NACA 0021 (naca0021-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: NACA 0021 (naca0021-il) Reynolds number: 1,000,000 Max Cl/Cd: 71.04 at α=9° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca0021-il-1000000-n5.txt Download as CSV file: xf-naca0021-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 0021
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
------ -------- --------- --------- -------- -------- --------
-19.750 -1.3373 0.07896 0.07414 -0.0364 1.0000 0.0448
-19.500 -1.3450 0.07492 0.07002 -0.0376 1.0000 0.0455
-19.250 -1.3515 0.07105 0.06608 -0.0387 1.0000 0.0462
-19.000 -1.3565 0.06740 0.06235 -0.0396 1.0000 0.0469
-18.750 -1.3589 0.06410 0.05898 -0.0404 1.0000 0.0475
-18.500 -1.3639 0.06056 0.05537 -0.0412 1.0000 0.0483
-18.250 -1.3679 0.05719 0.05194 -0.0419 1.0000 0.0491
-18.000 -1.3701 0.05404 0.04874 -0.0424 1.0000 0.0500
-17.750 -1.3705 0.05115 0.04578 -0.0429 1.0000 0.0509
-17.500 -1.3691 0.04849 0.04306 -0.0432 1.0000 0.0518
-17.250 -1.3657 0.04610 0.04062 -0.0434 1.0000 0.0526
-17.000 -1.3643 0.04355 0.03802 -0.0436 1.0000 0.0536
-16.750 -1.3616 0.04117 0.03560 -0.0436 1.0000 0.0547
-16.500 -1.3571 0.03902 0.03340 -0.0436 1.0000 0.0559
-16.250 -1.3511 0.03707 0.03140 -0.0434 1.0000 0.0571
-16.000 -1.3433 0.03532 0.02961 -0.0432 1.0000 0.0582
-15.750 -1.3375 0.03344 0.02770 -0.0428 1.0000 0.0596
-15.500 -1.3302 0.03176 0.02599 -0.0424 1.0000 0.0612
-15.250 -1.3212 0.03027 0.02447 -0.0419 1.0000 0.0627
-15.000 -1.3106 0.02895 0.02311 -0.0413 1.0000 0.0641
-14.750 -1.3016 0.02754 0.02168 -0.0406 1.0000 0.0657
-14.500 -1.2912 0.02629 0.02041 -0.0399 1.0000 0.0674
-14.250 -1.2794 0.02519 0.01928 -0.0390 1.0000 0.0690
-14.000 -1.2666 0.02421 0.01827 -0.0382 1.0000 0.0706
-13.750 -1.2553 0.02316 0.01721 -0.0371 1.0000 0.0724
-13.500 -1.2431 0.02223 0.01627 -0.0360 1.0000 0.0744
-13.250 -1.2294 0.02145 0.01547 -0.0349 1.0000 0.0762
-13.000 -1.2168 0.02067 0.01468 -0.0335 1.0000 0.0781
-12.750 -1.2058 0.01991 0.01392 -0.0318 1.0000 0.0804
-12.500 -1.1949 0.01928 0.01328 -0.0298 1.0000 0.0826
-12.000 -1.1649 0.01806 0.01206 -0.0272 0.9975 0.0874
-11.750 -1.1393 0.01745 0.01145 -0.0278 0.9946 0.0904
-11.500 -1.1125 0.01690 0.01090 -0.0286 0.9919 0.0932
-11.250 -1.0902 0.01633 0.01034 -0.0284 0.9863 0.0964
-11.000 -1.0650 0.01585 0.00986 -0.0287 0.9806 0.0999
-10.750 -1.0420 0.01534 0.00937 -0.0285 0.9739 0.1036
-10.500 -1.0202 0.01489 0.00892 -0.0279 0.9653 0.1075
-10.250 -0.9996 0.01449 0.00851 -0.0270 0.9558 0.1114
-10.000 -0.9807 0.01406 0.00809 -0.0257 0.9452 0.1162
-9.750 -0.9613 0.01372 0.00774 -0.0243 0.9335 0.1205
-9.500 -0.9428 0.01334 0.00737 -0.0228 0.9222 0.1257
