NACA 63(4)-221 (naca634221-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: NACA 63(4)-221 (naca634221-il) Reynolds number: 100,000 Max Cl/Cd: 34 at α=8° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca634221-il-100000-n5.txt Download as CSV file: xf-naca634221-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 63(4)-221
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
------ -------- --------- --------- -------- -------- --------
-19.250 -0.7929 0.13370 0.12761 -0.0236 1.0000 0.0542
-19.000 -0.8497 0.11852 0.11204 -0.0326 1.0000 0.0546
-18.750 -0.8767 0.10987 0.10310 -0.0375 1.0000 0.0554
-18.500 -0.8966 0.10274 0.09569 -0.0413 1.0000 0.0562
-18.250 -0.8911 0.10007 0.09303 -0.0425 1.0000 0.0574
-18.000 -0.8869 0.09723 0.09017 -0.0438 1.0000 0.0587
-17.750 -0.8888 0.09340 0.08623 -0.0456 1.0000 0.0599
-17.500 -0.8920 0.08940 0.08207 -0.0474 1.0000 0.0613
-17.250 -0.8962 0.08529 0.07776 -0.0492 1.0000 0.0627
-17.000 -0.8922 0.08249 0.07488 -0.0501 1.0000 0.0641
-16.750 -0.8831 0.08050 0.07291 -0.0507 1.0000 0.0655
-16.500 -0.8770 0.07807 0.07043 -0.0515 1.0000 0.0671
-16.250 -0.8719 0.07548 0.06774 -0.0523 1.0000 0.0689
-16.000 -0.8676 0.07278 0.06488 -0.0531 1.0000 0.0709
-15.750 -0.8568 0.07110 0.06325 -0.0533 1.0000 0.0727
-15.500 -0.8476 0.06923 0.06138 -0.0537 1.0000 0.0747
-15.250 -0.8388 0.06727 0.05936 -0.0540 1.0000 0.0769
-15.000 -0.8302 0.06526 0.05723 -0.0544 1.0000 0.0795
-14.750 -0.8207 0.06355 0.05560 -0.0546 1.0000 0.0820
-14.500 -0.8121 0.06170 0.05375 -0.0549 1.0000 0.0850
-14.250 -0.8029 0.05988 0.05185 -0.0551 1.0000 0.0886
-14.000 -0.7947 0.05809 0.05013 -0.0553 1.0000 0.0918
-13.750 -0.7869 0.05623 0.04828 -0.0555 1.0000 0.0958
-13.500 -0.7782 0.05449 0.04652 -0.0556 1.0000 0.1005
-13.250 -0.7725 0.05250 0.04459 -0.0558 1.0000 0.1052
-13.000 -0.7641 0.05077 0.04283 -0.0559 1.0000 0.1113
-12.750 -0.7596 0.04876 0.04091 -0.0561 1.0000 0.1172
-12.500 -0.7529 0.04698 0.03913 -0.0562 1.0000 0.1247
-12.250 -0.7486 0.04505 0.03727 -0.0562 1.0000 0.1326
-12.000 -0.7441 0.04323 0.03551 -0.0562 1.0000 0.1415
-11.750 -0.7394 0.04150 0.03382 -0.0562 1.0000 0.1516
-11.500 -0.7293 0.03950 0.03188 -0.0578 0.9591 0.1644
-11.250 -0.7124 0.03738 0.02976 -0.0608 0.9347 0.1806
-11.000 -0.7006 0.03543 0.02782 -0.0623 0.9144 0.1973
-10.750 -0.6948 0.03364 0.02606 -0.0626 0.8969 0.2147
-10.500 -0.6917 0.03204 0.02447 -0.0619 0.8818 0.2325
-10.250 -0.6905 0.03054 0.02302 -0.0606 0.8684 0.2515
-10.000 -0.6894 0.02917 0.02171 -0.0592 0.8559 0.2718
-9.750 -0.6877 0.02796 0.02054 -0.0574 0.8455 0.2927
-9.500 -0.6853 0.02687 0.01951 -0.0556 0.8345 0.3140
-9.250 -0.6808 0.02605 0.01874 -0.0536 0.8256 0.3347
-9.000 -0.6759 0.02536 0.01808 -0.0515 0.8158 0.3543
-8.750 -0.6738 0.02475 0.01743 -0.0488 0.8079 0.3716
-8.500 -0.6710 0.02430 0.01695 -0.0460 0.7987 0.3874
-8.250 -0.6623 0.02393 0.01647 -0.0437 0.7916 0.4030
