RAF 69 AIRFOIL (raf69-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: RAF 69 AIRFOIL (raf69-il) Reynolds number: 200,000 Max Cl/Cd: 51.71 at α=8° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-raf69-il-200000-n5.txt Download as CSV file: xf-raf69-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: RAF 69 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
------ -------- --------- --------- -------- -------- --------
-19.750 -0.8885 0.10688 0.10137 -0.0595 1.0000 0.0661
-19.500 -0.9021 0.10138 0.09572 -0.0622 1.0000 0.0674
-19.250 -0.9126 0.09647 0.09068 -0.0646 1.0000 0.0687
-19.000 -0.9117 0.09353 0.08777 -0.0658 1.0000 0.0699
-18.750 -0.9159 0.08977 0.08396 -0.0675 1.0000 0.0712
-18.500 -0.9214 0.08583 0.07994 -0.0692 1.0000 0.0725
-18.250 -0.9276 0.08181 0.07582 -0.0709 1.0000 0.0740
-18.000 -0.9335 0.07790 0.07179 -0.0725 1.0000 0.0754
-17.750 -0.9368 0.07450 0.06831 -0.0738 1.0000 0.0767
-17.500 -0.9381 0.07147 0.06528 -0.0748 1.0000 0.0780
-17.250 -0.9410 0.06824 0.06201 -0.0759 1.0000 0.0794
-17.000 -0.9440 0.06503 0.05873 -0.0769 1.0000 0.0810
-16.750 -0.9464 0.06195 0.05556 -0.0779 1.0000 0.0828
-16.500 -0.9478 0.05906 0.05254 -0.0786 1.0000 0.0844
-16.250 -0.9484 0.05643 0.04990 -0.0791 1.0000 0.0859
-16.000 -0.9498 0.05378 0.04723 -0.0795 1.0000 0.0875
-15.750 -0.9506 0.05124 0.04465 -0.0799 1.0000 0.0892
-15.500 -0.9505 0.04887 0.04221 -0.0800 1.0000 0.0911
-15.250 -0.9493 0.04668 0.03993 -0.0800 1.0000 0.0931
-15.000 -0.9483 0.04461 0.03781 -0.0797 1.0000 0.0948
-14.750 -0.9495 0.04246 0.03566 -0.0793 1.0000 0.0967
-14.500 -0.9494 0.04050 0.03368 -0.0788 1.0000 0.0988
-14.250 -0.9481 0.03874 0.03186 -0.0780 1.0000 0.1010
-14.000 -0.9455 0.03718 0.03023 -0.0771 1.0000 0.1033
-13.750 -0.9443 0.03564 0.02866 -0.0758 1.0000 0.1054
-13.500 -0.9460 0.03407 0.02710 -0.0742 1.0000 0.1076
-13.250 -0.9472 0.03271 0.02573 -0.0723 1.0000 0.1100
-13.000 -0.9486 0.03156 0.02455 -0.0700 1.0000 0.1126
-12.750 -0.9475 0.03055 0.02349 -0.0679 0.9995 0.1153
-12.500 -0.9255 0.02896 0.02191 -0.0700 0.9898 0.1193
-12.250 -0.9036 0.02769 0.02060 -0.0717 0.9811 0.1238
-11.750 -0.8581 0.02547 0.01831 -0.0746 0.9635 0.1337
-11.500 -0.8316 0.02454 0.01731 -0.0763 0.9553 0.1396
-11.250 -0.8037 0.02360 0.01634 -0.0783 0.9477 0.1452
-11.000 -0.7756 0.02276 0.01546 -0.0801 0.9393 0.1513
-10.750 -0.7456 0.02206 0.01467 -0.0819 0.9309 0.1576
-10.500 -0.7176 0.02129 0.01389 -0.0835 0.9215 0.1640
-10.250 -0.6894 0.02073 0.01323 -0.0846 0.9113 0.1707
-10.000 -0.6623 0.02010 0.01258 -0.0857 0.9017 0.1765
-9.750 -0.6411 0.01963 0.01206 -0.0853 0.8903 0.1823
-9.500 -0.6149 0.01921 0.01152 -0.0857 0.8811 0.1882
-9.250 -0.6004 0.01878 0.01109 -0.0840 0.8691 0.1934
-9.000 -0.5806 0.01842 0.01066 -0.0830 0.8598 0.1993
-8.750 -0.5636 0.01814 0.01029 -0.0813 0.8498 0.2046
-8.500 -0.5472 0.01777 0.00990 -0.0796 0.8415 0.2101
