NASA/LANGLEY RC-12(B)3 AIRFOIL (rc12b3-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: NASA/LANGLEY RC-12(B)3 AIRFOIL (rc12b3-il) Reynolds number: 1,000,000 Max Cl/Cd: 87.24 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-rc12b3-il-1000000.txt Download as CSV file: xf-rc12b3-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.500 -1.0168 0.04947 0.04701 -0.0564 1.0000 0.0135
-14.250 -1.0421 0.04385 0.04117 -0.0579 1.0000 0.0135
-14.000 -1.0648 0.03965 0.03675 -0.0563 1.0000 0.0136
-13.750 -1.0801 0.03656 0.03347 -0.0535 1.0000 0.0137
-13.500 -1.0859 0.03441 0.03119 -0.0505 1.0000 0.0138
-13.250 -1.0849 0.03284 0.02952 -0.0478 1.0000 0.0140
-13.000 -1.0795 0.03161 0.02821 -0.0452 1.0000 0.0141
-12.750 -1.0719 0.03053 0.02705 -0.0428 1.0000 0.0143
-12.500 -1.0618 0.02943 0.02585 -0.0407 1.0000 0.0145
-12.250 -1.0501 0.02820 0.02451 -0.0390 1.0000 0.0147
-12.000 -1.0372 0.02700 0.02318 -0.0373 1.0000 0.0149
-11.750 -1.0162 0.02570 0.02171 -0.0372 0.9868 0.0151
-11.500 -0.9964 0.02453 0.02039 -0.0366 0.9760 0.0154
-11.250 -0.9800 0.02354 0.01925 -0.0350 0.9654 0.0156
-10.750 -0.9480 0.02187 0.01729 -0.0312 0.9481 0.0161
-10.250 -0.9101 0.02055 0.01571 -0.0282 0.9352 0.0165
-10.000 -0.8955 0.01910 0.01405 -0.0261 0.9290 0.0168
-9.750 -0.8776 0.01804 0.01286 -0.0246 0.9236 0.0173
-9.500 -0.8555 0.01748 0.01225 -0.0237 0.9184 0.0177
-9.250 -0.8333 0.01698 0.01168 -0.0227 0.9135 0.0180
-9.000 -0.8105 0.01648 0.01110 -0.0219 0.9089 0.0184
-8.750 -0.7869 0.01596 0.01051 -0.0212 0.9041 0.0188
-8.500 -0.7634 0.01546 0.00992 -0.0204 0.8994 0.0193
-8.250 -0.7397 0.01502 0.00939 -0.0196 0.8950 0.0197
-8.000 -0.7146 0.01460 0.00891 -0.0191 0.8906 0.0200
-7.750 -0.6899 0.01416 0.00840 -0.0185 0.8859 0.0204
-7.500 -0.6682 0.01333 0.00747 -0.0174 0.8814 0.0212
-7.250 -0.6432 0.01294 0.00705 -0.0169 0.8771 0.0219
-7.000 -0.6174 0.01262 0.00671 -0.0166 0.8724 0.0227
-6.750 -0.5916 0.01233 0.00638 -0.0161 0.8679 0.0236
-6.500 -0.5660 0.01206 0.00603 -0.0157 0.8634 0.0243
-6.250 -0.5403 0.01167 0.00560 -0.0153 0.8589 0.0251
-6.000 -0.5153 0.01122 0.00513 -0.0147 0.8541 0.0265
-5.750 -0.4892 0.01097 0.00485 -0.0143 0.8495 0.0278
-5.500 -0.4626 0.01075 0.00460 -0.0141 0.8450 0.0292
-5.250 -0.4366 0.01043 0.00425 -0.0137 0.8401 0.0309
-5.000 -0.4104 0.01018 0.00400 -0.0134 0.8353 0.0334
-4.750 -0.3835 0.01003 0.00381 -0.0131 0.8306 0.0356
-4.500 -0.3573 0.00973 0.00352 -0.0128 0.8255 0.0390
