RG-15 8.9% (rg15-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: RG-15 8.9% (rg15-il) Reynolds number: 200,000 Max Cl/Cd: 68.75 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-rg15-il-200000.txt Download as CSV file: xf-rg15-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: RG-15 8.9%
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.4922 0.08612 0.08270 -0.0383 1.0000 0.0465
-8.500 -0.5059 0.08177 0.07836 -0.0415 1.0000 0.0466
-8.250 -0.5165 0.07774 0.07428 -0.0434 1.0000 0.0466
-8.000 -0.5200 0.07136 0.06803 -0.0423 1.0000 0.0479
-7.750 -0.5148 0.06906 0.06578 -0.0403 1.0000 0.0490
-7.500 -0.5140 0.06614 0.06286 -0.0398 1.0000 0.0502
-7.250 -0.5150 0.06263 0.05932 -0.0402 1.0000 0.0512
-7.000 -0.5157 0.05887 0.05549 -0.0405 1.0000 0.0531
-6.750 -0.5150 0.05491 0.05138 -0.0408 1.0000 0.0554
-6.500 -0.5228 0.04987 0.04564 -0.0415 1.0000 0.0601
-6.250 -0.5121 0.04601 0.04192 -0.0405 1.0000 0.0616
-6.000 -0.5010 0.04339 0.03929 -0.0392 1.0000 0.0635
-5.750 -0.4887 0.03212 0.02678 -0.0372 1.0000 0.0333
-5.500 -0.4734 0.02778 0.02198 -0.0361 1.0000 0.0312
-5.250 -0.4539 0.02449 0.01819 -0.0348 1.0000 0.0305
-5.000 -0.4326 0.02292 0.01625 -0.0336 1.0000 0.0331
-4.750 -0.4101 0.02133 0.01424 -0.0324 1.0000 0.0344
-4.500 -0.3867 0.01906 0.01164 -0.0314 1.0000 0.0355
-4.250 -0.3635 0.01719 0.00969 -0.0307 1.0000 0.0384
-4.000 -0.3410 0.01664 0.00908 -0.0299 1.0000 0.0440
-3.750 -0.3179 0.01572 0.00805 -0.0289 1.0000 0.0474
-3.500 -0.2955 0.01481 0.00719 -0.0283 1.0000 0.0540
-3.250 -0.2729 0.01414 0.00648 -0.0275 1.0000 0.0615
-3.000 -0.2438 0.01334 0.00576 -0.0281 0.9985 0.0841
-2.750 -0.2048 0.01208 0.00527 -0.0313 0.9944 0.2364
-2.500 -0.1690 0.01099 0.00516 -0.0339 0.9890 0.4661
-2.250 -0.1341 0.01055 0.00554 -0.0351 0.9834 0.6904
-2.000 -0.1010 0.01050 0.00563 -0.0356 0.9754 0.7624
-1.750 -0.0620 0.01053 0.00566 -0.0374 0.9697 0.8055
-1.500 -0.0312 0.01044 0.00559 -0.0374 0.9603 0.8406
-1.250 0.0020 0.01037 0.00551 -0.0378 0.9525 0.8722
-1.000 0.0366 0.01024 0.00536 -0.0385 0.9451 0.8989
-0.750 0.0702 0.01011 0.00522 -0.0390 0.9368 0.9246
-0.500 0.1164 0.00997 0.00504 -0.0421 0.9319 0.9473
-0.250 0.1719 0.00982 0.00483 -0.0473 0.9293 0.9631
0.000 0.2226 0.00968 0.00465 -0.0517 0.9216 0.9772
0.250 0.2798 0.00945 0.00439 -0.0574 0.9166 0.9856
0.500 0.3320 0.00924 0.00415 -0.0623 0.9066 0.9944
0.750 0.3788 0.00899 0.00388 -0.0661 0.8939 1.0000
1.000 0.4087 0.00878 0.00364 -0.0665 0.8761 1.0000
1.250 0.4333 0.00866 0.00347 -0.0658 0.8558 1.0000
1.500 0.4560 0.00861 0.00334 -0.0647 0.8344 1.0000
