RAE6-9CK AIRFOIL (rae69ck-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: RAE6-9CK AIRFOIL (rae69ck-il) Reynolds number: 100,000 Max Cl/Cd: 37.54 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-rae69ck-il-100000-n5.txt Download as CSV file: xf-rae69ck-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.500 -0.6530 0.08807 0.08258 -0.0487 1.0000 0.0263
-12.250 -0.6780 0.08008 0.07451 -0.0536 1.0000 0.0259
-12.000 -0.7023 0.07341 0.06773 -0.0573 1.0000 0.0257
-11.750 -0.7253 0.06775 0.06192 -0.0598 1.0000 0.0256
-11.500 -0.7463 0.06297 0.05698 -0.0611 1.0000 0.0255
-11.250 -0.7654 0.05890 0.05273 -0.0615 1.0000 0.0255
-11.000 -0.7830 0.05542 0.04907 -0.0608 1.0000 0.0255
-10.750 -0.8005 0.05243 0.04587 -0.0589 1.0000 0.0256
-10.500 -0.8166 0.04994 0.04321 -0.0559 1.0000 0.0257
-10.250 -0.8274 0.04719 0.04019 -0.0530 1.0000 0.0260
-10.000 -0.8325 0.04460 0.03729 -0.0503 1.0000 0.0263
-9.750 -0.8342 0.04214 0.03447 -0.0476 1.0000 0.0270
-9.500 -0.8320 0.03987 0.03189 -0.0452 1.0000 0.0279
-9.250 -0.8242 0.03816 0.03011 -0.0433 1.0000 0.0291
-9.000 -0.8151 0.03658 0.02839 -0.0414 1.0000 0.0301
-8.750 -0.8042 0.03489 0.02651 -0.0394 1.0000 0.0312
-8.500 -0.7915 0.03314 0.02455 -0.0375 1.0000 0.0324
-8.250 -0.7774 0.03153 0.02274 -0.0356 1.0000 0.0337
-8.000 -0.7628 0.03028 0.02123 -0.0337 1.0000 0.0356
-7.750 -0.7496 0.02886 0.01983 -0.0319 1.0000 0.0377
-7.500 -0.7359 0.02782 0.01875 -0.0301 1.0000 0.0402
-7.250 -0.7214 0.02673 0.01758 -0.0282 1.0000 0.0424
-7.000 -0.7067 0.02574 0.01647 -0.0263 1.0000 0.0450
-6.750 -0.6935 0.02471 0.01545 -0.0245 1.0000 0.0488
-6.500 -0.6788 0.02386 0.01458 -0.0229 1.0000 0.0532
-6.000 -0.6480 0.02216 0.01279 -0.0200 1.0000 0.0642
-5.750 -0.6196 0.02126 0.01187 -0.0212 0.9966 0.0755
-5.500 -0.5892 0.02037 0.01101 -0.0228 0.9925 0.0940
-5.250 -0.5599 0.01935 0.01015 -0.0244 0.9881 0.1282
-5.000 -0.5304 0.01787 0.00915 -0.0267 0.9842 0.2203
-4.750 -0.5066 0.01647 0.00902 -0.0275 0.9796 0.4487
-4.500 -0.4752 0.01662 0.00915 -0.0283 0.9748 0.5129
-4.250 -0.4412 0.01687 0.00926 -0.0295 0.9709 0.5472
-4.000 -0.4128 0.01715 0.00946 -0.0295 0.9654 0.5713
-3.750 -0.3827 0.01752 0.00978 -0.0296 0.9605 0.5938
-3.500 -0.3505 0.01805 0.01026 -0.0299 0.9568 0.6170
-3.250 -0.3247 0.01833 0.01049 -0.0292 0.9508 0.6311
-3.000 -0.2929 0.01824 0.01028 -0.0303 0.9462 0.6372
-2.750 -0.2585 0.01817 0.01009 -0.0319 0.9429 0.6409
-2.500 -0.2297 0.01805 0.00986 -0.0325 0.9374 0.6453
-2.250 -0.1982 0.01790 0.00958 -0.0338 0.9324 0.6504
-2.000 -0.1642 0.01784 0.00948 -0.0352 0.9289 0.6535
-1.750 -0.1343 0.01778 0.00935 -0.0359 0.9240 0.6572
-1.500 -0.1048 0.01770 0.00921 -0.0366 0.9184 0.6620
-1.250 -0.0703 0.01761 0.00907 -0.0383 0.9148 0.6663