-8.250 -0.5331 0.01752 0.00961 -0.0774 0.8316 0.2160
-8.000 -0.5146 0.01729 0.00929 -0.0758 0.8238 0.2215
-7.750 -0.5016 0.01704 0.00906 -0.0733 0.8155 0.2273
-7.500 -0.4852 0.01686 0.00882 -0.0713 0.8075 0.2338
-7.250 -0.4663 0.01664 0.00854 -0.0698 0.8008 0.2400
-7.000 -0.4502 0.01642 0.00834 -0.0677 0.7926 0.2463
-6.750 -0.4298 0.01624 0.00808 -0.0664 0.7857 0.2533
-6.500 -0.4107 0.01601 0.00785 -0.0649 0.7792 0.2596
-6.250 -0.3921 0.01583 0.00766 -0.0632 0.7714 0.2669
-6.000 -0.3707 0.01564 0.00742 -0.0620 0.7648 0.2741
-5.750 -0.3513 0.01544 0.00723 -0.0605 0.7577 0.2818
-5.500 -0.3303 0.01530 0.00704 -0.0592 0.7501 0.2899
-5.250 -0.3093 0.01509 0.00683 -0.0580 0.7438 0.2981
-5.000 -0.2884 0.01494 0.00668 -0.0567 0.7368 0.3073
-4.750 -0.2680 0.01476 0.00652 -0.0553 0.7298 0.3164
-4.500 -0.2448 0.01462 0.00633 -0.0544 0.7241 0.3266
-4.250 -0.2243 0.01446 0.00621 -0.0530 0.7176 0.3366
-4.000 -0.2024 0.01434 0.00609 -0.0518 0.7109 0.3478
-3.750 -0.1800 0.01419 0.00594 -0.0508 0.7051 0.3594
-3.500 -0.1579 0.01407 0.00584 -0.0497 0.6991 0.3709
-3.250 -0.1359 0.01396 0.00575 -0.0485 0.6923 0.3839
-3.000 -0.1133 0.01383 0.00564 -0.0474 0.6865 0.3971
-2.750 -0.0904 0.01373 0.00556 -0.0464 0.6807 0.4101
-2.500 -0.0680 0.01365 0.00550 -0.0453 0.6736 0.4234
-2.250 -0.0451 0.01355 0.00542 -0.0443 0.6675 0.4375
-2.000 -0.0217 0.01347 0.00536 -0.0434 0.6619 0.4516
-1.750 0.0006 0.01340 0.00533 -0.0422 0.6547 0.4654
-1.500 0.0242 0.01334 0.00527 -0.0413 0.6482 0.4792
-1.250 0.0478 0.01327 0.00523 -0.0404 0.6422 0.4931
-1.000 0.0704 0.01323 0.00523 -0.0393 0.6351 0.5068
-0.750 0.0943 0.01319 0.00519 -0.0384 0.6285 0.5213
-0.500 0.1176 0.01314 0.00518 -0.0374 0.6219 0.5351
-0.250 0.1403 0.01311 0.00520 -0.0363 0.6143 0.5484
0.000 0.1645 0.01309 0.00517 -0.0355 0.6078 0.5630
0.250 0.1872 0.01307 0.00521 -0.0343 0.6006 0.5773
0.500 0.2100 0.01305 0.00524 -0.0332 0.5928 0.5916
0.750 0.2337 0.01306 0.00524 -0.0323 0.5859 0.6064
1.000 0.2557 0.01307 0.00530 -0.0310 0.5777 0.6218
1.250 0.2787 0.01308 0.00534 -0.0299 0.5701 0.6368
1.500 0.3010 0.01310 0.00542 -0.0287 0.5622 0.6515
1.750 0.3233 0.01314 0.00548 -0.0275 0.5539 0.6660
2.000 0.3455 0.01320 0.00554 -0.0263 0.5461 0.6809
2.250 0.3671 0.01325 0.00565 -0.0249 0.5372 0.6941
2.500 0.3892 0.01333 0.00570 -0.0236 0.5292 0.7073
2.750 0.4096 0.01340 0.00580 -0.0221 0.5198 0.7206
3.000 0.4312 0.01349 0.00587 -0.0207 0.5116 0.7327
3.250 0.4511 0.01357 0.00599 -0.0191 0.5023 0.7450
3.500 0.4716 0.01367 0.00606 -0.0176 0.4942 0.7573
3.750 0.4917 0.01376 0.00619 -0.0160 0.4857 0.7686
4.000 0.5109 0.01387 0.00628 -0.0143 0.4778 0.7807
4.250 0.5314 0.01397 0.00642 -0.0128 0.4701 0.7913
4.500 0.5502 0.01409 0.00654 -0.0111 0.4620 0.8027
4.750 0.5699 0.01421 0.00667 -0.0095 0.4548 0.8141
5.000 0.5885 0.01432 0.00683 -0.0077 0.4472 0.8254
5.250 0.6064 0.01446 0.00696 -0.0058 0.4397 0.8380
