NASA/LANGLEY RC-12(N)1 AIRFOIL (rc12n1-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: NASA/LANGLEY RC-12(N)1 AIRFOIL (rc12n1-il) Reynolds number: 100,000 Max Cl/Cd: 49.2 at α=6.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-rc12n1-il-100000.txt Download as CSV file: xf-rc12n1-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: NASA/LANGLEY RC-12(N)1 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
------ -------- --------- --------- -------- -------- --------
-9.750 -0.5708 0.10485 0.10032 -0.0018 1.0000 0.1112
-9.500 -0.6021 0.09783 0.09341 -0.0136 1.0000 0.1139
-9.250 -0.6346 0.09269 0.08826 -0.0199 1.0000 0.1143
-9.000 -0.5766 0.09081 0.08643 -0.0096 1.0000 0.1220
-8.750 -0.5938 0.08455 0.08023 -0.0168 1.0000 0.1259
-8.500 -0.6355 0.07997 0.07551 -0.0221 1.0000 0.1286
-8.250 -0.6204 0.07492 0.07057 -0.0217 1.0000 0.1331
-8.000 -0.6164 0.07155 0.06718 -0.0222 1.0000 0.1403
-7.750 -0.6238 0.06713 0.06266 -0.0234 1.0000 0.1477
-7.250 -0.6091 0.06063 0.05611 -0.0235 1.0000 0.1688
-7.000 -0.6056 0.05762 0.05308 -0.0229 1.0000 0.1818
-6.750 -0.6211 0.05596 0.05135 -0.0191 1.0000 0.1929
-6.500 -0.6343 0.05517 0.05050 -0.0145 1.0000 0.2020
-5.500 -0.5321 0.03501 0.02720 -0.0173 0.9764 0.0884
-5.250 -0.4914 0.03188 0.02359 -0.0193 0.9718 0.0805
-5.000 -0.4577 0.02941 0.02071 -0.0202 0.9650 0.0783
-4.750 -0.4170 0.02746 0.01841 -0.0226 0.9601 0.0805
-4.500 -0.3761 0.02558 0.01621 -0.0248 0.9553 0.0813
-4.250 -0.3398 0.02413 0.01457 -0.0261 0.9488 0.0834
-4.000 -0.2998 0.02246 0.01294 -0.0285 0.9443 0.0900
-3.750 -0.2682 0.02144 0.01192 -0.0292 0.9374 0.0964
-3.500 -0.2378 0.02032 0.01092 -0.0298 0.9310 0.1065
-3.250 -0.2130 0.01952 0.01017 -0.0294 0.9240 0.1216
-3.000 -0.1905 0.01861 0.00942 -0.0286 0.9166 0.1556
-2.750 -0.1965 0.01608 0.00954 -0.0216 0.9089 0.6951
-2.500 -0.1670 0.01671 0.01054 -0.0174 0.9039 0.8343
-2.250 -0.1221 0.01784 0.01150 -0.0171 0.9003 0.8858
-2.000 -0.0209 0.01932 0.01265 -0.0265 0.9011 0.9282
-1.750 0.0269 0.01934 0.01250 -0.0306 0.8956 0.9385
-1.500 0.0622 0.01929 0.01232 -0.0328 0.8882 0.9481
-1.250 0.0996 0.01924 0.01214 -0.0353 0.8820 0.9573
-1.000 0.1406 0.01917 0.01198 -0.0388 0.8746 0.9658
-0.750 0.1781 0.01909 0.01181 -0.0413 0.8685 0.9753
-0.500 0.2195 0.01904 0.01170 -0.0452 0.8609 0.9849
-0.250 0.2621 0.01888 0.01147 -0.0488 0.8545 0.9937
0.000 0.3011 0.01880 0.01136 -0.0524 0.8467 1.0000
0.250 0.3178 0.01883 0.01134 -0.0512 0.8390 1.0000
0.500 0.3366 0.01896 0.01148 -0.0511 0.8299 1.0000
0.750 0.3530 0.01903 0.01149 -0.0495 0.8228 1.0000
1.000 0.3718 0.01925 0.01171 -0.0492 0.8130 1.0000
