NACA 16-021 (naca16021-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: NACA 16-021 (naca16021-il) Reynolds number: 500,000 Max Cl/Cd: 39.54 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca16021-il-500000.txt Download as CSV file: xf-naca16021-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 16-021
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-19.750 -1.0989 0.08207 0.07706 -0.0873 0.9955 0.0261
-19.500 -1.0998 0.07890 0.07381 -0.0879 0.9950 0.0266
-19.250 -1.0958 0.07620 0.07106 -0.0889 0.9945 0.0270
-19.000 -1.0913 0.07354 0.06835 -0.0900 0.9940 0.0275
-18.750 -1.0868 0.07089 0.06563 -0.0910 0.9935 0.0279
-18.500 -1.0859 0.06835 0.06299 -0.0908 0.9922 0.0283
-18.250 -1.0841 0.06588 0.06042 -0.0907 0.9909 0.0287
-18.000 -1.0811 0.06352 0.05795 -0.0906 0.9897 0.0292
-17.750 -1.0763 0.06131 0.05562 -0.0907 0.9885 0.0297
-17.500 -1.0702 0.05914 0.05331 -0.0908 0.9874 0.0301
-17.250 -1.0631 0.05703 0.05104 -0.0911 0.9864 0.0305
-17.000 -1.0531 0.05527 0.04925 -0.0910 0.9858 0.0313
-16.750 -1.0420 0.05361 0.04757 -0.0912 0.9851 0.0319
-16.500 -1.0304 0.05203 0.04594 -0.0915 0.9844 0.0325
-16.250 -1.0180 0.05052 0.04436 -0.0918 0.9839 0.0331
-16.000 -1.0047 0.04906 0.04282 -0.0921 0.9834 0.0338
-15.750 -0.9903 0.04770 0.04136 -0.0924 0.9829 0.0345
-15.500 -0.9870 0.04654 0.04011 -0.0900 0.9800 0.0350
-15.250 -0.9771 0.04537 0.03884 -0.0889 0.9777 0.0355
-15.000 -0.9661 0.04395 0.03742 -0.0882 0.9765 0.0364
-14.750 -0.9528 0.04273 0.03618 -0.0879 0.9753 0.0372
-14.500 -0.9377 0.04162 0.03503 -0.0877 0.9743 0.0381
-14.250 -0.9215 0.04055 0.03390 -0.0878 0.9735 0.0389
-14.000 -0.9044 0.03951 0.03279 -0.0879 0.9728 0.0398
-13.750 -0.8854 0.03858 0.03178 -0.0882 0.9722 0.0406
-13.500 -0.8688 0.03748 0.03061 -0.0882 0.9716 0.0416
-13.250 -0.8533 0.03628 0.02942 -0.0881 0.9711 0.0428
-13.000 -0.8527 0.03558 0.02869 -0.0842 0.9666 0.0435
-12.750 -0.8408 0.03477 0.02785 -0.0827 0.9642 0.0445
-12.500 -0.8248 0.03396 0.02699 -0.0821 0.9627 0.0457
-12.250 -0.8058 0.03322 0.02618 -0.0819 0.9616 0.0469
-12.000 -0.7899 0.03221 0.02514 -0.0815 0.9607 0.0484
-11.750 -0.7722 0.03127 0.02419 -0.0813 0.9599 0.0501
-11.500 -0.7507 0.03048 0.02337 -0.0817 0.9592 0.0520
-11.250 -0.7274 0.02978 0.02263 -0.0823 0.9586 0.0540
-11.000 -0.7073 0.02886 0.02171 -0.0825 0.9580 0.0568
-10.750 -0.7192 0.02863 0.02147 -0.0752 0.9511 0.0582
-10.500 -0.7018 0.02805 0.02086 -0.0743 0.9493 0.0613
-10.250 -0.6836 0.02731 0.02013 -0.0738 0.9480 0.0655
-10.000 -0.6616 0.02666 0.01947 -0.0739 0.9471 0.0712
-9.750 -0.6404 0.02588 0.01875 -0.0740 0.9462 0.0798
-9.500 -0.6181 0.02517 0.01809 -0.0742 0.9455 0.0910
-9.250 -0.5951 0.02450 0.01748 -0.0745 0.9448 0.1047
-9.000 -0.6014 0.02436 0.01737 -0.0682 0.9392 0.1130
-8.750 -0.5930 0.02391 0.01698 -0.0652 0.9357 0.1265