-4.250 -0.3304 0.00956 0.00334 -0.0126 0.8204 0.0422
-4.000 -0.3040 0.00936 0.00312 -0.0123 0.8155 0.0462
-3.750 -0.2769 0.00918 0.00297 -0.0121 0.8102 0.0506
-3.500 -0.2501 0.00900 0.00279 -0.0119 0.8048 0.0560
-3.250 -0.2232 0.00888 0.00265 -0.0117 0.7995 0.0613
-3.000 -0.1961 0.00869 0.00250 -0.0115 0.7940 0.0683
-2.750 -0.1689 0.00858 0.00238 -0.0114 0.7882 0.0741
-2.500 -0.1422 0.00842 0.00225 -0.0111 0.7825 0.0843
-2.250 -0.1150 0.00827 0.00214 -0.0110 0.7762 0.0945
-2.000 -0.0882 0.00815 0.00203 -0.0108 0.7700 0.1070
-1.750 -0.0613 0.00800 0.00194 -0.0106 0.7638 0.1239
-1.500 -0.0345 0.00785 0.00184 -0.0104 0.7572 0.1454
-1.250 -0.0083 0.00767 0.00176 -0.0101 0.7511 0.1783
-1.000 0.0172 0.00740 0.00168 -0.0097 0.7442 0.2337
-0.750 0.0387 0.00690 0.00157 -0.0086 0.7376 0.3629
-0.500 0.0475 0.00575 0.00140 -0.0048 0.7305 0.6431
-0.250 0.0742 0.00511 0.00173 -0.0040 0.7233 0.9175
0.000 0.1020 0.00533 0.00192 -0.0037 0.7153 0.9358
0.250 0.1318 0.00562 0.00216 -0.0037 0.7070 0.9464
0.500 0.1776 0.00599 0.00249 -0.0074 0.6985 0.9509
0.750 0.2030 0.00622 0.00266 -0.0066 0.6900 0.9582
1.000 0.2537 0.00651 0.00291 -0.0116 0.6803 0.9597
1.250 0.2978 0.00674 0.00309 -0.0151 0.6705 0.9617
1.500 0.3398 0.00700 0.00329 -0.0181 0.6590 0.9651
1.750 0.3706 0.00727 0.00351 -0.0186 0.6452 0.9716
2.000 0.4223 0.00747 0.00363 -0.0238 0.6277 0.9739
2.250 0.4608 0.00757 0.00367 -0.0262 0.6123 0.9756
2.750 0.5223 0.00769 0.00368 -0.0277 0.5790 0.9780
3.000 0.5512 0.00778 0.00370 -0.0281 0.5593 0.9793
3.500 0.6005 0.00817 0.00389 -0.0271 0.5093 0.9835
3.750 0.6319 0.00828 0.00389 -0.0282 0.4829 0.9839
4.000 0.6627 0.00842 0.00393 -0.0291 0.4561 0.9844
4.250 0.6936 0.00857 0.00397 -0.0301 0.4294 0.9849
4.500 0.7243 0.00876 0.00405 -0.0310 0.4004 0.9855
4.750 0.7545 0.00897 0.00415 -0.0319 0.3732 0.9862
5.000 0.7838 0.00920 0.00426 -0.0325 0.3455 0.9869
5.250 0.8124 0.00945 0.00439 -0.0331 0.3172 0.9876
5.500 0.8406 0.00970 0.00453 -0.0335 0.2912 0.9885
5.750 0.8685 0.00998 0.00470 -0.0339 0.2660 0.9895
6.000 0.8960 0.01027 0.00488 -0.0343 0.2411 0.9906
6.250 0.9226 0.01058 0.00509 -0.0344 0.2177 0.9918
6.500 0.9474 0.01094 0.00533 -0.0342 0.1940 0.9929
6.750 0.9719 0.01128 0.00558 -0.0339 0.1732 0.9940
7.000 0.9997 0.01163 0.00581 -0.0345 0.1513 0.9945
7.250 1.0281 0.01195 0.00605 -0.0351 0.1331 0.9951
7.500 1.0560 0.01230 0.00632 -0.0356 0.1153 0.9959
7.750 1.0827 0.01271 0.00664 -0.0360 0.0987 0.9967
