NACA 0021 (naca0021-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 0021 (naca0021-il) Reynolds number: 50,000 Max Cl/Cd: 25.19 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca0021-il-50000-n5.txt Download as CSV file: xf-naca0021-il-50000-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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.750 -0.6667 0.10156 0.09168 -0.0381 1.0000 0.1803
-13.500 -0.6363 0.10347 0.09361 -0.0363 1.0000 0.1821
-13.250 -0.7672 0.07934 0.06924 -0.0463 1.0000 0.1952
-13.000 -0.7088 0.08477 0.07480 -0.0430 1.0000 0.1972
-12.750 -0.6887 0.08472 0.07477 -0.0421 1.0000 0.2010
-12.500 -0.8465 0.06192 0.05146 -0.0489 1.0000 0.2110
-12.250 -0.8120 0.06309 0.05276 -0.0478 1.0000 0.2158
-12.000 -0.8439 0.05771 0.04721 -0.0474 1.0000 0.2214
-11.750 -0.8795 0.05278 0.04205 -0.0457 1.0000 0.2264
-11.500 -0.8530 0.05291 0.04233 -0.0449 1.0000 0.2319
-11.250 -0.8659 0.05025 0.03956 -0.0428 1.0000 0.2376
-11.000 -0.8862 0.04743 0.03658 -0.0397 1.0000 0.2430
-10.750 -0.8660 0.04715 0.03644 -0.0385 1.0000 0.2489
-10.500 -0.8759 0.04538 0.03457 -0.0352 1.0000 0.2549
-10.250 -0.8889 0.04369 0.03279 -0.0310 1.0000 0.2606
-10.000 -0.8754 0.04327 0.03249 -0.0290 1.0000 0.2667
-9.750 -0.8871 0.04205 0.03122 -0.0243 1.0000 0.2728
-9.500 -0.8994 0.04096 0.03008 -0.0190 1.0000 0.2785
-9.250 -0.8902 0.04057 0.02980 -0.0162 1.0000 0.2848
-9.000 -0.8984 0.03962 0.02878 -0.0113 1.0000 0.2915
-8.750 -0.8988 0.03888 0.02804 -0.0074 1.0000 0.2981
-8.500 -0.8933 0.03841 0.02764 -0.0041 1.0000 0.3051
-8.250 -0.9011 0.03748 0.02659 0.0008 1.0000 0.3127
-8.000 -0.8913 0.03714 0.02638 0.0036 1.0000 0.3197
-7.750 -0.8897 0.03656 0.02578 0.0074 1.0000 0.3277
-7.500 -0.8875 0.03595 0.02513 0.0110 1.0000 0.3357
-7.250 -0.8793 0.03562 0.02487 0.0139 1.0000 0.3437
-7.000 -0.8796 0.03492 0.02406 0.0178 1.0000 0.3529
-6.750 -0.8672 0.03474 0.02402 0.0201 1.0000 0.3609
-6.500 -0.8577 0.03413 0.02327 0.0222 0.9979 0.3719
-6.250 -0.8182 0.03399 0.02326 0.0195 0.9902 0.3836
-6.000 -0.7838 0.03358 0.02282 0.0175 0.9808 0.3967
-5.750 -0.7504 0.03321 0.02241 0.0157 0.9713 0.4101
-5.500 -0.7104 0.03305 0.02233 0.0130 0.9630 0.4227
-5.250 -0.6811 0.03263 0.02186 0.0121 0.9518 0.4360
-5.000 -0.6443 0.03243 0.02169 0.0101 0.9428 0.4495
-4.750 -0.6102 0.03222 0.02152 0.0087 0.9322 0.4620
-4.500 -0.5808 0.03185 0.02109 0.0079 0.9212 0.4764
-4.250 -0.5413 0.03174 0.02107 0.0058 0.9118 0.4893
-4.000 -0.5109 0.03152 0.02087 0.0052 0.9004 0.5024
-3.500 -0.4417 0.03115 0.02055 0.0028 0.8793 0.5296
-3.250 -0.4032 0.03085 0.02026 0.0009 0.8703 0.5440
-3.000 -0.3775 0.03068 0.02010 0.0014 0.8574 0.5575
-2.750 -0.3360 0.03051 0.01999 -0.0006 0.8487 0.5707
-2.500 -0.3145 0.03028 0.01974 0.0006 0.8350 0.5848
-2.250 -0.2724 0.03012 0.01963 -0.0013 0.8265 0.5981
-2.000 -0.2483 0.03004 0.01959 -0.0003 0.8124 0.6108
-1.750 -0.2131 0.02966 0.01916 -0.0012 0.8037 0.6265
-1.500 -0.1843 0.02980 0.01940 -0.0007 0.7892 0.6373
-1.250 -0.1500 0.02951 0.01909 -0.0013 0.7797 0.6519
-1.000 -0.1228 0.02956 0.01918 -0.0006 0.7656 0.6643
-0.750 -0.0907 0.02947 0.01910 -0.0007 0.7539 0.6772
