RG-15 8.9% (rg15-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: RG-15 8.9% (rg15-il) Reynolds number: 200,000 Max Cl/Cd: 63.25 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-rg15-il-200000-n5.txt Download as CSV file: xf-rg15-il-200000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.4977 0.08502 0.08145 -0.0286 1.0000 0.0123
-9.000 -0.5164 0.07610 0.07265 -0.0333 1.0000 0.0116
-8.500 -0.5443 0.06145 0.05806 -0.0428 1.0000 0.0110
-8.250 -0.5596 0.05578 0.05230 -0.0448 1.0000 0.0109
-8.000 -0.5724 0.05027 0.04661 -0.0454 1.0000 0.0108
-7.750 -0.5805 0.04519 0.04129 -0.0450 1.0000 0.0107
-7.500 -0.5844 0.04013 0.03585 -0.0440 1.0000 0.0107
-7.250 -0.5818 0.03580 0.03110 -0.0428 1.0000 0.0107
-7.000 -0.5747 0.03170 0.02646 -0.0413 1.0000 0.0109
-6.750 -0.5621 0.02866 0.02292 -0.0399 1.0000 0.0110
-6.500 -0.5485 0.02536 0.01919 -0.0386 1.0000 0.0114
-6.250 -0.5308 0.02349 0.01705 -0.0375 1.0000 0.0120
-6.000 -0.5114 0.02208 0.01541 -0.0365 1.0000 0.0126
-5.750 -0.4910 0.02094 0.01408 -0.0355 1.0000 0.0138
-5.500 -0.4590 0.01997 0.01285 -0.0366 0.9974 0.0160
-5.250 -0.4259 0.01844 0.01106 -0.0379 0.9946 0.0171
-5.000 -0.3949 0.01691 0.00943 -0.0390 0.9912 0.0191
-4.750 -0.3618 0.01605 0.00844 -0.0404 0.9873 0.0217
-4.500 -0.3271 0.01539 0.00766 -0.0420 0.9838 0.0253
-4.250 -0.2956 0.01450 0.00672 -0.0431 0.9791 0.0286
-4.000 -0.2624 0.01400 0.00615 -0.0443 0.9742 0.0338
-3.750 -0.2271 0.01334 0.00545 -0.0461 0.9704 0.0406
-3.500 -0.1964 0.01281 0.00491 -0.0468 0.9639 0.0547
-3.250 -0.1622 0.01226 0.00447 -0.0483 0.9589 0.0903
-3.000 -0.1299 0.01171 0.00414 -0.0496 0.9530 0.1480
-2.750 -0.0978 0.01106 0.00386 -0.0509 0.9467 0.2388
-2.500 -0.0649 0.01023 0.00361 -0.0526 0.9416 0.3851
-2.250 -0.0356 0.00961 0.00344 -0.0530 0.9336 0.5098
-2.000 -0.0043 0.00923 0.00343 -0.0535 0.9268 0.6263
-1.750 0.0267 0.00906 0.00336 -0.0538 0.9181 0.6848
-1.500 0.0577 0.00894 0.00328 -0.0541 0.9085 0.7219
-1.250 0.0904 0.00883 0.00316 -0.0547 0.8992 0.7506
-1.000 0.1220 0.00873 0.00306 -0.0551 0.8883 0.7754
-0.750 0.1521 0.00865 0.00298 -0.0551 0.8755 0.7968
-0.250 0.2110 0.00853 0.00282 -0.0549 0.8466 0.8345
0.000 0.2385 0.00849 0.00276 -0.0544 0.8302 0.8527
0.250 0.2652 0.00847 0.00271 -0.0537 0.8123 0.8711
0.500 0.2917 0.00846 0.00266 -0.0530 0.7936 0.8890
0.750 0.3191 0.00846 0.00261 -0.0524 0.7742 0.9071
1.000 0.3478 0.00849 0.00258 -0.0523 0.7531 0.9248
1.250 0.3788 0.00854 0.00256 -0.0527 0.7313 0.9411
1.500 0.4118 0.00861 0.00254 -0.0536 0.7079 0.9565
1.750 0.4465 0.00870 0.00254 -0.0550 0.6829 0.9722
2.000 0.4812 0.00881 0.00257 -0.0565 0.6567 0.9910
2.250 0.5085 0.00897 0.00262 -0.0565 0.6308 1.0000
2.500 0.5322 0.00917 0.00270 -0.0557 0.6046 1.0000