-9.250 -0.9225 0.01306 0.00705 -0.0216 0.9097 0.1302
-9.000 -0.9029 0.01272 0.00672 -0.0202 0.8973 0.1357
-8.750 -0.8820 0.01246 0.00643 -0.0190 0.8846 0.1405
-8.500 -0.8616 0.01219 0.00614 -0.0177 0.8709 0.1458
-8.250 -0.8412 0.01196 0.00589 -0.0163 0.8575 0.1514
-8.000 -0.8209 0.01177 0.00566 -0.0149 0.8438 0.1563
-7.750 -0.7993 0.01155 0.00543 -0.0138 0.8293 0.1625
-7.500 -0.7758 0.01137 0.00522 -0.0130 0.8161 0.1679
-7.250 -0.7530 0.01117 0.00500 -0.0120 0.8018 0.1748
-7.000 -0.7287 0.01101 0.00482 -0.0114 0.7877 0.1808
-6.750 -0.7053 0.01081 0.00461 -0.0106 0.7742 0.1881
-6.250 -0.6564 0.01049 0.00426 -0.0092 0.7460 0.2022
-6.000 -0.6314 0.01037 0.00411 -0.0087 0.7322 0.2091
-5.750 -0.6069 0.01022 0.00395 -0.0080 0.7177 0.2171
-5.500 -0.5812 0.01010 0.00382 -0.0076 0.7044 0.2243
-5.250 -0.5564 0.00997 0.00367 -0.0070 0.6904 0.2326
-5.000 -0.5305 0.00986 0.00355 -0.0066 0.6764 0.2406
-4.750 -0.5051 0.00973 0.00342 -0.0061 0.6634 0.2492
-4.250 -0.4536 0.00953 0.00320 -0.0052 0.6364 0.2671
-4.000 -0.4274 0.00946 0.00311 -0.0048 0.6233 0.2760
-3.750 -0.4015 0.00935 0.00301 -0.0044 0.6102 0.2856
-3.500 -0.3749 0.00928 0.00293 -0.0041 0.5980 0.2946
-3.250 -0.3491 0.00920 0.00284 -0.0036 0.5846 0.3048
-2.750 -0.2962 0.00907 0.00270 -0.0029 0.5600 0.3245
-2.250 -0.2427 0.00896 0.00259 -0.0023 0.5363 0.3439
-1.750 -0.1890 0.00887 0.00250 -0.0018 0.5131 0.3634
-1.500 -0.1618 0.00887 0.00247 -0.0016 0.5007 0.3723
-1.250 -0.1351 0.00881 0.00243 -0.0013 0.4902 0.3832
-1.000 -0.1079 0.00882 0.00242 -0.0010 0.4779 0.3923
-0.750 -0.0811 0.00877 0.00239 -0.0008 0.4677 0.4035
-0.250 -0.0270 0.00875 0.00237 -0.0002 0.4462 0.4248
0.000 0.0000 0.00878 0.00237 0.0000 0.4345 0.4345
0.250 0.0270 0.00875 0.00237 0.0002 0.4248 0.4462
0.750 0.0811 0.00877 0.00239 0.0008 0.4034 0.4678
1.000 0.1079 0.00882 0.00242 0.0010 0.3924 0.4779
1.250 0.1351 0.00881 0.00243 0.0013 0.3832 0.4901
1.500 0.1618 0.00887 0.00247 0.0016 0.3723 0.5008
1.750 0.1890 0.00887 0.00250 0.0018 0.3634 0.5131
2.250 0.2427 0.00896 0.00259 0.0023 0.3439 0.5363
2.750 0.2962 0.00907 0.00270 0.0029 0.3245 0.5600
3.250 0.3491 0.00920 0.00284 0.0036 0.3048 0.5846
3.500 0.3750 0.00928 0.00293 0.0040 0.2946 0.5979
3.750 0.4016 0.00935 0.00301 0.0043 0.2857 0.6103
4.000 0.4275 0.00946 0.00311 0.0048 0.2760 0.6234
4.250 0.4537 0.00952 0.00320 0.0052 0.2672 0.6365
4.750 0.5053 0.00973 0.00342 0.0060 0.2491 0.6634
5.000 0.5307 0.00986 0.00355 0.0065 0.2405 0.6765
5.250 0.5565 0.00997 0.00367 0.0070 0.2325 0.6904
5.500 0.5814 0.01010 0.00381 0.0075 0.2243 0.7043
5.750 0.6071 0.01022 0.00395 0.0080 0.2171 0.7176
6.000 0.6316 0.01037 0.00411 0.0086 0.2091 0.7323