-8.000 -0.6496 0.02368 0.01613 -0.0420 0.7843 0.4177
-7.750 -0.6287 0.02377 0.01619 -0.0409 0.7771 0.4299
-7.500 -0.6109 0.02367 0.01598 -0.0395 0.7713 0.4417
-7.250 -0.5956 0.02342 0.01560 -0.0382 0.7644 0.4536
-7.000 -0.5687 0.02368 0.01584 -0.0376 0.7579 0.4618
-6.750 -0.5541 0.02327 0.01522 -0.0362 0.7523 0.4727
-6.500 -0.5242 0.02359 0.01553 -0.0360 0.7468 0.4788
-6.250 -0.5033 0.02347 0.01532 -0.0352 0.7400 0.4874
-6.000 -0.4788 0.02349 0.01526 -0.0346 0.7346 0.4949
-5.750 -0.4523 0.02366 0.01534 -0.0340 0.7302 0.5026
-5.500 -0.4320 0.02349 0.01508 -0.0334 0.7236 0.5115
-5.250 -0.4031 0.02373 0.01531 -0.0331 0.7178 0.5164
-5.000 -0.3792 0.02357 0.01503 -0.0326 0.7130 0.5227
-4.750 -0.3579 0.02319 0.01449 -0.0321 0.7086 0.5295
-4.500 -0.3300 0.02335 0.01467 -0.0320 0.7023 0.5331
-4.250 -0.3039 0.02333 0.01459 -0.0317 0.6970 0.5377
-4.000 -0.2811 0.02299 0.01410 -0.0314 0.6926 0.5443
-3.750 -0.2559 0.02285 0.01387 -0.0311 0.6880 0.5491
-3.500 -0.2291 0.02296 0.01400 -0.0310 0.6821 0.5527
-3.250 -0.2031 0.02290 0.01390 -0.0308 0.6774 0.5572
-3.000 -0.1787 0.02261 0.01347 -0.0306 0.6733 0.5634
-2.750 -0.1528 0.02246 0.01323 -0.0305 0.6692 0.5678
-2.500 -0.1268 0.02258 0.01340 -0.0303 0.6631 0.5712
-2.250 -0.1005 0.02256 0.01334 -0.0301 0.6583 0.5753
-2.000 -0.0744 0.02238 0.01307 -0.0301 0.6545 0.5805
-1.750 -0.0481 0.02212 0.01268 -0.0303 0.6515 0.5860
-1.500 -0.0229 0.02229 0.01293 -0.0300 0.6457 0.5890
-1.250 0.0031 0.02234 0.01298 -0.0298 0.6407 0.5926
-1.000 0.0298 0.02225 0.01285 -0.0298 0.6366 0.5969
-0.750 0.0571 0.02204 0.01252 -0.0301 0.6333 0.6026
-0.500 0.0825 0.02210 0.01260 -0.0300 0.6288 0.6066
-0.250 0.1075 0.02226 0.01283 -0.0297 0.6238 0.6098
0.000 0.1338 0.02229 0.01286 -0.0296 0.6196 0.6137
0.250 0.1613 0.02221 0.01272 -0.0297 0.6161 0.6184
0.500 0.1901 0.02203 0.01243 -0.0302 0.6132 0.6243
0.750 0.2125 0.02233 0.01286 -0.0296 0.6075 0.6274
1.000 0.2374 0.02249 0.01308 -0.0293 0.6030 0.6313
1.250 0.2641 0.02253 0.01312 -0.0293 0.5993 0.6358
1.500 0.2927 0.02244 0.01298 -0.0297 0.5962 0.6411
1.750 0.3198 0.02248 0.01302 -0.0298 0.5927 0.6455
2.000 0.3407 0.02284 0.01351 -0.0290 0.5870 0.6492
2.250 0.3656 0.02301 0.01373 -0.0287 0.5828 0.6539
2.500 0.3932 0.02302 0.01373 -0.0289 0.5793 0.6595
2.750 0.4231 0.02295 0.01362 -0.0294 0.5764 0.6646
3.000 0.4440 0.02331 0.01410 -0.0286 0.5714 0.6683
3.250 0.4654 0.02363 0.01452 -0.0279 0.5662 0.6728
3.500 0.4917 0.02371 0.01463 -0.0279 0.5621 0.6785
3.750 0.5214 0.02367 0.01457 -0.0283 0.5589 0.6844
4.000 0.5473 0.02380 0.01477 -0.0280 0.5554 0.6885
4.250 0.5625 0.02437 0.01550 -0.0266 0.5489 0.6935
4.500 0.5874 0.02452 0.01569 -0.0265 0.5444 0.6994
4.750 0.6169 0.02448 0.01567 -0.0268 0.5409 0.7051
5.000 0.6467 0.02444 0.01566 -0.0268 0.5380 0.7097
5.250 0.6553 0.02523 0.01665 -0.0247 0.5305 0.7156
5.500 0.6802 0.02538 0.01684 -0.0247 0.5257 0.7224
