RG 15A-1.8/11.0 AIRFOIL (rg15a111-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: RG 15A-1.8/11.0 AIRFOIL (rg15a111-il) Reynolds number: 100,000 Max Cl/Cd: 50.02 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-rg15a111-il-100000.txt Download as CSV file: xf-rg15a111-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: RG 15A-1.8/11.0 AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-9.500 -0.3649 0.09118 0.08645 -0.0308 1.0000 0.1421
-9.250 -0.3644 0.08765 0.08295 -0.0308 1.0000 0.1467
-9.000 -0.4109 0.08335 0.07884 -0.0362 1.0000 0.1519
-8.750 -0.3892 0.07891 0.07437 -0.0333 1.0000 0.1546
-8.500 -0.3830 0.07539 0.07087 -0.0322 1.0000 0.1576
-8.250 -0.3905 0.07146 0.06701 -0.0324 1.0000 0.1611
-8.000 -0.6127 0.06044 0.05501 -0.0458 1.0000 0.0816
-7.750 -0.6162 0.05150 0.04583 -0.0447 1.0000 0.0673
-7.500 -0.6135 0.04738 0.04157 -0.0430 1.0000 0.0655
-7.250 -0.6114 0.04337 0.03724 -0.0411 1.0000 0.0644
-7.000 -0.6060 0.03983 0.03328 -0.0391 1.0000 0.0647
-6.750 -0.5969 0.03660 0.02959 -0.0372 1.0000 0.0654
-6.500 -0.5843 0.03350 0.02601 -0.0354 1.0000 0.0656
-6.250 -0.5686 0.03075 0.02279 -0.0337 1.0000 0.0662
-6.000 -0.5507 0.02871 0.02024 -0.0320 1.0000 0.0680
-5.750 -0.5323 0.02653 0.01797 -0.0309 1.0000 0.0721
-5.500 -0.5122 0.02511 0.01641 -0.0296 1.0000 0.0765
-5.250 -0.4907 0.02369 0.01468 -0.0282 1.0000 0.0809
-5.000 -0.4705 0.02226 0.01333 -0.0271 1.0000 0.0890
-4.750 -0.4496 0.02108 0.01214 -0.0259 1.0000 0.1006
-4.500 -0.4290 0.01995 0.01107 -0.0247 1.0000 0.1195
-4.250 -0.4091 0.01898 0.01022 -0.0236 1.0000 0.1511
-4.000 -0.3896 0.01813 0.00964 -0.0227 1.0000 0.1889
-3.750 -0.3701 0.01742 0.00919 -0.0219 1.0000 0.2420
-3.500 -0.3510 0.01656 0.00879 -0.0209 1.0000 0.3152
-3.250 -0.3333 0.01564 0.00858 -0.0196 1.0000 0.4290
-3.000 -0.3192 0.01515 0.00885 -0.0169 1.0000 0.5741
-2.750 -0.3054 0.01527 0.00919 -0.0139 1.0000 0.6718
-2.500 -0.2927 0.01550 0.00949 -0.0107 1.0000 0.7321
-2.250 -0.2758 0.01581 0.00984 -0.0081 0.9976 0.7811
-2.000 -0.2436 0.01631 0.01034 -0.0080 0.9874 0.8293
-1.750 -0.2123 0.01669 0.01065 -0.0078 0.9769 0.8714
-1.500 -0.1754 0.01702 0.01091 -0.0086 0.9676 0.9114
-1.250 -0.1185 0.01738 0.01114 -0.0134 0.9602 0.9459
-1.000 -0.0379 0.01784 0.01138 -0.0233 0.9571 0.9706
-0.750 0.0440 0.01799 0.01136 -0.0339 0.9523 0.9866
-0.500 0.1209 0.01798 0.01121 -0.0439 0.9471 1.0000
-0.250 0.1637 0.01784 0.01099 -0.0477 0.9348 1.0000
0.000 0.2094 0.01765 0.01074 -0.0518 0.9236 1.0000
0.250 0.2632 0.01737 0.01041 -0.0570 0.9147 1.0000
0.500 0.3066 0.01708 0.01010 -0.0603 0.9022 1.0000
0.750 0.3502 0.01675 0.00975 -0.0634 0.8899 1.0000
1.000 0.3921 0.01636 0.00937 -0.0659 0.8771 1.0000
1.250 0.4304 0.01598 0.00899 -0.0677 0.8633 1.0000
1.500 0.4637 0.01564 0.00865 -0.0684 0.8479 1.0000
