RAE6-9CK AIRFOIL (rae69ck-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: RAE6-9CK AIRFOIL (rae69ck-il) Reynolds number: 1,000,000 Max Cl/Cd: 69.43 at α=7.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-rae69ck-il-1000000-n5.txt Download as CSV file: xf-rae69ck-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: RAE6-9CK 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
------ -------- --------- --------- -------- -------- --------
-19.000 -0.6753 0.20875 0.20691 0.0137 1.0000 0.0039
-18.500 -0.8211 0.15006 0.14813 -0.0093 1.0000 0.0051
-18.250 -0.9366 0.11929 0.11708 -0.0244 1.0000 0.0049
-18.000 -0.9916 0.10356 0.10114 -0.0323 1.0000 0.0048
-17.750 -1.0368 0.09036 0.08774 -0.0393 1.0000 0.0047
-17.500 -1.0690 0.08041 0.07760 -0.0448 1.0000 0.0047
-17.250 -1.0883 0.07341 0.07045 -0.0485 1.0000 0.0047
-17.000 -1.1021 0.06763 0.06455 -0.0514 1.0000 0.0047
-16.750 -1.1126 0.06268 0.05948 -0.0537 1.0000 0.0048
-16.500 -1.1237 0.05788 0.05455 -0.0558 1.0000 0.0048
-16.250 -1.1287 0.05414 0.05071 -0.0572 1.0000 0.0048
-16.000 -1.1367 0.05024 0.04668 -0.0585 1.0000 0.0048
-15.750 -1.1378 0.04735 0.04370 -0.0593 1.0000 0.0049
-15.500 -1.1383 0.04464 0.04089 -0.0599 1.0000 0.0050
-15.250 -1.1395 0.04191 0.03806 -0.0604 1.0000 0.0050
-15.000 -1.1388 0.03948 0.03553 -0.0606 1.0000 0.0051
-14.750 -1.1376 0.03716 0.03311 -0.0607 1.0000 0.0052
-14.500 -1.1333 0.03522 0.03109 -0.0606 1.0000 0.0052
-14.250 -1.1313 0.03310 0.02886 -0.0604 1.0000 0.0053
-14.000 -1.1261 0.03139 0.02705 -0.0600 1.0000 0.0054
-13.750 -1.1192 0.02986 0.02545 -0.0594 1.0000 0.0056
-13.500 -1.1146 0.02822 0.02372 -0.0587 1.0000 0.0056
-13.250 -1.1071 0.02691 0.02233 -0.0578 1.0000 0.0058
-13.000 -1.1017 0.02555 0.02089 -0.0567 1.0000 0.0058
-12.750 -1.0958 0.02438 0.01964 -0.0552 1.0000 0.0059
-12.500 -1.0916 0.02329 0.01847 -0.0533 1.0000 0.0060
-12.250 -1.0900 0.02237 0.01749 -0.0507 1.0000 0.0060
-12.000 -1.0989 0.02159 0.01665 -0.0459 1.0000 0.0061
-11.750 -1.0810 0.02049 0.01546 -0.0461 0.9988 0.0063
-11.500 -1.0554 0.01948 0.01438 -0.0474 0.9967 0.0066
-11.250 -1.0287 0.01871 0.01356 -0.0486 0.9947 0.0069
-11.000 -1.0031 0.01805 0.01286 -0.0494 0.9925 0.0072
-10.750 -0.9774 0.01738 0.01214 -0.0501 0.9899 0.0075
-10.500 -0.9503 0.01674 0.01144 -0.0511 0.9876 0.0078
-10.250 -0.9218 0.01615 0.01078 -0.0522 0.9856 0.0082
-10.000 -0.8926 0.01555 0.01013 -0.0535 0.9841 0.0084
-9.750 -0.8652 0.01502 0.00954 -0.0542 0.9818 0.0087
-9.500 -0.8405 0.01437 0.00885 -0.0545 0.9780 0.0093
-9.250 -0.8122 0.01387 0.00833 -0.0554 0.9754 0.0099