-8.500 -0.5739 0.02328 0.01643 -0.0646 0.9341 0.1460
-8.250 -0.5534 0.02260 0.01587 -0.0643 0.9330 0.1703
-8.000 -0.5343 0.02185 0.01528 -0.0637 0.9320 0.2023
-7.750 -0.5174 0.02099 0.01463 -0.0628 0.9311 0.2446
-7.500 -0.5018 0.02005 0.01394 -0.0617 0.9303 0.2972
-7.250 -0.5289 0.02012 0.01408 -0.0505 0.9210 0.3150
-7.000 -0.5240 0.01914 0.01336 -0.0469 0.9187 0.3727
-6.750 -0.5219 0.01801 0.01254 -0.0427 0.9170 0.4371
-6.500 -0.5224 0.01682 0.01165 -0.0379 0.9155 0.5056
-6.250 -0.5605 0.01693 0.01185 -0.0240 0.9051 0.5252
-6.000 -0.5691 0.01595 0.01115 -0.0168 0.9024 0.5872
-5.750 -0.5687 0.01518 0.01065 -0.0113 0.9007 0.6466
-5.500 -0.6061 0.01541 0.01096 0.0027 0.8905 0.6671
-5.250 -0.5975 0.01512 0.01079 0.0068 0.8881 0.7041
-5.000 -0.5765 0.01497 0.01072 0.0081 0.8868 0.7305
-4.750 -0.5577 0.01481 0.01058 0.0100 0.8856 0.7511
-4.500 -0.5823 0.01518 0.01097 0.0213 0.8768 0.7624
-4.250 -0.5739 0.01521 0.01102 0.0255 0.8735 0.7779
-4.000 -0.5632 0.01511 0.01090 0.0293 0.8716 0.7911
-3.750 -0.5492 0.01500 0.01075 0.0324 0.8701 0.8012
-3.500 -0.5136 0.01506 0.01080 0.0306 0.8695 0.8080
-3.250 -0.5094 0.01528 0.01100 0.0357 0.8657 0.8154
-3.000 -0.4737 0.01500 0.01067 0.0340 0.8672 0.8221
-2.750 -0.4159 0.01559 0.01127 0.0269 0.8668 0.8259
-2.250 -0.2950 0.01711 0.01279 0.0129 0.8685 0.8380
-2.000 -0.2972 0.01843 0.01414 0.0191 0.8579 0.8401
-1.750 -0.2502 0.01872 0.01440 0.0145 0.8576 0.8404
-1.500 -0.2048 0.01897 0.01463 0.0103 0.8573 0.8407
-1.250 -0.1600 0.01918 0.01483 0.0063 0.8569 0.8410
-1.000 -0.1164 0.01935 0.01498 0.0025 0.8565 0.8413
-0.750 -0.0741 0.01945 0.01508 -0.0009 0.8560 0.8416
-0.500 -0.0335 0.01951 0.01513 -0.0041 0.8556 0.8422
-0.250 0.0071 0.01951 0.01513 -0.0072 0.8553 0.8429
0.000 0.0479 0.01946 0.01508 -0.0104 0.8550 0.8437
0.250 0.0871 0.01934 0.01495 -0.0133 0.8547 0.8448
0.500 0.0334 0.01951 0.01513 0.0041 0.8422 0.8556
0.750 0.0741 0.01945 0.01508 0.0009 0.8416 0.8561
1.000 0.1165 0.01934 0.01498 -0.0026 0.8413 0.8565
1.250 0.1601 0.01918 0.01483 -0.0063 0.8410 0.8569
1.500 0.2048 0.01896 0.01463 -0.0103 0.8407 0.8573
1.750 0.2503 0.01871 0.01440 -0.0145 0.8404 0.8576
2.000 0.2973 0.01842 0.01413 -0.0191 0.8401 0.8579
2.750 0.4160 0.01559 0.01127 -0.0270 0.8260 0.8667
3.000 0.4740 0.01498 0.01066 -0.0341 0.8220 0.8672
3.250 0.5097 0.01527 0.01100 -0.0357 0.8155 0.8657
3.500 0.5138 0.01506 0.01080 -0.0306 0.8080 0.8696
3.750 0.5501 0.01498 0.01074 -0.0326 0.8013 0.8701
4.000 0.5632 0.01511 0.01090 -0.0293 0.7911 0.8716
4.250 0.5740 0.01520 0.01101 -0.0255 0.7778 0.8735
4.500 0.5824 0.01517 0.01096 -0.0213 0.7626 0.8768
4.750 0.5581 0.01481 0.01057 -0.0101 0.7512 0.8856
5.000 0.5767 0.01496 0.01071 -0.0081 0.7305 0.8868
5.250 0.5975 0.01511 0.01079 -0.0068 0.7039 0.8881
5.500 0.6061 0.01540 0.01095 -0.0027 0.6671 0.8906