2.750 0.5562 0.00938 0.00280 -0.0550 0.5776 1.0000
3.000 0.5803 0.00961 0.00292 -0.0543 0.5493 1.0000
3.250 0.6045 0.00986 0.00309 -0.0536 0.5203 1.0000
3.500 0.6287 0.01013 0.00325 -0.0529 0.4905 1.0000
3.750 0.6528 0.01042 0.00344 -0.0522 0.4599 1.0000
4.000 0.6767 0.01074 0.00365 -0.0515 0.4285 1.0000
4.250 0.7004 0.01109 0.00392 -0.0508 0.3958 1.0000
4.500 0.7242 0.01145 0.00418 -0.0501 0.3628 1.0000
4.750 0.7478 0.01184 0.00447 -0.0495 0.3302 1.0000
5.000 0.7713 0.01227 0.00480 -0.0488 0.2971 1.0000
5.250 0.7945 0.01273 0.00515 -0.0481 0.2621 1.0000
5.500 0.8173 0.01326 0.00558 -0.0474 0.2252 1.0000
5.750 0.8399 0.01382 0.00601 -0.0467 0.1910 1.0000
6.000 0.8626 0.01439 0.00649 -0.0460 0.1612 1.0000
6.250 0.8851 0.01500 0.00701 -0.0453 0.1332 1.0000
6.500 0.9074 0.01564 0.00757 -0.0446 0.1094 1.0000
6.750 0.9298 0.01626 0.00818 -0.0438 0.0900 1.0000
7.000 0.9513 0.01698 0.00888 -0.0430 0.0719 1.0000
7.250 0.9725 0.01772 0.00956 -0.0422 0.0536 1.0000
7.500 0.9933 0.01851 0.01027 -0.0413 0.0381 1.0000
7.750 1.0141 0.01928 0.01107 -0.0404 0.0290 1.0000
8.000 1.0338 0.02021 0.01206 -0.0392 0.0217 1.0000
8.250 1.0513 0.02137 0.01327 -0.0378 0.0168 1.0000
8.500 1.0694 0.02242 0.01447 -0.0364 0.0144 1.0000
8.750 1.0863 0.02354 0.01572 -0.0350 0.0126 1.0000
9.000 1.1018 0.02476 0.01707 -0.0334 0.0113 1.0000
9.250 1.1178 0.02589 0.01836 -0.0319 0.0101 1.0000
9.500 1.1318 0.02718 0.01980 -0.0302 0.0095 1.0000
9.750 1.1443 0.02854 0.02131 -0.0284 0.0090 1.0000
10.000 1.1548 0.03005 0.02297 -0.0264 0.0086 1.0000
10.250 1.1615 0.03169 0.02475 -0.0239 0.0083 1.0000
10.500 1.1644 0.03371 0.02694 -0.0211 0.0080 1.0000
10.750 1.1663 0.03594 0.02934 -0.0185 0.0078 1.0000
11.000 1.1693 0.03803 0.03166 -0.0162 0.0077 1.0000
11.250 1.1698 0.04037 0.03425 -0.0140 0.0076 1.0000
11.750 1.1639 0.04583 0.04023 -0.0107 0.0075 1.0000
12.000 1.1566 0.04919 0.04385 -0.0097 0.0074 1.0000
12.250 1.1470 0.05302 0.04794 -0.0095 0.0073 1.0000
12.500 1.1353 0.05739 0.05255 -0.0101 0.0073 1.0000
12.750 1.1225 0.06227 0.05767 -0.0116 0.0073 1.0000
13.000 1.1078 0.06793 0.06355 -0.0142 0.0073 1.0000
13.250 1.0915 0.07438 0.07021 -0.0177 0.0073 1.0000
13.500 1.0754 0.08135 0.07737 -0.0219 0.0073 1.0000
13.750 1.0576 0.08924 0.08544 -0.0270 0.0074 1.0000
14.000 1.0380 0.09823 0.09459 -0.0328 0.0074 1.0000
14.250 1.0186 0.10776 0.10427 -0.0390 0.0075 1.0000
14.500 1.0005 0.11750 0.11409 -0.0450 0.0076 1.0000
14.750 0.9790 0.12882 0.12550 -0.0518 0.0077 1.0000
15.000 0.9567 0.14106 0.13780 -0.0587 0.0078 1.0000
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Polar data table (+)
Polar graphs
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