6.250 0.6567 0.01049 0.00426 0.0092 0.2022 0.7460
6.750 0.7055 0.01081 0.00461 0.0105 0.1881 0.7742
7.000 0.7290 0.01101 0.00482 0.0113 0.1807 0.7877
7.250 0.7534 0.01117 0.00500 0.0119 0.1748 0.8018
7.500 0.7761 0.01137 0.00522 0.0129 0.1679 0.8161
7.750 0.7997 0.01156 0.00543 0.0137 0.1623 0.8293
8.000 0.8214 0.01177 0.00566 0.0148 0.1562 0.8438
8.250 0.8418 0.01196 0.00589 0.0162 0.1512 0.8574
8.500 0.8622 0.01219 0.00614 0.0175 0.1457 0.8708
8.750 0.8826 0.01246 0.00643 0.0189 0.1405 0.8845
9.000 0.9036 0.01272 0.00672 0.0201 0.1356 0.8972
9.250 0.9232 0.01306 0.00705 0.0214 0.1302 0.9095
9.500 0.9436 0.01334 0.00736 0.0227 0.1258 0.9220
9.750 0.9621 0.01372 0.00774 0.0242 0.1205 0.9334
10.000 0.9816 0.01406 0.00809 0.0255 0.1161 0.9451
10.250 1.0006 0.01448 0.00851 0.0268 0.1114 0.9556
10.500 1.0210 0.01489 0.00892 0.0277 0.1076 0.9652
10.750 1.0429 0.01534 0.00936 0.0283 0.1035 0.9738
11.000 1.0658 0.01584 0.00985 0.0285 0.0998 0.9806
11.250 1.0911 0.01632 0.01033 0.0283 0.0964 0.9863
11.500 1.1135 0.01690 0.01089 0.0284 0.0931 0.9920
11.750 1.1404 0.01744 0.01143 0.0276 0.0903 0.9947
12.000 1.1660 0.01804 0.01204 0.0270 0.0874 0.9975
12.500 1.1956 0.01926 0.01326 0.0297 0.0826 1.0000
12.750 1.2068 0.01988 0.01389 0.0316 0.0803 1.0000
13.000 1.2180 0.02065 0.01466 0.0333 0.0780 1.0000
13.250 1.2308 0.02142 0.01544 0.0346 0.0762 1.0000
13.500 1.2446 0.02220 0.01624 0.0358 0.0743 1.0000
13.750 1.2570 0.02313 0.01718 0.0369 0.0724 1.0000
14.000 1.2683 0.02417 0.01824 0.0379 0.0705 1.0000
14.250 1.2814 0.02515 0.01924 0.0388 0.0690 1.0000
14.500 1.2933 0.02625 0.02037 0.0395 0.0673 1.0000
14.750 1.3038 0.02749 0.02163 0.0403 0.0656 1.0000
15.000 1.3129 0.02890 0.02305 0.0410 0.0640 1.0000
15.250 1.3236 0.03021 0.02441 0.0415 0.0626 1.0000
15.500 1.3327 0.03170 0.02593 0.0420 0.0611 1.0000
15.750 1.3401 0.03338 0.02764 0.0425 0.0595 1.0000
16.000 1.3460 0.03525 0.02954 0.0428 0.0581 1.0000
16.250 1.3541 0.03699 0.03132 0.0430 0.0570 1.0000
16.500 1.3602 0.03893 0.03331 0.0432 0.0558 1.0000
16.750 1.3647 0.04108 0.03550 0.0432 0.0547 1.0000
17.000 1.3675 0.04346 0.03792 0.0432 0.0535 1.0000
17.250 1.3693 0.04598 0.04049 0.0430 0.0525 1.0000
17.500 1.3728 0.04836 0.04293 0.0428 0.0517 1.0000
17.750 1.3741 0.05103 0.04566 0.0424 0.0508 1.0000
18.000 1.3739 0.05392 0.04861 0.0420 0.0499 1.0000
18.250 1.3718 0.05705 0.05180 0.0414 0.0490 1.0000
18.500 1.3679 0.06042 0.05523 0.0407 0.0482 1.0000
18.750 1.3634 0.06391 0.05878 0.0400 0.0475 1.0000
19.000 1.3608 0.06724 0.06218 0.0392 0.0469 1.0000
19.250 1.3559 0.07090 0.06592 0.0382 0.0462 1.0000
|
Polar data table (+)
Polar graphs
<< Back to NACA 0021 (naca0021-il)