RG-15 8.9% (rg15-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: RG-15 8.9% (rg15-il) Reynolds number: 100,000 Max Cl/Cd: 50.54 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-rg15-il-100000-n5.txt Download as CSV file: xf-rg15-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.4836 0.09107 0.08599 -0.0275 1.0000 0.0221
-9.000 -0.4865 0.08666 0.08164 -0.0294 1.0000 0.0219
-8.750 -0.4913 0.08202 0.07707 -0.0316 1.0000 0.0216
-8.500 -0.4982 0.07721 0.07235 -0.0340 1.0000 0.0213
-8.250 -0.5101 0.07189 0.06712 -0.0373 1.0000 0.0208
-8.000 -0.5230 0.06614 0.06138 -0.0409 1.0000 0.0206
-7.750 -0.5326 0.06065 0.05581 -0.0428 1.0000 0.0202
-7.500 -0.5389 0.05561 0.05063 -0.0437 1.0000 0.0204
-7.250 -0.5415 0.05082 0.04562 -0.0438 1.0000 0.0203
-7.000 -0.5396 0.04656 0.04106 -0.0435 1.0000 0.0214
-6.750 -0.5344 0.04236 0.03648 -0.0428 1.0000 0.0221
-6.500 -0.5256 0.03832 0.03195 -0.0418 1.0000 0.0230
-6.250 -0.5132 0.03468 0.02779 -0.0407 1.0000 0.0234
-6.000 -0.4976 0.03143 0.02400 -0.0395 1.0000 0.0238
-5.750 -0.4792 0.02874 0.02077 -0.0382 1.0000 0.0245
-5.500 -0.4600 0.02608 0.01773 -0.0371 1.0000 0.0254
-5.250 -0.4400 0.02433 0.01584 -0.0362 1.0000 0.0272
-5.000 -0.4190 0.02331 0.01464 -0.0353 1.0000 0.0310
-4.750 -0.3969 0.02193 0.01294 -0.0342 1.0000 0.0337
-4.500 -0.3752 0.02046 0.01133 -0.0331 1.0000 0.0359
-4.250 -0.3539 0.01959 0.01047 -0.0322 1.0000 0.0410
-4.000 -0.3319 0.01877 0.00949 -0.0312 1.0000 0.0457
-3.750 -0.3100 0.01782 0.00852 -0.0304 1.0000 0.0507
-3.500 -0.2874 0.01718 0.00777 -0.0296 1.0000 0.0593
-3.250 -0.2595 0.01643 0.00715 -0.0301 0.9979 0.0832
-3.000 -0.2238 0.01562 0.00658 -0.0322 0.9925 0.1422
-2.750 -0.1901 0.01461 0.00628 -0.0344 0.9865 0.2852
-2.250 -0.1287 0.01325 0.00630 -0.0357 0.9728 0.6462
-2.000 -0.0983 0.01316 0.00631 -0.0356 0.9644 0.7246
-1.750 -0.0653 0.01312 0.00624 -0.0360 0.9569 0.7773
-1.500 -0.0367 0.01305 0.00615 -0.0356 0.9471 0.8173
-1.250 -0.0060 0.01297 0.00604 -0.0355 0.9383 0.8528
-1.000 0.0286 0.01288 0.00589 -0.0362 0.9306 0.8869
-0.750 0.0651 0.01278 0.00575 -0.0374 0.9218 0.9182
-0.500 0.1143 0.01268 0.00557 -0.0413 0.9162 0.9462
-0.250 0.1627 0.01257 0.00538 -0.0454 0.9072 0.9714
0.000 0.2142 0.01242 0.00516 -0.0502 0.8989 0.9916
0.250 0.2550 0.01229 0.00496 -0.0529 0.8875 1.0000
0.500 0.2858 0.01219 0.00479 -0.0536 0.8723 1.0000
0.750 0.3162 0.01212 0.00466 -0.0541 0.8559 1.0000
1.000 0.3469 0.01207 0.00456 -0.0546 0.8389 1.0000
1.250 0.3780 0.01203 0.00448 -0.0551 0.8212 1.0000
1.500 0.4085 0.01202 0.00441 -0.0554 0.8025 1.0000