8.000 1.1086 0.01310 0.00696 -0.0361 0.0855 0.9974
8.250 1.1341 0.01349 0.00729 -0.0361 0.0743 0.9982
8.500 1.1594 0.01389 0.00765 -0.0362 0.0642 0.9989
8.750 1.1846 0.01431 0.00803 -0.0362 0.0556 0.9996
9.000 1.2071 0.01475 0.00844 -0.0356 0.0487 1.0000
9.250 1.2242 0.01521 0.00887 -0.0340 0.0434 1.0000
9.500 1.2416 0.01559 0.00927 -0.0323 0.0398 1.0000
9.750 1.2572 0.01606 0.00972 -0.0304 0.0364 1.0000
10.000 1.2724 0.01651 0.01019 -0.0283 0.0337 1.0000
10.250 1.2873 0.01691 0.01062 -0.0262 0.0316 1.0000
10.500 1.2989 0.01745 0.01116 -0.0236 0.0293 1.0000
10.750 1.3103 0.01792 0.01166 -0.0209 0.0277 1.0000
11.000 1.3210 0.01833 0.01212 -0.0180 0.0265 1.0000
11.250 1.3218 0.01876 0.01258 -0.0133 0.0254 1.0000
11.500 1.3203 0.01928 0.01313 -0.0083 0.0244 1.0000
11.750 1.3181 0.02000 0.01389 -0.0034 0.0231 1.0000
12.000 1.3243 0.02048 0.01443 -0.0002 0.0225 1.0000
12.250 1.3301 0.02104 0.01504 0.0031 0.0217 1.0000
12.500 1.3349 0.02169 0.01573 0.0064 0.0208 1.0000
12.750 1.3382 0.02247 0.01653 0.0097 0.0198 1.0000
13.000 1.3372 0.02353 0.01764 0.0134 0.0188 1.0000
13.250 1.3444 0.02421 0.01838 0.0160 0.0183 1.0000
13.500 1.3501 0.02503 0.01925 0.0186 0.0176 1.0000
13.750 1.3554 0.02593 0.02020 0.0211 0.0170 1.0000
14.000 1.3595 0.02698 0.02129 0.0236 0.0163 1.0000
14.250 1.3603 0.02837 0.02272 0.0261 0.0155 1.0000
14.500 1.3617 0.02981 0.02424 0.0283 0.0150 1.0000
14.750 1.3683 0.03099 0.02548 0.0300 0.0145 1.0000
15.000 1.3735 0.03233 0.02690 0.0315 0.0140 1.0000
15.250 1.3783 0.03380 0.02842 0.0329 0.0135 1.0000
15.500 1.3816 0.03548 0.03016 0.0341 0.0131 1.0000
15.750 1.3819 0.03755 0.03229 0.0353 0.0126 1.0000
16.000 1.3752 0.04041 0.03525 0.0363 0.0121 1.0000
16.250 1.3776 0.04255 0.03747 0.0369 0.0119 1.0000
16.500 1.3807 0.04472 0.03974 0.0372 0.0116 1.0000
16.750 1.3824 0.04714 0.04225 0.0374 0.0113 1.0000
17.000 1.3827 0.04979 0.04498 0.0374 0.0110 1.0000
17.250 1.3820 0.05267 0.04795 0.0372 0.0107 1.0000
17.500 1.3798 0.05584 0.05119 0.0368 0.0104 1.0000
17.750 1.3753 0.05942 0.05485 0.0361 0.0102 1.0000
18.000 1.3670 0.06359 0.05912 0.0351 0.0100 1.0000
18.250 1.3546 0.06847 0.06411 0.0338 0.0098 1.0000
18.500 1.3384 0.07408 0.06985 0.0320 0.0096 1.0000
18.750 1.3196 0.08020 0.07609 0.0299 0.0095 1.0000
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Polar data table (+)
Polar graphs
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