NASA/LANGLEY RC-12(B)3 AIRFOIL (rc12b3-il) Xfoil prediction polar at RE=50,000 Ncrit=9
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Airfoil: NASA/LANGLEY RC-12(B)3 AIRFOIL (rc12b3-il) Reynolds number: 50,000 Max Cl/Cd: 32.51 at α=7.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-rc12b3-il-50000.txt Download as CSV file: xf-rc12b3-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: NASA/LANGLEY RC-12(B)3 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.4634 0.12557 0.11842 -0.0173 1.0000 0.2278
-10.250 -0.4333 0.11956 0.11237 -0.0156 1.0000 0.2366
-10.000 -0.4632 0.11905 0.11200 -0.0187 1.0000 0.2443
-9.750 -0.4290 0.11312 0.10600 -0.0166 1.0000 0.2556
-9.500 -0.4306 0.10982 0.10277 -0.0172 1.0000 0.2648
-9.250 -0.4496 0.10832 0.10139 -0.0186 1.0000 0.2766
-9.000 -0.4371 0.10448 0.09756 -0.0175 1.0000 0.2922
-8.750 -0.4327 0.10125 0.09438 -0.0167 1.0000 0.3084
-8.500 -0.4341 0.09839 0.09159 -0.0160 1.0000 0.3251
-8.250 -0.4416 0.09587 0.08917 -0.0150 1.0000 0.3421
-8.000 -0.4101 0.09126 0.08452 -0.0130 1.0000 0.3635
-7.750 -0.4064 0.08863 0.08193 -0.0111 1.0000 0.3872
-7.500 -0.3953 0.08563 0.07897 -0.0087 1.0000 0.4155
-7.250 -0.3892 0.08335 0.07674 -0.0054 1.0000 0.4524
-7.000 -0.3676 0.08043 0.07383 -0.0021 1.0000 0.4972
-6.750 -0.3485 0.07773 0.07114 0.0011 1.0000 0.5443
-6.500 -0.3133 0.07476 0.06811 0.0039 1.0000 0.6113
-5.250 -0.6018 0.05386 0.04599 0.0018 1.0000 0.1813
-5.000 -0.5910 0.05065 0.04253 0.0039 1.0000 0.1740
-4.750 -0.5818 0.04742 0.03887 0.0062 1.0000 0.1685
-4.500 -0.5700 0.04471 0.03537 0.0089 1.0000 0.1624
-4.250 -0.5542 0.04205 0.03240 0.0107 1.0000 0.1612
-4.000 -0.5379 0.04000 0.02977 0.0127 1.0000 0.1629
-3.750 -0.5189 0.03783 0.02754 0.0137 1.0000 0.1679
-3.500 -0.4981 0.03606 0.02545 0.0150 1.0000 0.1717
-3.250 -0.4769 0.03471 0.02357 0.0164 1.0000 0.1789
-3.000 -0.4543 0.03311 0.02196 0.0170 1.0000 0.1874
-2.750 -0.4308 0.03190 0.02043 0.0177 1.0000 0.1981
-2.500 -0.4067 0.03091 0.01923 0.0183 1.0000 0.2117
-2.250 -0.1293 0.02603 0.01761 -0.0232 1.0000 1.0000
-2.000 -0.1179 0.02629 0.01738 -0.0208 1.0000 1.0000
-1.750 -0.1080 0.02655 0.01732 -0.0184 1.0000 1.0000
-1.500 -0.0982 0.02684 0.01735 -0.0160 1.0000 1.0000
-1.250 -0.0882 0.02715 0.01744 -0.0138 1.0000 1.0000
-1.000 -0.0780 0.02750 0.01758 -0.0116 1.0000 1.0000
-0.750 -0.0676 0.02787 0.01777 -0.0095 1.0000 1.0000
-0.500 -0.0570 0.02828 0.01802 -0.0075 1.0000 1.0000
-0.250 -0.0462 0.02872 0.01832 -0.0056 1.0000 1.0000
0.000 -0.0353 0.02920 0.01866 -0.0037 1.0000 1.0000
0.250 -0.0243 0.02971 0.01906 -0.0020 1.0000 1.0000
0.500 -0.0132 0.03027 0.01951 -0.0003 1.0000 1.0000
0.750 -0.0021 0.03087 0.02001 0.0012 1.0000 1.0000