-0.500 -0.0648 0.02929 0.01889 0.0001 0.7415 0.6921
-0.250 -0.0304 0.02945 0.01911 -0.0002 0.7284 0.7028
0.000 0.0000 0.02923 0.01884 0.0000 0.7173 0.7173
0.250 0.0304 0.02945 0.01911 0.0002 0.7028 0.7284
0.500 0.0649 0.02929 0.01889 -0.0001 0.6921 0.7415
0.750 0.0907 0.02947 0.01910 0.0007 0.6772 0.7539
1.000 0.1228 0.02956 0.01918 0.0006 0.6644 0.7656
1.250 0.1499 0.02951 0.01908 0.0013 0.6519 0.7797
1.500 0.1843 0.02980 0.01940 0.0007 0.6373 0.7893
1.750 0.2131 0.02966 0.01916 0.0012 0.6265 0.8037
2.000 0.2483 0.03004 0.01959 0.0003 0.6108 0.8124
2.250 0.2724 0.03012 0.01963 0.0013 0.5981 0.8265
2.500 0.3144 0.03028 0.01974 -0.0005 0.5848 0.8350
2.750 0.3359 0.03050 0.01998 0.0006 0.5707 0.8487
3.000 0.3774 0.03067 0.02009 -0.0013 0.5576 0.8574
3.250 0.4032 0.03085 0.02026 -0.0009 0.5440 0.8703
3.500 0.4417 0.03114 0.02055 -0.0027 0.5296 0.8794
3.750 0.4754 0.03114 0.02044 -0.0035 0.5179 0.8910
4.000 0.5108 0.03152 0.02086 -0.0052 0.5024 0.9004
4.250 0.5413 0.03174 0.02107 -0.0058 0.4894 0.9119
4.500 0.5807 0.03184 0.02109 -0.0079 0.4764 0.9213
4.750 0.6102 0.03221 0.02152 -0.0087 0.4621 0.9322
5.000 0.6442 0.03243 0.02168 -0.0101 0.4495 0.9429
5.250 0.6812 0.03263 0.02185 -0.0121 0.4360 0.9519
5.500 0.7106 0.03304 0.02232 -0.0131 0.4227 0.9631
5.750 0.7504 0.03320 0.02240 -0.0157 0.4101 0.9714
6.000 0.7840 0.03357 0.02281 -0.0175 0.3967 0.9809
6.250 0.8183 0.03398 0.02325 -0.0196 0.3836 0.9903
6.500 0.8579 0.03412 0.02326 -0.0222 0.3719 0.9980
6.750 0.8670 0.03473 0.02400 -0.0201 0.3609 1.0000
7.000 0.8794 0.03491 0.02405 -0.0177 0.3530 1.0000
7.250 0.8792 0.03561 0.02486 -0.0139 0.3438 1.0000
7.500 0.8874 0.03594 0.02512 -0.0110 0.3357 1.0000
7.750 0.8896 0.03655 0.02576 -0.0073 0.3277 1.0000
8.000 0.8912 0.03713 0.02636 -0.0036 0.3198 1.0000
8.250 0.9011 0.03746 0.02657 -0.0008 0.3127 1.0000
8.500 0.8933 0.03840 0.02763 0.0041 0.3051 1.0000
8.750 0.8989 0.03886 0.02803 0.0074 0.2981 1.0000
9.000 0.8985 0.03960 0.02876 0.0113 0.2915 1.0000
9.250 0.8904 0.04056 0.02978 0.0162 0.2848 1.0000
9.500 0.8998 0.04095 0.03006 0.0190 0.2784 1.0000
9.750 0.8874 0.04204 0.03120 0.0242 0.2727 1.0000
10.000 0.8759 0.04325 0.03247 0.0290 0.2667 1.0000
10.250 0.8896 0.04366 0.03276 0.0310 0.2605 1.0000
10.500 0.8764 0.04536 0.03455 0.0351 0.2549 1.0000
10.750 0.8669 0.04712 0.03640 0.0384 0.2489 1.0000
11.000 0.8875 0.04738 0.03652 0.0395 0.2430 1.0000
11.250 0.8667 0.05023 0.03954 0.0427 0.2375 1.0000
11.500 0.8545 0.05284 0.04226 0.0448 0.2318 1.0000
11.750 0.8816 0.05268 0.04194 0.0456 0.2263 1.0000
12.000 0.8451 0.05767 0.04717 0.0473 0.2213 1.0000
12.250 0.8147 0.06290 0.05257 0.0477 0.2157 1.0000
12.500 0.8500 0.06167 0.05120 0.0488 0.2109 1.0000
12.750 0.6927 0.08431 0.07435 0.0421 0.2011 1.0000
13.000 0.7124 0.08443 0.07445 0.0430 0.1973 1.0000
13.250 0.7718 0.07889 0.06878 0.0463 0.1952 1.0000
13.500 0.6389 0.10329 0.09343 0.0361 0.1821 1.0000
13.750 0.6696 0.10133 0.09145 0.0380 0.1803 1.0000
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Polar data table (+)
Polar graphs
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