1.750 0.4927 0.01537 0.00837 -0.0682 0.8313 1.0000
2.000 0.5196 0.01514 0.00812 -0.0676 0.8142 1.0000
2.250 0.5454 0.01494 0.00790 -0.0667 0.7967 1.0000
2.500 0.5659 0.01488 0.00783 -0.0650 0.7774 1.0000
2.750 0.5861 0.01486 0.00778 -0.0631 0.7570 1.0000
3.000 0.6099 0.01482 0.00767 -0.0618 0.7375 1.0000
3.250 0.6311 0.01489 0.00769 -0.0601 0.7158 1.0000
3.500 0.6545 0.01494 0.00771 -0.0588 0.6940 1.0000
3.750 0.6773 0.01506 0.00777 -0.0574 0.6711 1.0000
4.000 0.7015 0.01518 0.00781 -0.0562 0.6480 1.0000
4.250 0.7237 0.01537 0.00797 -0.0548 0.6229 1.0000
4.500 0.7471 0.01557 0.00810 -0.0535 0.5980 1.0000
4.750 0.7706 0.01579 0.00823 -0.0523 0.5726 1.0000
5.000 0.7924 0.01607 0.00846 -0.0509 0.5450 1.0000
5.250 0.8142 0.01638 0.00873 -0.0495 0.5170 1.0000
5.500 0.8357 0.01674 0.00901 -0.0481 0.4885 1.0000
5.750 0.8568 0.01713 0.00933 -0.0467 0.4596 1.0000
6.000 0.8774 0.01758 0.00969 -0.0452 0.4301 1.0000
6.250 0.8977 0.01807 0.01012 -0.0437 0.4007 1.0000
6.500 0.9173 0.01862 0.01059 -0.0422 0.3709 1.0000
6.750 0.9364 0.01924 0.01112 -0.0407 0.3410 1.0000
7.000 0.9548 0.01992 0.01170 -0.0391 0.3112 1.0000
7.250 0.9726 0.02068 0.01238 -0.0374 0.2819 1.0000
7.500 0.9896 0.02150 0.01310 -0.0357 0.2533 1.0000
7.750 1.0062 0.02241 0.01392 -0.0340 0.2264 1.0000
8.000 1.0225 0.02342 0.01479 -0.0324 0.2022 1.0000
8.250 1.0387 0.02447 0.01579 -0.0307 0.1797 1.0000
8.500 1.0554 0.02573 0.01696 -0.0293 0.1606 1.0000
8.750 1.0715 0.02697 0.01824 -0.0276 0.1427 1.0000
9.000 1.0886 0.02840 0.01966 -0.0262 0.1278 1.0000
9.250 1.1061 0.02995 0.02123 -0.0249 0.1151 1.0000
9.500 1.1247 0.03165 0.02290 -0.0239 0.1045 1.0000
9.750 1.1440 0.03334 0.02458 -0.0229 0.0955 1.0000
10.000 1.1594 0.03524 0.02679 -0.0213 0.0879 1.0000
10.250 1.1818 0.03774 0.02916 -0.0212 0.0809 1.0000
10.500 1.1905 0.03949 0.03136 -0.0187 0.0757 1.0000
10.750 1.2064 0.04147 0.03333 -0.0177 0.0702 1.0000
11.000 1.2119 0.04434 0.03659 -0.0153 0.0664 1.0000
11.250 1.2146 0.04653 0.03912 -0.0127 0.0627 1.0000
11.500 1.2216 0.04872 0.04142 -0.0108 0.0594 1.0000
11.750 1.2239 0.05257 0.04540 -0.0092 0.0566 1.0000
12.000 1.2076 0.05492 0.04814 -0.0050 0.0555 1.0000
12.250 1.1908 0.05797 0.05154 -0.0019 0.0547 1.0000
12.500 1.1721 0.06142 0.05530 0.0003 0.0539 1.0000
12.750 1.1510 0.06555 0.05972 0.0014 0.0536 1.0000
13.000 1.1277 0.07031 0.06474 0.0013 0.0534 1.0000
13.250 1.1022 0.07590 0.07058 0.0000 0.0537 1.0000
13.500 1.0751 0.08245 0.07735 -0.0027 0.0544 1.0000
13.750 1.0482 0.08983 0.08489 -0.0066 0.0552 1.0000
14.000 1.0207 0.09821 0.09341 -0.0114 0.0561 1.0000
14.250 0.9970 0.10702 0.10228 -0.0164 0.0569 1.0000
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Polar data table (+)
Polar graphs
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