-9.000 -0.7822 0.01340 0.00782 -0.0565 0.9733 0.0105
-8.500 -0.7188 0.01256 0.00691 -0.0594 0.9701 0.0117
-8.250 -0.6941 0.01213 0.00646 -0.0594 0.9648 0.0128
-8.000 -0.6646 0.01174 0.00606 -0.0603 0.9612 0.0139
-7.750 -0.6338 0.01139 0.00567 -0.0614 0.9581 0.0150
-7.500 -0.6041 0.01107 0.00532 -0.0622 0.9544 0.0160
-7.250 -0.5772 0.01072 0.00496 -0.0625 0.9488 0.0179
-7.000 -0.5480 0.01041 0.00463 -0.0632 0.9441 0.0199
-6.750 -0.5199 0.01014 0.00434 -0.0636 0.9390 0.0221
-6.500 -0.4929 0.00985 0.00405 -0.0638 0.9326 0.0253
-6.250 -0.4645 0.00962 0.00379 -0.0642 0.9273 0.0281
-6.000 -0.4382 0.00935 0.00353 -0.0642 0.9207 0.0335
-5.750 -0.4109 0.00911 0.00329 -0.0643 0.9142 0.0401
-5.500 -0.3840 0.00890 0.00308 -0.0644 0.9080 0.0469
-5.000 -0.3304 0.00840 0.00264 -0.0645 0.8950 0.0737
-4.750 -0.3038 0.00814 0.00244 -0.0645 0.8879 0.0935
-4.500 -0.2772 0.00785 0.00223 -0.0646 0.8816 0.1220
-4.250 -0.2509 0.00751 0.00201 -0.0646 0.8748 0.1599
-3.750 -0.2005 0.00633 0.00142 -0.0647 0.8612 0.3289
-3.500 -0.1748 0.00582 0.00122 -0.0647 0.8545 0.4216
-3.250 -0.1472 0.00566 0.00115 -0.0649 0.8483 0.4590
-3.000 -0.1193 0.00559 0.00110 -0.0650 0.8417 0.4782
-2.750 -0.0911 0.00555 0.00106 -0.0651 0.8357 0.4931
-2.500 -0.0629 0.00551 0.00103 -0.0652 0.8292 0.5060
-2.250 -0.0348 0.00549 0.00101 -0.0653 0.8231 0.5219
-2.000 -0.0063 0.00548 0.00100 -0.0655 0.8165 0.5318
-1.500 0.0503 0.00547 0.00095 -0.0657 0.8039 0.5379
-1.250 0.0786 0.00547 0.00093 -0.0658 0.7972 0.5410
-1.000 0.1070 0.00548 0.00092 -0.0660 0.7909 0.5437
-0.750 0.1353 0.00550 0.00091 -0.0661 0.7836 0.5462
-0.500 0.1633 0.00550 0.00091 -0.0661 0.7754 0.5489
0.000 0.2189 0.00555 0.00092 -0.0661 0.7535 0.5553
0.250 0.2465 0.00560 0.00093 -0.0660 0.7401 0.5583
0.750 0.3008 0.00572 0.00097 -0.0657 0.7072 0.5638
1.000 0.3271 0.00582 0.00100 -0.0654 0.6807 0.5670
1.250 0.3509 0.00605 0.00105 -0.0646 0.6290 0.5704
1.500 0.3733 0.00643 0.00114 -0.0635 0.5530 0.5738
1.750 0.3944 0.00697 0.00131 -0.0623 0.4576 0.5768
2.000 0.4161 0.00751 0.00152 -0.0613 0.3667 0.5800
2.250 0.4387 0.00801 0.00172 -0.0605 0.2860 0.5834
2.500 0.4615 0.00850 0.00193 -0.0598 0.2119 0.5869
2.750 0.4856 0.00890 0.00212 -0.0592 0.1584 0.5902
3.000 0.5097 0.00928 0.00233 -0.0587 0.1108 0.5941
3.250 0.5348 0.00957 0.00252 -0.0582 0.0811 0.5982
3.500 0.5603 0.00984 0.00271 -0.0579 0.0611 0.6023
3.750 0.5862 0.01006 0.00289 -0.0576 0.0491 0.6059
4.000 0.6120 0.01027 0.00309 -0.0573 0.0404 0.6098
4.250 0.6380 0.01047 0.00329 -0.0570 0.0349 0.6142
4.500 0.6639 0.01069 0.00349 -0.0567 0.0303 0.6187
4.750 0.6898 0.01089 0.00371 -0.0565 0.0272 0.6232
