RG-15 8.9% (rg15-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: RG-15 8.9% (rg15-il) Reynolds number: 100,000 Max Cl/Cd: 52.06 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-rg15-il-100000.txt Download as CSV file: xf-rg15-il-100000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.4676 0.10268 0.09767 -0.0221 1.0000 0.0962
-9.000 -0.4828 0.09964 0.09475 -0.0268 1.0000 0.0985
-8.750 -0.5052 0.09647 0.09172 -0.0324 1.0000 0.0991
-8.500 -0.4662 0.09231 0.08746 -0.0244 1.0000 0.1069
-8.250 -0.4759 0.08900 0.08426 -0.0269 1.0000 0.1107
-8.000 -0.5005 0.08558 0.08099 -0.0314 1.0000 0.1121
-7.750 -0.4814 0.08225 0.07766 -0.0268 1.0000 0.1186
-7.500 -0.4928 0.07871 0.07421 -0.0294 1.0000 0.1236
-7.250 -0.5140 0.07419 0.06964 -0.0365 1.0000 0.1261
-7.000 -0.4618 0.05934 0.05521 -0.0349 1.0000 0.1416
-6.750 -0.4403 0.05644 0.05235 -0.0300 1.0000 0.1469
-6.500 -0.4701 0.05165 0.04747 -0.0345 1.0000 0.1553
-6.250 -0.5035 0.05976 0.05519 -0.0351 1.0000 0.1567
-5.750 -0.4901 0.05388 0.04910 -0.0342 1.0000 0.1812
-5.500 -0.4669 0.03684 0.03036 -0.0392 1.0000 0.0680
-5.250 -0.4460 0.03277 0.02515 -0.0376 1.0000 0.0594
-5.000 -0.4258 0.02938 0.02129 -0.0365 1.0000 0.0590
-4.750 -0.4062 0.02647 0.01828 -0.0359 1.0000 0.0637
-4.500 -0.3836 0.02456 0.01606 -0.0349 1.0000 0.0674
-4.250 -0.3593 0.02264 0.01375 -0.0337 1.0000 0.0699
-4.000 -0.3363 0.02100 0.01200 -0.0328 1.0000 0.0767
-3.750 -0.3127 0.01984 0.01068 -0.0317 1.0000 0.0842
-3.500 -0.2896 0.01843 0.00937 -0.0307 1.0000 0.0933
-3.250 -0.2667 0.01735 0.00833 -0.0297 1.0000 0.1135
-3.000 -0.2440 0.01578 0.00725 -0.0290 1.0000 0.1829
-2.750 -0.2255 0.01350 0.00681 -0.0282 1.0000 0.4973
-2.500 -0.2179 0.01316 0.00729 -0.0228 1.0000 0.7251
-2.250 -0.2094 0.01321 0.00745 -0.0178 1.0000 0.8072
-2.000 -0.2016 0.01322 0.00750 -0.0127 1.0000 0.8695
-1.750 -0.1734 0.01323 0.00746 -0.0116 1.0000 0.9472
-1.500 -0.1216 0.01323 0.00716 -0.0170 1.0000 1.0000
-1.250 -0.1067 0.01324 0.00699 -0.0163 1.0000 1.0000
-1.000 -0.0872 0.01338 0.00695 -0.0163 1.0000 1.0000
-0.750 -0.0665 0.01361 0.00701 -0.0163 1.0000 1.0000
-0.500 -0.0268 0.01408 0.00727 -0.0198 0.9941 1.0000
-0.250 0.0247 0.01456 0.00759 -0.0253 0.9834 1.0000
0.000 0.0736 0.01491 0.00782 -0.0302 0.9717 1.0000
0.250 0.1214 0.01517 0.00797 -0.0346 0.9595 1.0000
0.500 0.1683 0.01534 0.00807 -0.0388 0.9469 1.0000
0.750 0.2149 0.01543 0.00812 -0.0427 0.9342 1.0000
1.000 0.2616 0.01544 0.00811 -0.0464 0.9214 1.0000