1.750 0.4367 0.01205 0.00439 -0.0553 0.7814 1.0000
2.000 0.4656 0.01210 0.00438 -0.0553 0.7602 1.0000
2.250 0.4929 0.01218 0.00444 -0.0550 0.7370 1.0000
2.500 0.5198 0.01230 0.00450 -0.0546 0.7130 1.0000
2.750 0.5463 0.01244 0.00458 -0.0541 0.6879 1.0000
3.000 0.5723 0.01261 0.00469 -0.0535 0.6618 1.0000
3.250 0.5977 0.01281 0.00486 -0.0528 0.6344 1.0000
3.500 0.6226 0.01304 0.00503 -0.0520 0.6055 1.0000
3.750 0.6472 0.01330 0.00523 -0.0512 0.5755 1.0000
4.000 0.6713 0.01359 0.00545 -0.0503 0.5443 1.0000
4.250 0.6951 0.01392 0.00575 -0.0494 0.5121 1.0000
4.500 0.7185 0.01428 0.00603 -0.0485 0.4788 1.0000
4.750 0.7416 0.01468 0.00636 -0.0476 0.4439 1.0000
5.000 0.7642 0.01512 0.00672 -0.0466 0.4081 1.0000
5.250 0.7864 0.01561 0.00712 -0.0456 0.3711 1.0000
5.500 0.8084 0.01613 0.00761 -0.0446 0.3332 1.0000
5.750 0.8299 0.01673 0.00811 -0.0436 0.2951 1.0000
6.000 0.8509 0.01739 0.00867 -0.0426 0.2556 1.0000
6.250 0.8714 0.01814 0.00929 -0.0416 0.2165 1.0000
6.500 0.8919 0.01894 0.00999 -0.0406 0.1796 1.0000
6.750 0.9117 0.01983 0.01078 -0.0396 0.1476 1.0000
7.000 0.9312 0.02079 0.01166 -0.0385 0.1213 1.0000
7.250 0.9505 0.02179 0.01270 -0.0374 0.0986 1.0000
7.500 0.9685 0.02292 0.01380 -0.0361 0.0814 1.0000
7.750 0.9865 0.02407 0.01500 -0.0348 0.0659 1.0000
8.000 1.0039 0.02526 0.01623 -0.0335 0.0518 1.0000
8.250 1.0203 0.02654 0.01755 -0.0321 0.0404 1.0000
8.500 1.0341 0.02810 0.01918 -0.0304 0.0333 1.0000
8.750 1.0491 0.02951 0.02072 -0.0289 0.0271 1.0000
9.000 1.0602 0.03138 0.02275 -0.0269 0.0237 1.0000
9.250 1.0730 0.03324 0.02486 -0.0250 0.0215 1.0000
9.500 1.0850 0.03520 0.02702 -0.0232 0.0200 1.0000
9.750 1.0957 0.03721 0.02919 -0.0214 0.0188 1.0000
10.000 1.1040 0.03947 0.03161 -0.0196 0.0179 1.0000
10.250 1.1088 0.04231 0.03465 -0.0175 0.0173 1.0000
10.500 1.1120 0.04501 0.03765 -0.0153 0.0167 1.0000
10.750 1.1119 0.04769 0.04068 -0.0130 0.0162 1.0000
11.000 1.1079 0.05051 0.04382 -0.0109 0.0155 1.0000
11.250 1.1009 0.05362 0.04723 -0.0093 0.0150 1.0000
11.500 1.0914 0.05712 0.05100 -0.0084 0.0147 1.0000
11.750 1.0794 0.06109 0.05524 -0.0083 0.0145 1.0000
12.000 1.0658 0.06553 0.05991 -0.0093 0.0142 1.0000
12.250 1.0483 0.07114 0.06578 -0.0115 0.0143 1.0000
12.500 1.0287 0.07772 0.07259 -0.0151 0.0144 1.0000
12.750 1.0074 0.08547 0.08054 -0.0200 0.0146 1.0000
13.000 0.9829 0.09487 0.09013 -0.0263 0.0152 1.0000
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Polar data table (+)
Polar graphs
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