5.000 0.7152 0.01113 0.00396 -0.0561 0.0237 0.6282
5.250 0.7411 0.01133 0.00419 -0.0558 0.0219 0.6330
5.500 0.7664 0.01158 0.00444 -0.0554 0.0198 0.6375
5.750 0.7914 0.01185 0.00474 -0.0549 0.0179 0.6426
6.000 0.8167 0.01208 0.00501 -0.0546 0.0169 0.6480
6.250 0.8417 0.01234 0.00530 -0.0541 0.0157 0.6534
6.500 0.8662 0.01263 0.00562 -0.0536 0.0143 0.6595
7.000 0.9150 0.01324 0.00631 -0.0525 0.0126 0.6711
7.250 0.9391 0.01355 0.00666 -0.0520 0.0120 0.6773
7.500 0.9630 0.01387 0.00704 -0.0514 0.0113 0.6833
7.750 0.9863 0.01424 0.00744 -0.0507 0.0107 0.6906
8.000 1.0087 0.01471 0.00796 -0.0499 0.0099 0.6974
8.250 1.0318 0.01507 0.00839 -0.0492 0.0097 0.7049
8.500 1.0548 0.01544 0.00883 -0.0484 0.0093 0.7118
8.750 1.0774 0.01582 0.00929 -0.0477 0.0089 0.7195
9.000 1.0998 0.01621 0.00973 -0.0469 0.0085 0.7273
9.250 1.1217 0.01663 0.01022 -0.0460 0.0081 0.7363
9.500 1.1427 0.01711 0.01077 -0.0450 0.0078 0.7453
10.000 1.1815 0.01834 0.01217 -0.0425 0.0071 0.7646
10.250 1.2015 0.01883 0.01276 -0.0414 0.0070 0.7751
10.500 1.2206 0.01937 0.01341 -0.0401 0.0069 0.7870
10.750 1.2383 0.01991 0.01406 -0.0386 0.0067 0.8011
11.000 1.2539 0.02050 0.01476 -0.0367 0.0065 0.8168
11.250 1.2686 0.02110 0.01550 -0.0347 0.0064 0.8350
11.500 1.2821 0.02172 0.01626 -0.0325 0.0062 0.8589
11.750 1.2938 0.02219 0.01692 -0.0300 0.0061 0.9020
12.000 1.3072 0.02286 0.01779 -0.0280 0.0060 1.0000
12.250 1.3213 0.02359 0.01858 -0.0262 0.0058 1.0000
12.500 1.3336 0.02444 0.01951 -0.0243 0.0057 1.0000
12.750 1.3456 0.02532 0.02045 -0.0225 0.0055 1.0000
13.000 1.3562 0.02629 0.02151 -0.0206 0.0054 1.0000
13.250 1.3649 0.02743 0.02274 -0.0185 0.0053 1.0000
13.500 1.3719 0.02870 0.02411 -0.0165 0.0052 1.0000
13.750 1.3751 0.03031 0.02584 -0.0142 0.0051 1.0000
14.000 1.3772 0.03203 0.02769 -0.0121 0.0050 1.0000
14.250 1.3780 0.03392 0.02972 -0.0101 0.0049 1.0000
14.500 1.3822 0.03558 0.03149 -0.0086 0.0049 1.0000
14.750 1.3853 0.03739 0.03343 -0.0072 0.0048 1.0000
15.000 1.3851 0.03960 0.03576 -0.0060 0.0048 1.0000
15.250 1.3836 0.04202 0.03832 -0.0049 0.0048 1.0000
15.500 1.3828 0.04451 0.04093 -0.0043 0.0047 1.0000
15.750 1.3759 0.04779 0.04436 -0.0039 0.0047 1.0000
16.000 1.3678 0.05144 0.04815 -0.0040 0.0047 1.0000
16.250 1.3627 0.05497 0.05180 -0.0046 0.0046 1.0000
16.500 1.3467 0.06024 0.05725 -0.0061 0.0046 1.0000
16.750 1.3327 0.06574 0.06291 -0.0083 0.0045 1.0000
17.000 1.3124 0.07290 0.07023 -0.0120 0.0046 1.0000
17.250 1.2860 0.08216 0.07969 -0.0175 0.0045 1.0000
17.500 1.2442 0.09615 0.09392 -0.0266 0.0046 1.0000
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