1.000 0.0436 0.03193 0.02096 -0.0041 0.9884 1.0000
1.250 0.0923 0.03307 0.02201 -0.0099 0.9738 1.0000
1.500 0.1379 0.03415 0.02303 -0.0149 0.9588 1.0000
1.750 0.1813 0.03519 0.02403 -0.0193 0.9432 1.0000
2.000 0.2240 0.03620 0.02502 -0.0234 0.9272 1.0000
2.250 0.2662 0.03716 0.02598 -0.0271 0.9109 1.0000
2.500 0.3019 0.03801 0.02686 -0.0296 0.8939 1.0000
2.750 0.3330 0.03881 0.02769 -0.0311 0.8760 1.0000
3.000 0.3651 0.03957 0.02849 -0.0326 0.8579 1.0000
3.250 0.3989 0.04028 0.02925 -0.0342 0.8396 1.0000
3.500 0.4349 0.04089 0.02995 -0.0360 0.8214 1.0000
3.750 0.4745 0.04138 0.03053 -0.0381 0.8034 1.0000
4.000 0.5189 0.04165 0.03094 -0.0407 0.7856 1.0000
4.250 0.5535 0.04197 0.03137 -0.0416 0.7669 1.0000
4.500 0.5743 0.04250 0.03199 -0.0404 0.7468 1.0000
4.750 0.6131 0.04249 0.03214 -0.0414 0.7276 1.0000
5.000 0.6644 0.04177 0.03161 -0.0436 0.7090 1.0000
5.250 0.7166 0.04038 0.03045 -0.0448 0.6913 1.0000
5.500 0.7387 0.04027 0.03047 -0.0427 0.6700 1.0000
5.750 0.7753 0.03921 0.02958 -0.0417 0.6498 1.0000
6.000 0.8272 0.03699 0.02758 -0.0417 0.6304 1.0000
6.250 0.8613 0.03577 0.02650 -0.0401 0.6076 1.0000
6.500 0.9068 0.03361 0.02445 -0.0391 0.5828 1.0000
6.750 0.9350 0.03272 0.02364 -0.0367 0.5542 1.0000
7.000 0.9642 0.03188 0.02279 -0.0345 0.5233 1.0000
7.250 0.9907 0.03138 0.02220 -0.0322 0.4903 1.0000
7.500 1.0152 0.03123 0.02189 -0.0299 0.4556 1.0000
7.750 1.0299 0.03184 0.02242 -0.0268 0.4209 1.0000
8.000 1.0446 0.03257 0.02302 -0.0238 0.3862 1.0000
8.250 1.0588 0.03345 0.02374 -0.0209 0.3523 1.0000
8.500 1.0718 0.03456 0.02470 -0.0181 0.3206 1.0000
8.750 1.0835 0.03587 0.02590 -0.0152 0.2916 1.0000
9.000 1.0961 0.03728 0.02716 -0.0125 0.2653 1.0000
9.250 1.1086 0.03883 0.02863 -0.0100 0.2420 1.0000
9.500 1.1225 0.04060 0.03029 -0.0077 0.2219 1.0000
9.750 1.1321 0.04254 0.03235 -0.0050 0.2054 1.0000
10.000 1.1437 0.04462 0.03447 -0.0027 0.1911 1.0000
10.250 1.1580 0.04675 0.03657 -0.0008 0.1782 1.0000
10.500 1.1569 0.04920 0.03942 0.0030 0.1698 1.0000
10.750 1.1651 0.05187 0.04220 0.0054 0.1617 1.0000
11.000 1.1602 0.05455 0.04520 0.0092 0.1558 1.0000
11.250 1.1720 0.05737 0.04804 0.0109 0.1489 1.0000
11.500 1.1525 0.06065 0.05173 0.0159 0.1471 1.0000
11.750 1.1301 0.06402 0.05542 0.0207 0.1457 1.0000
12.000 1.1023 0.06732 0.05893 0.0257 0.1453 1.0000
12.250 1.0707 0.07118 0.06298 0.0298 0.1456 1.0000
12.500 1.0362 0.07597 0.06792 0.0323 0.1465 1.0000
12.750 1.0006 0.08180 0.07388 0.0331 0.1478 1.0000
13.000 0.9659 0.08867 0.08084 0.0324 0.1491 1.0000
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Polar data table (+)
Polar graphs
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