RAE6-9CK AIRFOIL (rae69ck-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: RAE6-9CK AIRFOIL (rae69ck-il) Reynolds number: 200,000 Max Cl/Cd: 49.1 at α=3.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-rae69ck-il-200000-n5.txt Download as CSV file: xf-rae69ck-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.500 -0.7179 0.08429 0.08026 -0.0480 1.0000 0.0142
-13.250 -0.7523 0.07422 0.07000 -0.0543 1.0000 0.0142
-13.000 -0.7788 0.06695 0.06257 -0.0582 1.0000 0.0139
-12.750 -0.8013 0.06101 0.05643 -0.0607 1.0000 0.0139
-12.500 -0.8201 0.05607 0.05127 -0.0623 1.0000 0.0139
-12.250 -0.8361 0.05181 0.04680 -0.0630 1.0000 0.0140
-12.000 -0.8496 0.04811 0.04287 -0.0629 1.0000 0.0141
-11.750 -0.8606 0.04490 0.03943 -0.0622 1.0000 0.0143
-11.500 -0.8692 0.04210 0.03639 -0.0609 1.0000 0.0145
-11.250 -0.8759 0.03965 0.03370 -0.0591 1.0000 0.0148
-11.000 -0.8811 0.03762 0.03145 -0.0567 1.0000 0.0151
-10.750 -0.8867 0.03592 0.02953 -0.0535 1.0000 0.0154
-10.500 -0.8882 0.03446 0.02783 -0.0504 1.0000 0.0158
-10.250 -0.8855 0.03289 0.02623 -0.0479 1.0000 0.0164
-10.000 -0.8798 0.03168 0.02492 -0.0455 1.0000 0.0168
-9.750 -0.8727 0.03060 0.02376 -0.0432 1.0000 0.0174
-9.500 -0.8644 0.02939 0.02243 -0.0408 1.0000 0.0179
-9.250 -0.8551 0.02821 0.02112 -0.0385 1.0000 0.0185
-9.000 -0.8448 0.02705 0.01984 -0.0363 1.0000 0.0191
-8.750 -0.8339 0.02597 0.01860 -0.0340 1.0000 0.0199
-8.500 -0.8220 0.02504 0.01752 -0.0319 1.0000 0.0207
-8.250 -0.7993 0.02377 0.01621 -0.0322 0.9979 0.0221
-8.000 -0.7700 0.02286 0.01525 -0.0337 0.9948 0.0238
-7.750 -0.7423 0.02187 0.01418 -0.0347 0.9915 0.0254
-7.500 -0.7139 0.02093 0.01309 -0.0358 0.9878 0.0272
-7.250 -0.6851 0.01986 0.01199 -0.0373 0.9845 0.0297
-7.000 -0.6564 0.01916 0.01125 -0.0384 0.9809 0.0330
-6.750 -0.6285 0.01844 0.01042 -0.0392 0.9765 0.0361
-6.500 -0.5988 0.01758 0.00954 -0.0406 0.9730 0.0412
-6.250 -0.5664 0.01693 0.00883 -0.0424 0.9705 0.0480
-6.000 -0.5406 0.01633 0.00821 -0.0426 0.9651 0.0561
-5.750 -0.5109 0.01571 0.00761 -0.0438 0.9612 0.0697
-5.500 -0.4790 0.01504 0.00702 -0.0454 0.9583 0.0919
-5.250 -0.4467 0.01428 0.00644 -0.0473 0.9558 0.1340
-5.000 -0.4235 0.01341 0.00587 -0.0475 0.9496 0.2021
-4.750 -0.3969 0.01187 0.00521 -0.0490 0.9457 0.3878
-4.500 -0.3637 0.01160 0.00519 -0.0504 0.9432 0.4750
-4.250 -0.3318 0.01156 0.00514 -0.0513 0.9399 0.5075
-4.000 -0.3034 0.01156 0.00509 -0.0515 0.9345 0.5296
-3.750 -0.2708 0.01157 0.00505 -0.0525 0.9311 0.5478
-3.500 -0.2371 0.01160 0.00507 -0.0536 0.9285 0.5650
-3.250 -0.2080 0.01172 0.00518 -0.0537 0.9239 0.5824
-3.000 -0.1786 0.01172 0.00513 -0.0540 0.9188 0.5925
-2.750 -0.1457 0.01162 0.00498 -0.0551 0.9154 0.5957
-2.500 -0.1114 0.01151 0.00481 -0.0566 0.9128 0.5993
-2.250 -0.0845 0.01145 0.00468 -0.0565 0.9064 0.6033
-2.000 -0.0532 0.01136 0.00455 -0.0573 0.9020 0.6065
-1.750 -0.0200 0.01126 0.00444 -0.0584 0.8988 0.6093