5.750 0.7096 0.02530 0.01681 -0.0246 0.5222 0.7272
6.000 0.7312 0.02555 0.01716 -0.0238 0.5174 0.7327
6.250 0.7421 0.02619 0.01795 -0.0221 0.5103 0.7397
6.500 0.7693 0.02615 0.01796 -0.0219 0.5057 0.7457
6.750 0.8047 0.02577 0.01760 -0.0224 0.5020 0.7512
7.000 0.8027 0.02673 0.01875 -0.0191 0.4924 0.7586
7.250 0.8341 0.02636 0.01841 -0.0193 0.4864 0.7652
7.500 0.8457 0.02671 0.01888 -0.0171 0.4788 0.7717
7.750 0.8599 0.02699 0.01925 -0.0155 0.4711 0.7797
8.000 0.8980 0.02641 0.01868 -0.0162 0.4659 0.7859
8.250 0.8782 0.02773 0.02020 -0.0107 0.4563 0.7944
8.500 0.9106 0.02732 0.01980 -0.0110 0.4497 0.8024
8.750 0.8987 0.02867 0.02132 -0.0068 0.4402 0.8113
9.000 0.9249 0.02844 0.02112 -0.0064 0.4322 0.8204
9.250 0.9139 0.03001 0.02285 -0.0030 0.4218 0.8303
9.500 0.9435 0.02947 0.02231 -0.0026 0.4132 0.8400
9.750 0.9266 0.03161 0.02463 0.0006 0.4010 0.8522
10.000 0.9310 0.03256 0.02567 0.0024 0.3898 0.8645
10.250 0.9478 0.03266 0.02580 0.0037 0.3784 0.8780
10.500 0.9405 0.03456 0.02784 0.0057 0.3645 0.8964
10.750 0.9434 0.03596 0.02934 0.0068 0.3499 0.9208
11.000 0.9549 0.03701 0.03044 0.0064 0.3332 0.9834
11.250 0.9651 0.03831 0.03166 0.0064 0.3159 1.0000
11.500 0.9743 0.03974 0.03299 0.0065 0.2978 1.0000
11.750 0.9808 0.04141 0.03455 0.0066 0.2796 1.0000
12.000 0.9848 0.04335 0.03638 0.0068 0.2619 1.0000
12.250 0.9874 0.04550 0.03844 0.0069 0.2448 1.0000
12.500 0.9889 0.04783 0.04069 0.0069 0.2284 1.0000
12.750 0.9903 0.05027 0.04306 0.0068 0.2131 1.0000
13.000 0.9914 0.05282 0.04555 0.0067 0.1987 1.0000
13.250 0.9931 0.05539 0.04808 0.0064 0.1856 1.0000
13.500 0.9953 0.05796 0.05061 0.0061 0.1738 1.0000
13.750 0.9969 0.06064 0.05323 0.0057 0.1629 1.0000
14.000 0.9988 0.06336 0.05591 0.0053 0.1527 1.0000
14.250 1.0016 0.06608 0.05865 0.0048 0.1429 1.0000
14.500 1.0040 0.06885 0.06139 0.0042 0.1344 1.0000
14.750 1.0062 0.07172 0.06426 0.0035 0.1262 1.0000
15.000 1.0095 0.07452 0.06708 0.0029 0.1186 1.0000
15.250 1.0113 0.07751 0.07003 0.0021 0.1122 1.0000
15.500 1.0152 0.08034 0.07291 0.0013 0.1055 1.0000
15.750 1.0172 0.08337 0.07589 0.0004 0.1004 1.0000
16.000 1.0220 0.08615 0.07876 -0.0004 0.0950 1.0000
16.250 1.0251 0.08913 0.08171 -0.0013 0.0907 1.0000
16.500 1.0302 0.09188 0.08451 -0.0022 0.0865 1.0000
16.750 1.0345 0.09476 0.08742 -0.0032 0.0827 1.0000
17.000 1.0396 0.09747 0.09009 -0.0041 0.0797 1.0000
17.250 1.0448 0.10032 0.09306 -0.0051 0.0764 1.0000
17.500 1.0501 0.10310 0.09587 -0.0062 0.0736 1.0000
17.750 1.0575 0.10546 0.09818 -0.0070 0.0714 1.0000
18.000 1.0614 0.10859 0.10146 -0.0082 0.0689 1.0000
18.250 1.0657 0.11161 0.10455 -0.0095 0.0666 1.0000
18.500 1.0721 0.11421 0.10715 -0.0107 0.0647 1.0000
18.750 1.0775 0.11702 0.11002 -0.0119 0.0629 1.0000
19.000 1.0783 0.12074 0.11389 -0.0137 0.0611 1.0000
19.250 1.0805 0.12419 0.11744 -0.0154 0.0593 1.0000
|
Polar data table (+)
Polar graphs
<< Back to NACA 63(4)-221 (naca634221-il)