NASA/LANGLEY RC-12(B)3 AIRFOIL (rc12b3-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| 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: 76.43 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-rc12b3-il-1000000-n5.txt Download as CSV file: xf-rc12b3-il-1000000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.000 -1.1889 0.04617 0.04339 -0.0575 1.0000 0.0104
-15.750 -1.2078 0.04168 0.03872 -0.0577 1.0000 0.0105
-15.500 -1.2185 0.03860 0.03548 -0.0564 1.0000 0.0105
-15.250 -1.2237 0.03625 0.03298 -0.0544 1.0000 0.0106
-15.000 -1.2247 0.03435 0.03095 -0.0522 1.0000 0.0107
-14.750 -1.2238 0.03266 0.02912 -0.0498 1.0000 0.0108
-14.500 -1.2205 0.03118 0.02750 -0.0473 1.0000 0.0108
-14.250 -1.2153 0.02984 0.02604 -0.0448 1.0000 0.0109
-14.000 -1.2084 0.02863 0.02470 -0.0423 1.0000 0.0109
-13.750 -1.1992 0.02756 0.02351 -0.0399 1.0000 0.0110
-13.500 -1.1905 0.02627 0.02208 -0.0376 0.9869 0.0111
-13.250 -1.1779 0.02492 0.02059 -0.0360 0.9647 0.0113
-13.000 -1.1657 0.02393 0.01946 -0.0337 0.9507 0.0115
-12.750 -1.1517 0.02308 0.01849 -0.0317 0.9409 0.0116
-12.500 -1.1352 0.02231 0.01761 -0.0300 0.9330 0.0118
-12.250 -1.1177 0.02161 0.01680 -0.0285 0.9267 0.0119
-12.000 -1.0986 0.02093 0.01603 -0.0273 0.9209 0.0121
-11.750 -1.0790 0.02032 0.01532 -0.0260 0.9154 0.0123
-11.500 -1.0583 0.01975 0.01466 -0.0250 0.9107 0.0125
-11.250 -1.0369 0.01919 0.01403 -0.0240 0.9058 0.0127
-11.000 -1.0154 0.01864 0.01339 -0.0231 0.9009 0.0129
-10.750 -0.9937 0.01809 0.01273 -0.0221 0.8966 0.0131
-10.500 -0.9712 0.01753 0.01209 -0.0213 0.8922 0.0133
-10.250 -0.9485 0.01702 0.01149 -0.0205 0.8874 0.0135
-10.000 -0.9255 0.01654 0.01092 -0.0197 0.8830 0.0137
-9.750 -0.9018 0.01607 0.01038 -0.0191 0.8788 0.0139
-9.500 -0.8777 0.01564 0.00987 -0.0185 0.8740 0.0140
-9.250 -0.8543 0.01513 0.00928 -0.0178 0.8694 0.0143
-9.000 -0.8307 0.01461 0.00869 -0.0171 0.8653 0.0147
-8.750 -0.8060 0.01418 0.00821 -0.0166 0.8607 0.0150
-8.500 -0.7811 0.01380 0.00779 -0.0161 0.8559 0.0154
-8.250 -0.7560 0.01346 0.00739 -0.0156 0.8516 0.0158
-8.000 -0.7304 0.01313 0.00701 -0.0152 0.8472 0.0161
-7.750 -0.7047 0.01282 0.00666 -0.0149 0.8424 0.0166
-7.500 -0.6789 0.01253 0.00632 -0.0145 0.8378 0.0171
-7.250 -0.6530 0.01226 0.00599 -0.0142 0.8335 0.0175
-7.000 -0.6270 0.01194 0.00564 -0.0138 0.8287 0.0179
-6.750 -0.6011 0.01162 0.00529 -0.0135 0.8238 0.0187
-6.500 -0.5750 0.01136 0.00500 -0.0132 0.8192 0.0195
-6.250 -0.5485 0.01111 0.00473 -0.0129 0.8146 0.0203
-6.000 -0.5219 0.01089 0.00447 -0.0127 0.8094 0.0211
-5.750 -0.4954 0.01069 0.00423 -0.0124 0.8047 0.0219