5.500 0.6281 0.01461 0.00717 -0.0047 0.4322 0.8503
5.750 0.6504 0.01481 0.00741 -0.0038 0.4245 0.8637
6.000 0.6762 0.01506 0.00767 -0.0036 0.4171 0.8782
6.250 0.7076 0.01535 0.00802 -0.0046 0.4084 0.8922
6.500 0.7410 0.01571 0.00836 -0.0061 0.4000 0.9062
6.750 0.7764 0.01605 0.00876 -0.0081 0.3904 0.9205
7.000 0.8112 0.01646 0.00915 -0.0101 0.3812 0.9346
7.250 0.8465 0.01686 0.00958 -0.0122 0.3703 0.9476
7.500 0.8805 0.01730 0.01001 -0.0142 0.3597 0.9600
7.750 0.9116 0.01774 0.01044 -0.0157 0.3495 0.9739
8.000 0.9416 0.01821 0.01091 -0.0170 0.3396 0.9881
8.250 0.9648 0.01877 0.01144 -0.0171 0.3302 1.0000
8.500 0.9682 0.01912 0.01176 -0.0134 0.3229 1.0000
8.750 0.9732 0.01955 0.01217 -0.0100 0.3152 1.0000
9.000 0.9795 0.02006 0.01264 -0.0070 0.3079 1.0000
9.250 0.9873 0.02059 0.01317 -0.0043 0.2996 1.0000
9.500 0.9940 0.02123 0.01376 -0.0016 0.2924 1.0000
9.750 1.0035 0.02184 0.01439 0.0006 0.2843 1.0000
10.250 1.0201 0.02332 0.01584 0.0050 0.2692 1.0000
10.500 1.0277 0.02417 0.01666 0.0070 0.2622 1.0000
10.750 1.0372 0.02500 0.01749 0.0088 0.2552 1.0000
11.000 1.0454 0.02593 0.01842 0.0106 0.2481 1.0000
11.250 1.0531 0.02693 0.01941 0.0123 0.2417 1.0000
11.500 1.0625 0.02790 0.02040 0.0137 0.2348 1.0000
11.750 1.0691 0.02906 0.02153 0.0153 0.2289 1.0000
12.000 1.0788 0.03009 0.02260 0.0166 0.2229 1.0000
12.250 1.0869 0.03125 0.02378 0.0179 0.2171 1.0000
12.500 1.0927 0.03260 0.02510 0.0192 0.2117 1.0000
12.750 1.1027 0.03374 0.02631 0.0202 0.2061 1.0000
13.000 1.1094 0.03513 0.02771 0.0212 0.2006 1.0000
13.250 1.1150 0.03663 0.02919 0.0223 0.1957 1.0000
13.500 1.1241 0.03795 0.03059 0.0231 0.1906 1.0000
13.750 1.1309 0.03947 0.03213 0.0239 0.1859 1.0000
14.000 1.1357 0.04115 0.03380 0.0247 0.1816 1.0000
14.250 1.1439 0.04266 0.03538 0.0253 0.1774 1.0000
14.500 1.1510 0.04428 0.03705 0.0258 0.1730 1.0000
14.750 1.1553 0.04616 0.03895 0.0264 0.1686 1.0000
15.000 1.1592 0.04811 0.04090 0.0268 0.1644 1.0000
15.250 1.1650 0.04999 0.04287 0.0271 0.1596 1.0000
15.500 1.1685 0.05210 0.04501 0.0274 0.1552 1.0000
15.750 1.1703 0.05439 0.04729 0.0276 0.1514 1.0000
16.000 1.1754 0.05643 0.04940 0.0277 0.1479 1.0000
16.250 1.1795 0.05861 0.05166 0.0277 0.1440 1.0000
16.500 1.1808 0.06112 0.05420 0.0277 0.1401 1.0000
16.750 1.1823 0.06362 0.05670 0.0276 0.1371 1.0000
17.000 1.1853 0.06604 0.05920 0.0274 0.1336 1.0000
17.250 1.1877 0.06857 0.06182 0.0271 0.1303 1.0000
17.500 1.1887 0.07127 0.06457 0.0268 0.1271 1.0000
17.750 1.1879 0.07420 0.06751 0.0263 0.1241 1.0000
18.000 1.1884 0.07704 0.07042 0.0258 0.1211 1.0000
18.250 1.1885 0.08001 0.07349 0.0252 0.1178 1.0000
18.500 1.1874 0.08313 0.07668 0.0244 0.1148 1.0000
18.750 1.1856 0.08633 0.07991 0.0237 0.1121 1.0000
19.000 1.1843 0.08950 0.08312 0.0229 0.1096 1.0000
19.250 1.1830 0.09279 0.08654 0.0219 0.1068 1.0000
|
Polar data table (+)
Polar graphs
<< Back to RAF 69 AIRFOIL (raf69-il)