-1.000 -0.0377 0.01757 0.00901 -0.0394 0.9109 0.6696
-0.750 -0.0115 0.01755 0.00899 -0.0394 0.9043 0.6738
-0.500 0.0232 0.01747 0.00888 -0.0411 0.9005 0.6791
-0.250 0.0597 0.01741 0.00884 -0.0429 0.8978 0.6828
0.000 0.0821 0.01744 0.00891 -0.0421 0.8899 0.6867
0.250 0.1165 0.01739 0.00888 -0.0436 0.8859 0.6916
0.500 0.1531 0.01732 0.00885 -0.0455 0.8831 0.6964
0.750 0.1751 0.01739 0.00900 -0.0445 0.8747 0.7006
1.000 0.2094 0.01733 0.00900 -0.0459 0.8705 0.7056
1.250 0.2386 0.01732 0.00907 -0.0464 0.8643 0.7108
1.500 0.2679 0.01731 0.00917 -0.0466 0.8579 0.7153
1.750 0.3047 0.01718 0.00915 -0.0483 0.8539 0.7208
2.000 0.3289 0.01721 0.00930 -0.0477 0.8442 0.7265
2.250 0.3656 0.01703 0.00926 -0.0490 0.8391 0.7313
2.500 0.3918 0.01699 0.00934 -0.0486 0.8281 0.7375
2.750 0.4220 0.01679 0.00930 -0.0486 0.8168 0.7430
3.000 0.4540 0.01643 0.00910 -0.0485 0.8013 0.7492
3.250 0.4864 0.01584 0.00859 -0.0480 0.7731 0.7556
3.500 0.5156 0.01535 0.00814 -0.0468 0.7339 0.7614
3.750 0.5418 0.01515 0.00796 -0.0456 0.6887 0.7689
4.000 0.5658 0.01508 0.00784 -0.0439 0.6219 0.7751
4.250 0.5853 0.01559 0.00763 -0.0415 0.4659 0.7831
4.500 0.5924 0.01696 0.00809 -0.0378 0.2941 0.7903
4.750 0.6043 0.01835 0.00878 -0.0356 0.1644 0.7991
5.000 0.6203 0.01934 0.00947 -0.0338 0.1095 0.8074
5.250 0.6385 0.02015 0.01019 -0.0322 0.0864 0.8169
5.500 0.6572 0.02092 0.01097 -0.0307 0.0740 0.8277
5.750 0.6747 0.02166 0.01175 -0.0290 0.0647 0.8384
6.000 0.6925 0.02241 0.01266 -0.0271 0.0588 0.8506
6.250 0.7101 0.02318 0.01350 -0.0254 0.0536 0.8647
6.500 0.7277 0.02407 0.01449 -0.0237 0.0490 0.8814
6.750 0.7474 0.02499 0.01557 -0.0222 0.0457 0.9022
7.000 0.7704 0.02603 0.01668 -0.0216 0.0425 0.9320
7.250 0.8001 0.02750 0.01826 -0.0226 0.0391 1.0000
7.500 0.8280 0.02904 0.01998 -0.0229 0.0365 1.0000
7.750 0.8551 0.03084 0.02194 -0.0232 0.0346 1.0000
8.000 0.8792 0.03248 0.02369 -0.0232 0.0327 1.0000
8.250 0.9017 0.03466 0.02597 -0.0231 0.0309 1.0000
8.500 0.9216 0.03679 0.02855 -0.0221 0.0293 1.0000
8.750 0.9386 0.03952 0.03171 -0.0209 0.0283 1.0000
9.000 0.9514 0.04244 0.03504 -0.0193 0.0276 1.0000
9.250 0.9599 0.04555 0.03854 -0.0174 0.0270 1.0000
9.500 0.9645 0.04864 0.04200 -0.0152 0.0265 1.0000
9.750 0.9671 0.05143 0.04507 -0.0131 0.0259 1.0000
10.000 0.9718 0.05344 0.04721 -0.0114 0.0250 1.0000
10.250 0.9709 0.05575 0.04966 -0.0093 0.0244 1.0000
10.500 0.9654 0.05843 0.05250 -0.0070 0.0240 1.0000
10.750 0.9499 0.06183 0.05612 -0.0043 0.0237 1.0000
11.000 0.9314 0.06558 0.06012 -0.0024 0.0236 1.0000
11.250 0.9115 0.06984 0.06458 -0.0017 0.0236 1.0000
11.500 0.8913 0.07462 0.06955 -0.0022 0.0236 1.0000
11.750 0.8696 0.08023 0.07533 -0.0042 0.0237 1.0000
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