1.250 0.3089 0.01536 0.00804 -0.0501 0.9087 1.0000
1.500 0.3588 0.01514 0.00786 -0.0540 0.8966 1.0000
1.750 0.4059 0.01487 0.00763 -0.0572 0.8835 1.0000
2.000 0.4482 0.01459 0.00740 -0.0593 0.8682 1.0000
2.250 0.4879 0.01430 0.00719 -0.0607 0.8513 1.0000
2.500 0.5262 0.01402 0.00695 -0.0618 0.8334 1.0000
2.750 0.5571 0.01388 0.00683 -0.0615 0.8110 1.0000
3.000 0.5891 0.01373 0.00669 -0.0613 0.7887 1.0000
3.250 0.6168 0.01370 0.00669 -0.0604 0.7628 1.0000
3.500 0.6432 0.01374 0.00671 -0.0593 0.7351 1.0000
3.750 0.6689 0.01383 0.00676 -0.0581 0.7060 1.0000
4.000 0.6930 0.01399 0.00689 -0.0568 0.6742 1.0000
4.250 0.7168 0.01419 0.00708 -0.0554 0.6411 1.0000
4.500 0.7406 0.01444 0.00723 -0.0540 0.6075 1.0000
4.750 0.7629 0.01474 0.00749 -0.0525 0.5703 1.0000
5.000 0.7850 0.01509 0.00775 -0.0510 0.5321 1.0000
5.250 0.8064 0.01549 0.00806 -0.0494 0.4922 1.0000
5.500 0.8271 0.01596 0.00847 -0.0478 0.4497 1.0000
5.750 0.8469 0.01650 0.00890 -0.0461 0.4043 1.0000
6.000 0.8657 0.01716 0.00938 -0.0444 0.3567 1.0000
6.250 0.8835 0.01794 0.00999 -0.0427 0.3049 1.0000
6.500 0.9004 0.01893 0.01073 -0.0409 0.2535 1.0000
6.750 0.9170 0.02013 0.01169 -0.0392 0.2065 1.0000
7.000 0.9336 0.02151 0.01284 -0.0375 0.1669 1.0000
7.250 0.9509 0.02304 0.01423 -0.0359 0.1371 1.0000
7.500 0.9690 0.02460 0.01573 -0.0344 0.1126 1.0000
7.750 0.9869 0.02638 0.01745 -0.0331 0.0923 1.0000
8.000 1.0037 0.02797 0.01907 -0.0315 0.0737 1.0000
8.250 1.0217 0.03013 0.02124 -0.0301 0.0601 1.0000
8.500 1.0404 0.03245 0.02375 -0.0288 0.0508 1.0000
8.750 1.0609 0.03593 0.02723 -0.0281 0.0456 1.0000
9.000 1.0781 0.03889 0.03073 -0.0263 0.0436 1.0000
9.250 1.0906 0.04239 0.03480 -0.0242 0.0423 1.0000
9.500 1.0978 0.04624 0.03917 -0.0219 0.0418 1.0000
9.750 1.0995 0.05026 0.04367 -0.0194 0.0417 1.0000
10.000 1.0956 0.05430 0.04815 -0.0167 0.0415 1.0000
10.250 1.0864 0.05830 0.05254 -0.0141 0.0416 1.0000
10.500 1.0711 0.06206 0.05660 -0.0113 0.0417 1.0000
10.750 1.0517 0.06595 0.06073 -0.0090 0.0422 1.0000
11.000 1.0304 0.07017 0.06516 -0.0080 0.0425 1.0000
11.250 1.0084 0.07511 0.07028 -0.0087 0.0431 1.0000
11.500 0.9878 0.08074 0.07604 -0.0109 0.0439 1.0000
11.750 0.9681 0.08709 0.08249 -0.0142 0.0446 1.0000
12.000 0.9479 0.09440 0.08988 -0.0187 0.0451 1.0000
12.250 0.9385 0.10144 0.09692 -0.0214 0.0459 1.0000
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Polar data table (+)
Polar graphs
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