1.250 0.3897 0.01944 0.01188 -0.0480 0.8050 1.0000
1.500 0.4082 0.01967 0.01210 -0.0469 0.7961 1.0000
1.750 0.4271 0.01999 0.01242 -0.0458 0.7870 1.0000
2.000 0.4464 0.02014 0.01256 -0.0441 0.7794 1.0000
2.250 0.4656 0.02055 0.01299 -0.0432 0.7691 1.0000
2.500 0.4857 0.02070 0.01315 -0.0415 0.7616 1.0000
2.750 0.5054 0.02102 0.01351 -0.0403 0.7513 1.0000
3.000 0.5249 0.02136 0.01389 -0.0390 0.7411 1.0000
3.250 0.5465 0.02133 0.01387 -0.0370 0.7336 1.0000
3.500 0.5659 0.02168 0.01431 -0.0358 0.7217 1.0000
3.750 0.5860 0.02189 0.01457 -0.0342 0.7110 1.0000
4.000 0.6090 0.02165 0.01435 -0.0321 0.7030 1.0000
4.250 0.6294 0.02170 0.01448 -0.0305 0.6900 1.0000
4.500 0.6506 0.02139 0.01424 -0.0282 0.6761 1.0000
4.750 0.6726 0.02081 0.01369 -0.0258 0.6614 1.0000
5.000 0.6952 0.02016 0.01308 -0.0234 0.6461 1.0000
5.250 0.7184 0.01950 0.01248 -0.0211 0.6303 1.0000
5.500 0.7420 0.01882 0.01183 -0.0189 0.6136 1.0000
5.750 0.7642 0.01837 0.01147 -0.0170 0.5927 1.0000
6.000 0.7873 0.01784 0.01098 -0.0151 0.5702 1.0000
6.250 0.8092 0.01745 0.01068 -0.0131 0.5411 1.0000
6.500 0.8298 0.01721 0.01047 -0.0112 0.5005 1.0000
6.750 0.8477 0.01723 0.01033 -0.0088 0.4385 1.0000
7.000 0.8573 0.01816 0.01063 -0.0057 0.3331 1.0000
7.250 0.8580 0.02023 0.01183 -0.0021 0.2241 1.0000
7.500 0.8627 0.02212 0.01319 0.0008 0.1726 1.0000
7.750 0.8726 0.02367 0.01448 0.0033 0.1455 1.0000
8.000 0.8852 0.02522 0.01579 0.0053 0.1277 1.0000
8.250 0.9016 0.02671 0.01716 0.0069 0.1140 1.0000
8.500 0.9203 0.02810 0.01851 0.0082 0.1030 1.0000
8.750 0.9409 0.02965 0.02017 0.0093 0.0941 1.0000
9.000 0.9654 0.03174 0.02211 0.0096 0.0870 1.0000
9.250 0.9843 0.03319 0.02382 0.0109 0.0809 1.0000
9.500 1.0085 0.03539 0.02596 0.0111 0.0761 1.0000
9.750 1.0286 0.03807 0.02897 0.0122 0.0733 1.0000
10.000 1.0428 0.04020 0.03150 0.0138 0.0702 1.0000
10.250 1.0581 0.04227 0.03376 0.0150 0.0669 1.0000
10.500 1.0730 0.04495 0.03661 0.0161 0.0649 1.0000
10.750 1.0847 0.04864 0.04052 0.0172 0.0637 1.0000
11.000 1.0900 0.05302 0.04524 0.0187 0.0632 1.0000
11.250 1.0876 0.05689 0.04947 0.0208 0.0629 1.0000
11.500 1.0791 0.06001 0.05298 0.0234 0.0625 1.0000
11.750 1.0660 0.06328 0.05658 0.0259 0.0623 1.0000
12.000 1.0484 0.06659 0.06014 0.0284 0.0623 1.0000
12.250 1.0296 0.07040 0.06417 0.0298 0.0624 1.0000
12.500 1.0105 0.07479 0.06874 0.0302 0.0625 1.0000
12.750 0.9932 0.07987 0.07397 0.0299 0.0628 1.0000
13.000 0.9729 0.08435 0.07866 0.0290 0.0634 1.0000
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Polar data table (+)
Polar graphs
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