-5.500 -0.4689 0.01044 0.00397 -0.0122 0.7999 0.0235
-5.250 -0.4422 0.01023 0.00375 -0.0120 0.7947 0.0250
-5.000 -0.4154 0.01006 0.00355 -0.0118 0.7896 0.0265
-4.750 -0.3886 0.00986 0.00335 -0.0116 0.7846 0.0289
-4.500 -0.3617 0.00968 0.00316 -0.0114 0.7790 0.0312
-4.250 -0.3347 0.00954 0.00299 -0.0112 0.7736 0.0332
-4.000 -0.3078 0.00936 0.00283 -0.0110 0.7681 0.0365
-3.750 -0.2806 0.00922 0.00267 -0.0109 0.7620 0.0394
-3.500 -0.2537 0.00908 0.00253 -0.0107 0.7564 0.0431
-3.250 -0.2265 0.00894 0.00240 -0.0106 0.7502 0.0475
-3.000 -0.1994 0.00881 0.00227 -0.0104 0.7437 0.0525
-2.750 -0.1722 0.00869 0.00216 -0.0103 0.7375 0.0574
-2.500 -0.1451 0.00857 0.00205 -0.0102 0.7302 0.0640
-2.250 -0.1178 0.00848 0.00196 -0.0100 0.7231 0.0705
-2.000 -0.0907 0.00837 0.00186 -0.0099 0.7150 0.0785
-1.750 -0.0635 0.00828 0.00178 -0.0098 0.7076 0.0863
-1.500 -0.0363 0.00819 0.00170 -0.0097 0.6995 0.0961
-1.250 -0.0092 0.00810 0.00163 -0.0095 0.6918 0.1075
-1.000 0.0178 0.00800 0.00157 -0.0094 0.6832 0.1233
-0.750 0.0447 0.00791 0.00151 -0.0092 0.6749 0.1426
-0.500 0.0712 0.00780 0.00146 -0.0090 0.6653 0.1672
-0.250 0.0975 0.00767 0.00142 -0.0087 0.6543 0.2024
0.000 0.1226 0.00748 0.00138 -0.0083 0.6427 0.2612
0.250 0.1458 0.00716 0.00133 -0.0074 0.6310 0.3598
0.500 0.1361 0.00534 0.00113 0.0005 0.6215 0.8241
0.750 0.1792 0.00547 0.00152 -0.0026 0.6085 0.9209
1.000 0.2055 0.00563 0.00162 -0.0021 0.5956 0.9339
1.250 0.2305 0.00578 0.00171 -0.0013 0.5822 0.9422
1.500 0.2603 0.00597 0.00185 -0.0017 0.5677 0.9474
1.750 0.2950 0.00624 0.00204 -0.0032 0.5499 0.9514
2.000 0.3151 0.00647 0.00219 -0.0013 0.5294 0.9590
2.250 0.3625 0.00690 0.00249 -0.0057 0.4999 0.9608
2.500 0.4009 0.00716 0.00265 -0.0082 0.4777 0.9619
2.750 0.4327 0.00734 0.00274 -0.0093 0.4570 0.9627
3.000 0.4620 0.00748 0.00280 -0.0097 0.4392 0.9634
3.250 0.4905 0.00765 0.00289 -0.0101 0.4184 0.9643
3.500 0.5177 0.00786 0.00298 -0.0102 0.3921 0.9652
3.750 0.5438 0.00808 0.00309 -0.0100 0.3659 0.9663
4.000 0.5691 0.00828 0.00319 -0.0097 0.3445 0.9678
4.250 0.5887 0.00845 0.00330 -0.0080 0.3266 0.9702
4.500 0.6067 0.00863 0.00340 -0.0061 0.3083 0.9724
4.750 0.6359 0.00883 0.00352 -0.0066 0.2889 0.9727
5.000 0.6645 0.00909 0.00367 -0.0072 0.2657 0.9731
5.250 0.6928 0.00934 0.00384 -0.0076 0.2451 0.9736
5.500 0.7204 0.00959 0.00401 -0.0079 0.2255 0.9741
5.750 0.7470 0.00990 0.00420 -0.0080 0.2024 0.9746
6.000 0.7733 0.01021 0.00442 -0.0081 0.1797 0.9752
6.250 0.7999 0.01051 0.00463 -0.0082 0.1624 0.9759
6.500 0.8258 0.01083 0.00487 -0.0082 0.1456 0.9767
6.750 0.8507 0.01113 0.00510 -0.0080 0.1304 0.9776