-1.500 0.0079 0.01122 0.00438 -0.0585 0.8930 0.6129
-1.250 0.0382 0.01116 0.00429 -0.0590 0.8878 0.6168
-1.000 0.0708 0.01107 0.00418 -0.0601 0.8841 0.6205
-0.750 0.0985 0.01104 0.00418 -0.0601 0.8781 0.6234
-0.500 0.1281 0.01099 0.00415 -0.0605 0.8726 0.6269
-0.250 0.1602 0.01093 0.00409 -0.0613 0.8687 0.6311
0.000 0.1871 0.01093 0.00410 -0.0612 0.8617 0.6353
0.250 0.2170 0.01088 0.00411 -0.0616 0.8564 0.6383
0.500 0.2463 0.01086 0.00413 -0.0619 0.8508 0.6420
0.750 0.2744 0.01085 0.00417 -0.0619 0.8438 0.6463
1.000 0.3052 0.01081 0.00415 -0.0625 0.8382 0.6508
1.250 0.3316 0.01081 0.00423 -0.0621 0.8291 0.6545
1.500 0.3606 0.01078 0.00425 -0.0622 0.8206 0.6588
1.750 0.3896 0.01073 0.00425 -0.0623 0.8099 0.6635
2.000 0.4170 0.01068 0.00425 -0.0619 0.7954 0.6675
2.250 0.4428 0.01061 0.00421 -0.0610 0.7717 0.6720
2.500 0.4688 0.01057 0.00409 -0.0601 0.7357 0.6773
2.750 0.4935 0.01061 0.00408 -0.0591 0.6978 0.6820
3.000 0.5179 0.01072 0.00412 -0.0581 0.6549 0.6867
3.250 0.5396 0.01099 0.00415 -0.0566 0.5831 0.6920
3.500 0.5532 0.01175 0.00433 -0.0537 0.4535 0.6971
3.750 0.5643 0.01283 0.00478 -0.0509 0.3149 0.7024
4.000 0.5795 0.01385 0.00527 -0.0490 0.2019 0.7087
4.250 0.5973 0.01469 0.00576 -0.0475 0.1243 0.7141
4.500 0.6180 0.01531 0.00625 -0.0465 0.0866 0.7203
4.750 0.6399 0.01585 0.00672 -0.0456 0.0666 0.7265
5.000 0.6620 0.01632 0.00723 -0.0446 0.0560 0.7330
5.250 0.6841 0.01686 0.00779 -0.0437 0.0487 0.7404
5.500 0.7058 0.01734 0.00836 -0.0427 0.0429 0.7474
5.750 0.7265 0.01798 0.00906 -0.0415 0.0392 0.7553
6.000 0.7478 0.01851 0.00971 -0.0404 0.0358 0.7629
6.250 0.7688 0.01910 0.01034 -0.0394 0.0325 0.7713
6.500 0.7880 0.01990 0.01123 -0.0380 0.0303 0.7805
6.750 0.8084 0.02061 0.01209 -0.0367 0.0285 0.7899
7.000 0.8289 0.02135 0.01294 -0.0356 0.0267 0.8004
7.250 0.8489 0.02202 0.01368 -0.0344 0.0250 0.8116
7.500 0.8680 0.02305 0.01479 -0.0332 0.0234 0.8234
7.750 0.8887 0.02397 0.01590 -0.0320 0.0223 0.8370
8.000 0.9090 0.02502 0.01715 -0.0307 0.0212 0.8527
8.250 0.9285 0.02608 0.01839 -0.0294 0.0202 0.8717
8.500 0.9461 0.02701 0.01949 -0.0278 0.0194 0.8980
8.750 0.9660 0.02789 0.02049 -0.0269 0.0185 0.9821
9.000 0.9867 0.02954 0.02232 -0.0263 0.0176 1.0000
9.250 1.0061 0.03125 0.02432 -0.0254 0.0167 1.0000
9.500 1.0229 0.03332 0.02671 -0.0242 0.0161 1.0000
9.750 1.0365 0.03549 0.02917 -0.0227 0.0156 1.0000
10.000 1.0470 0.03767 0.03163 -0.0209 0.0151 1.0000
10.250 1.0540 0.03995 0.03419 -0.0188 0.0148 1.0000
10.500 1.0561 0.04216 0.03664 -0.0161 0.0145 1.0000
10.750 1.0551 0.04436 0.03906 -0.0132 0.0143 1.0000
11.000 1.0506 0.04681 0.04173 -0.0103 0.0141 1.0000
11.250 1.0435 0.04940 0.04454 -0.0077 0.0140 1.0000
11.500 1.0336 0.05232 0.04766 -0.0055 0.0139 1.0000
11.750 1.0252 0.05506 0.05053 -0.0041 0.0136 1.0000
12.000 1.0068 0.05930 0.05503 -0.0031 0.0136 1.0000
12.250 0.9885 0.06380 0.05968 -0.0032 0.0135 1.0000
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