5.750 0.5689 0.01517 0.01064 0.0112 0.6467 0.9007
6.000 0.5693 0.01594 0.01114 0.0168 0.5872 0.9025
6.250 0.5602 0.01693 0.01184 0.0241 0.5247 0.9052
7.000 0.4796 0.01777 0.01226 0.0577 0.4274 0.9288
7.250 0.4891 0.01897 0.01314 0.0601 0.3580 0.9296
7.500 0.5022 0.02004 0.01392 0.0616 0.2968 0.9303
7.750 0.5179 0.02098 0.01461 0.0627 0.2442 0.9311
8.000 0.5347 0.02183 0.01526 0.0637 0.2020 0.9320
8.250 0.5538 0.02258 0.01585 0.0642 0.1700 0.9330
8.500 0.5743 0.02325 0.01641 0.0645 0.1458 0.9342
8.750 0.5933 0.02388 0.01695 0.0652 0.1264 0.9358
9.000 0.5724 0.02384 0.01688 0.0748 0.1204 0.9443
9.250 0.5960 0.02448 0.01746 0.0744 0.1045 0.9449
9.500 0.6189 0.02514 0.01806 0.0741 0.0907 0.9455
9.750 0.6412 0.02585 0.01872 0.0738 0.0796 0.9463
10.000 0.6626 0.02663 0.01944 0.0737 0.0712 0.9471
10.250 0.6845 0.02728 0.02009 0.0736 0.0655 0.9481
10.500 0.7026 0.02802 0.02082 0.0742 0.0613 0.9495
10.750 0.7196 0.02858 0.02142 0.0751 0.0582 0.9513
11.000 0.7086 0.02883 0.02167 0.0822 0.0568 0.9581
11.250 0.7289 0.02974 0.02259 0.0820 0.0539 0.9587
11.500 0.7522 0.03044 0.02334 0.0814 0.0519 0.9593
11.750 0.7737 0.03122 0.02415 0.0810 0.0501 0.9600
12.000 0.7914 0.03217 0.02509 0.0812 0.0484 0.9608
12.250 0.8072 0.03317 0.02613 0.0817 0.0469 0.9617
12.500 0.8262 0.03391 0.02693 0.0818 0.0457 0.9629
12.750 0.8420 0.03471 0.02779 0.0825 0.0445 0.9645
13.000 0.8524 0.03550 0.02861 0.0843 0.0435 0.9672
13.250 0.8554 0.03623 0.02936 0.0877 0.0428 0.9712
13.500 0.8711 0.03741 0.03055 0.0878 0.0416 0.9717
13.750 0.8875 0.03853 0.03173 0.0878 0.0406 0.9722
14.000 0.9067 0.03945 0.03273 0.0875 0.0398 0.9729
14.250 0.9239 0.04048 0.03383 0.0874 0.0389 0.9736
14.500 0.9400 0.04155 0.03495 0.0874 0.0380 0.9745
14.750 0.9551 0.04265 0.03609 0.0875 0.0372 0.9755
15.000 0.9682 0.04388 0.03734 0.0878 0.0364 0.9768
15.250 0.9791 0.04528 0.03875 0.0886 0.0354 0.9781
15.500 0.9870 0.04642 0.03998 0.0902 0.0350 0.9808
15.750 0.9935 0.04761 0.04126 0.0919 0.0345 0.9830
16.000 1.0079 0.04897 0.04273 0.0916 0.0338 0.9835
16.250 1.0213 0.05042 0.04426 0.0912 0.0331 0.9840
16.500 1.0338 0.05194 0.04584 0.0909 0.0325 0.9846
16.750 1.0454 0.05350 0.04745 0.0906 0.0318 0.9853
17.000 1.0564 0.05516 0.04913 0.0904 0.0312 0.9860
17.250 1.0665 0.05692 0.05094 0.0906 0.0305 0.9866
17.500 1.0735 0.05903 0.05320 0.0903 0.0301 0.9877
17.750 1.0797 0.06120 0.05550 0.0902 0.0296 0.9888
18.000 1.0843 0.06340 0.05783 0.0902 0.0292 0.9900
18.250 1.0872 0.06576 0.06030 0.0903 0.0287 0.9912
18.500 1.0889 0.06821 0.06285 0.0905 0.0283 0.9926
18.750 1.0912 0.07075 0.06548 0.0903 0.0278 0.9937
19.000 1.0958 0.07339 0.06819 0.0893 0.0274 0.9941
19.250 1.1002 0.07606 0.07092 0.0882 0.0270 0.9946
|
Polar data table (+)
Polar graphs
<< Back to NACA 16-021 (naca16021-il)