.01635 -0.0540 0.3533 1.0000
7.250 0.9830 0.02687 0.01717 -0.0523 0.3232 1.0000
7.500 0.9989 0.02777 0.01807 -0.0506 0.2935 1.0000
7.750 1.0137 0.02876 0.01904 -0.0487 0.2645 1.0000
8.000 1.0276 0.02986 0.02011 -0.0468 0.2370 1.0000
8.250 1.0399 0.03106 0.02126 -0.0449 0.2110 1.0000
8.500 1.0521 0.03237 0.02261 -0.0430 0.1860 1.0000
8.750 1.0631 0.03382 0.02410 -0.0410 0.1639 1.0000
9.000 1.0723 0.03534 0.02562 -0.0389 0.1447 1.0000
9.250 1.0800 0.03699 0.02723 -0.0367 0.1284 1.0000
9.500 1.0880 0.03879 0.02905 -0.0346 0.1135 1.0000
9.750 1.0945 0.04070 0.03101 -0.0325 0.1000 1.0000
10.000 1.0995 0.04272 0.03307 -0.0305 0.0886 1.0000
10.250 1.1040 0.04487 0.03538 -0.0286 0.0777 1.0000
10.500 1.1078 0.04723 0.03791 -0.0268 0.0687 1.0000
10.750 1.1088 0.04967 0.04032 -0.0253 0.0622 1.0000
11.000 1.1116 0.05234 0.04330 -0.0239 0.0558 1.0000
11.250 1.1121 0.05500 0.04596 -0.0228 0.0518 1.0000
11.500 1.1154 0.05836 0.04973 -0.0217 0.0481 1.0000
11.750 1.1147 0.06174 0.05338 -0.0210 0.0453 1.0000
12.000 1.1116 0.06508 0.05686 -0.0206 0.0431 1.0000
12.250 1.1100 0.06845 0.06025 -0.0205 0.0412 1.0000
12.500 1.1007 0.07311 0.06523 -0.0211 0.0400 1.0000
12.750 1.0880 0.07838 0.07084 -0.0224 0.0393 1.0000
13.000 1.0728 0.08429 0.07704 -0.0246 0.0388 1.0000
13.250 1.0555 0.09092 0.08393 -0.0277 0.0387 1.0000
13.500 1.0361 0.09845 0.09168 -0.0318 0.0388 1.0000
13.750 1.0160 0.10674 0.10017 -0.0367 0.0392 1.0000
14.000 0.9947 0.11605 0.10964 -0.0424 0.0396 1.0000
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Polar data table (+)
Polar graphs
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