1.750 0.4779 0.00861 0.00328 -0.0634 0.8119 1.0000
2.000 0.5015 0.00866 0.00325 -0.0624 0.7895 1.0000
2.250 0.5245 0.00876 0.00326 -0.0612 0.7649 1.0000
2.500 0.5485 0.00887 0.00329 -0.0603 0.7396 1.0000
2.750 0.5727 0.00902 0.00334 -0.0593 0.7134 1.0000
3.000 0.5969 0.00919 0.00345 -0.0584 0.6860 1.0000
3.250 0.6211 0.00939 0.00355 -0.0575 0.6575 1.0000
3.500 0.6450 0.00961 0.00367 -0.0566 0.6278 1.0000
3.750 0.6689 0.00986 0.00382 -0.0556 0.5972 1.0000
4.000 0.6925 0.01013 0.00398 -0.0547 0.5655 1.0000
4.250 0.7159 0.01042 0.00422 -0.0537 0.5315 1.0000
4.500 0.7391 0.01075 0.00444 -0.0528 0.4972 1.0000
4.750 0.7621 0.01110 0.00469 -0.0518 0.4617 1.0000
5.000 0.7847 0.01150 0.00498 -0.0508 0.4247 1.0000
5.250 0.8070 0.01193 0.00529 -0.0498 0.3849 1.0000
5.500 0.8289 0.01242 0.00568 -0.0488 0.3425 1.0000
5.750 0.8504 0.01297 0.00608 -0.0478 0.2997 1.0000
6.000 0.8719 0.01358 0.00654 -0.0468 0.2560 1.0000
6.250 0.8927 0.01428 0.00708 -0.0458 0.2105 1.0000
6.500 0.9129 0.01510 0.00772 -0.0448 0.1681 1.0000
6.750 0.9323 0.01606 0.00848 -0.0436 0.1320 1.0000
7.000 0.9515 0.01706 0.00940 -0.0423 0.1026 1.0000
7.250 0.9712 0.01798 0.01021 -0.0413 0.0787 1.0000
7.500 0.9909 0.01890 0.01105 -0.0402 0.0595 1.0000
7.750 1.0078 0.02021 0.01237 -0.0386 0.0436 1.0000
8.000 1.0218 0.02195 0.01415 -0.0364 0.0326 1.0000
8.250 1.0382 0.02343 0.01570 -0.0346 0.0277 1.0000
8.500 1.0510 0.02615 0.01848 -0.0326 0.0246 1.0000
8.750 1.0709 0.02719 0.01972 -0.0313 0.0222 1.0000
9.000 1.0890 0.02899 0.02173 -0.0300 0.0208 1.0000
9.250 1.1063 0.03102 0.02395 -0.0286 0.0198 1.0000
9.500 1.1220 0.03330 0.02645 -0.0271 0.0191 1.0000
9.750 1.1353 0.03593 0.02933 -0.0255 0.0186 1.0000
10.000 1.1450 0.03899 0.03272 -0.0236 0.0184 1.0000
10.250 1.1498 0.04228 0.03639 -0.0212 0.0184 1.0000
10.500 1.1480 0.04588 0.04041 -0.0183 0.0187 1.0000
10.750 1.1366 0.04981 0.04476 -0.0145 0.0192 1.0000
11.000 1.1139 0.05396 0.04932 -0.0107 0.0197 1.0000
11.250 1.0898 0.05842 0.05411 -0.0084 0.0202 1.0000
11.500 1.0663 0.06327 0.05923 -0.0080 0.0206 1.0000
11.750 1.0435 0.06862 0.06481 -0.0093 0.0209 1.0000
12.000 1.0199 0.07489 0.07127 -0.0124 0.0211 1.0000
12.250 0.9950 0.08247 0.07904 -0.0173 0.0214 1.0000
12.500 0.9698 0.09151 0.08822 -0.0240 0.0216 1.0000
12.750 0.9423 0.10283 0.09966 -0.0324 0.0219 1.0000
13.000 0.9109 0.11744 0.11432 -0.0418 0.0227 1.0000
13.250 0.8896 0.12970 0.12651 -0.0482 0.0237 1.0000
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Polar data table (+)
Polar graphs
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