7.000 0.8744 0.01145 0.00535 -0.0075 0.1147 0.9786
7.250 0.8968 0.01178 0.00561 -0.0068 0.1007 0.9798
7.500 0.9177 0.01211 0.00589 -0.0057 0.0895 0.9814
8.000 0.9573 0.01268 0.00641 -0.0030 0.0735 0.9841
8.250 0.9827 0.01304 0.00673 -0.0031 0.0649 0.9846
8.500 1.0082 0.01344 0.00707 -0.0032 0.0562 0.9851
8.750 1.0339 0.01378 0.00741 -0.0033 0.0506 0.9856
9.000 1.0579 0.01416 0.00777 -0.0031 0.0453 0.9862
9.250 1.0816 0.01453 0.00813 -0.0028 0.0411 0.9869
9.500 1.1044 0.01494 0.00853 -0.0024 0.0371 0.9877
9.750 1.1267 0.01534 0.00894 -0.0019 0.0338 0.9886
10.000 1.1476 0.01579 0.00938 -0.0012 0.0305 0.9897
10.250 1.1676 0.01620 0.00980 -0.0003 0.0282 0.9909
10.500 1.1840 0.01666 0.01026 0.0013 0.0260 0.9926
10.750 1.1984 0.01709 0.01073 0.0033 0.0245 0.9940
11.000 1.2189 0.01755 0.01122 0.0038 0.0231 0.9946
11.250 1.2382 0.01809 0.01178 0.0045 0.0215 0.9953
11.500 1.2566 0.01870 0.01240 0.0052 0.0200 0.9961
11.750 1.2755 0.01925 0.01299 0.0059 0.0193 0.9969
12.000 1.2935 0.01987 0.01365 0.0066 0.0183 0.9978
12.250 1.3106 0.02056 0.01438 0.0074 0.0173 0.9986
12.500 1.3266 0.02135 0.01519 0.0082 0.0162 0.9993
12.750 1.3436 0.02208 0.01597 0.0089 0.0155 0.9999
13.000 1.3508 0.02279 0.01673 0.0115 0.0149 1.0000
13.250 1.3558 0.02356 0.01754 0.0144 0.0142 1.0000
13.500 1.3604 0.02440 0.01842 0.0172 0.0136 1.0000
13.750 1.3647 0.02534 0.01940 0.0199 0.0129 1.0000
14.000 1.3699 0.02628 0.02039 0.0223 0.0125 1.0000
14.250 1.3760 0.02726 0.02142 0.0244 0.0121 1.0000
14.500 1.3818 0.02833 0.02255 0.0265 0.0116 1.0000
14.750 1.3871 0.02951 0.02378 0.0283 0.0111 1.0000
15.000 1.3920 0.03081 0.02514 0.0300 0.0106 1.0000
15.250 1.3961 0.03226 0.02664 0.0316 0.0101 1.0000
15.500 1.4004 0.03379 0.02823 0.0330 0.0097 1.0000
15.750 1.4053 0.03535 0.02986 0.0341 0.0094 1.0000
16.000 1.4095 0.03706 0.03165 0.0350 0.0091 1.0000
16.250 1.4130 0.03894 0.03359 0.0358 0.0087 1.0000
16.500 1.4156 0.04099 0.03572 0.0365 0.0083 1.0000
16.750 1.4170 0.04326 0.03806 0.0369 0.0080 1.0000
17.000 1.4172 0.04578 0.04064 0.0372 0.0076 1.0000
17.250 1.4165 0.04848 0.04343 0.0373 0.0074 1.0000
17.500 1.4164 0.05122 0.04625 0.0372 0.0072 1.0000
17.750 1.4150 0.05422 0.04936 0.0369 0.0070 1.0000
18.000 1.4123 0.05747 0.05270 0.0364 0.0068 1.0000
18.250 1.4082 0.06099 0.05632 0.0357 0.0067 1.0000
18.500 1.4025 0.06483 0.06026 0.0348 0.0065 1.0000
18.750 1.3954 0.06896 0.06448 0.0336 0.0064 1.0000
19.000 1.3863 0.07350 0.06913 0.0322 0.0063 1.0000
19.250 1.3757 0.07832 0.07407 0.0306 0.0062 1.0000
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