NACA 0021 (naca0021-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 0021 (naca0021-il) Reynolds number: 50,000 Max Cl/Cd: 19.14 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca0021-il-50000.txt Download as CSV file: xf-naca0021-il-50000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.3112 0.12560 0.11631 -0.0086 1.0000 0.4567
-10.250 -0.2843 0.12215 0.11285 -0.0091 1.0000 0.4677
-10.000 -0.3247 0.12282 0.11357 -0.0069 1.0000 0.4753
-9.750 -0.2690 0.11676 0.10748 -0.0091 1.0000 0.4852
-9.500 -0.2967 0.11674 0.10749 -0.0069 1.0000 0.4959
-9.250 -0.2590 0.11173 0.10247 -0.0085 1.0000 0.5031
-9.000 -0.2672 0.11069 0.10145 -0.0071 1.0000 0.5161
-8.750 -0.3659 0.09402 0.08467 -0.0151 1.0000 0.4012
-8.500 -0.3767 0.09022 0.08089 -0.0147 1.0000 0.4051
-8.250 -0.4033 0.08534 0.07605 -0.0140 1.0000 0.4082
-8.000 -0.4715 0.07745 0.06824 -0.0124 1.0000 0.4117
-7.750 -0.4041 0.08041 0.07119 -0.0111 1.0000 0.4230
-7.500 -0.4468 0.07517 0.06603 -0.0087 1.0000 0.4287
-7.250 -0.6906 0.05799 0.04907 0.0058 1.0000 0.4299
-7.000 -0.8363 0.04920 0.04010 0.0218 1.0000 0.4330
-6.750 -0.7209 0.05447 0.04562 0.0155 1.0000 0.4459
-6.500 -0.8240 0.04776 0.03872 0.0279 1.0000 0.4524
-6.250 -0.7822 0.04914 0.04024 0.0279 1.0000 0.4625
-6.000 -0.8189 0.04596 0.03692 0.0346 1.0000 0.4728
-5.750 -0.7958 0.04632 0.03739 0.0361 1.0000 0.4828
-5.500 -0.8154 0.04402 0.03493 0.0410 1.0000 0.4947
-5.250 -0.7909 0.04456 0.03561 0.0424 1.0000 0.5048
-5.000 -0.8085 0.04222 0.03308 0.0468 1.0000 0.5182
-4.750 -0.7788 0.04326 0.03431 0.0478 1.0000 0.5282
-4.500 -0.7837 0.04171 0.03266 0.0511 1.0000 0.5417
-4.250 -0.7645 0.04213 0.03318 0.0527 1.0000 0.5532
-4.000 -0.7592 0.04136 0.03238 0.0552 1.0000 0.5662
-3.750 -0.7521 0.04079 0.03179 0.0574 1.0000 0.5804
-3.500 -0.7355 0.04107 0.03215 0.0591 1.0000 0.5920
-3.250 -0.7304 0.04029 0.03132 0.0612 1.0000 0.6071
-3.000 -0.6987 0.04088 0.03197 0.0601 0.9946 0.6226
-2.750 -0.6416 0.04215 0.03328 0.0550 0.9804 0.6399
-2.500 -0.5915 0.04298 0.03411 0.0507 0.9657 0.6576
-2.250 -0.5503 0.04341 0.03453 0.0478 0.9511 0.6755
-2.000 -0.5136 0.04365 0.03474 0.0454 0.9362 0.6940
-1.750 -0.4532 0.04526 0.03640 0.0410 0.9214 0.7085
-1.500 -0.3880 0.04646 0.03760 0.0352 0.9073 0.7247
-1.250 -0.3540 0.04667 0.03780 0.0338 0.8918 0.7416
-1.000 -0.3318 0.04665 0.03775 0.0340 0.8768 0.7596
-0.750 -0.2325 0.04876 0.03989 0.0239 0.8613 0.7709
-0.500 -0.1461 0.04940 0.04050 0.0147 0.8477 0.7869
-0.250 -0.1393 0.04928 0.04038 0.0172 0.8314 0.8043
0.000 0.0000 0.05040 0.04152 0.0000 0.8152 0.8152
0.250 0.1392 0.04928 0.04038 -0.0172 0.8043 0.8314
0.500 0.1463 0.04939 0.04050 -0.0147 0.7869 0.8477
0.750 0.2325 0.04876 0.03988 -0.0238 0.7709 0.8613
1.000 0.3317 0.04665 0.03775 -0.0339 0.7596 0.8768
1.250 0.3539 0.04667 0.03779 -0.0338 0.7416 0.8918
1.500 0.3878 0.04646 0.03760 -0.0352 0.7247 0.9073
1.750 0.4531 0.04526 0.03639 -0.0410 0.7085 0.9215
2.000 0.5135 0.04365 0.03474 -0.0454 0.6941 0.9363
2.250 0.5504 0.04340 0.03452 -0.0478 0.6755 0.9512
2.500 0.5915 0.04297 0.03410 -0.0507 0.6576 0.9657
2.750 0.6416 0.04214 0.03327 -0.0550 0.6399 0.9805
3.000 0.6987 0.04087 0.03195 -0.0601 0.6226 0.9947
3.250 0.7301 0.04029 0.03132 -0.0612 0.6072 1.0000
3.500 0.7353 0.04106 0.03215 -0.0591 0.5920 1.0000
3.750 0.7520 0.04077 0.03176 -0.0574 0.5804 1.0000
4.000 0.7589 0.04135 0.03237 -0.0551 0.5662 1.0000
4.250 0.7643 0.04211 0.03316 -0.0527 0.5532 1.0000
4.500 0.7834 0.04171 0.03265 -0.0511 0.5418 1.0000
4.750 0.7786 0.04325 0.03430 -0.0478 0.5283 1.0000
5.000 0.8081 0.04222 0.03308 -0.0468 0.5183 1.0000
5.250 0.7906 0.04455 0.03560 -0.0423 0.5049 1.0000
5.500 0.8155 0.04398 0.03490 -0.0410 0.4947 1.0000
5.750 0.7955 0.04631 0.03737 -0.0360 0.4828 1.0000
6.000 0.8190 0.04593 0.03689 -0.0346 0.4728 1.0000
6.250 0.7819 0.04913 0.04023 -0.0279 0.4626 1.0000
6.500 0.8243 0.04773 0.03868 -0.0279 0.4524 1.0000
6.750 0.7216 0.05441 0.04555 -0.0156 0.4459 1.0000
7.000 0.6677 0.05811 0.04924 -0.0076 0.4388 1.0000
7.250 0.6916 0.05791 0.04899 -0.0058 0.4299 1.0000
7.500 0.4474 0.07510 0.06595 0.0087 0.4287 1.0000
7.750 0.4049 0.08033 0.07110 0.0111 0.4229 1.0000
8.000 0.4721 0.07739 0.06817 0.0124 0.4117 1.0000
8.250 0.4039 0.08528 0.07599 0.0140 0.4082 1.0000
8.500 0.3775 0.09015 0.08082 0.0146 0.4050 1.0000
8.750 0.3673 0.09391 0.08456 0.0150 0.4010 1.0000
9.000 0.3997 0.09451 0.08514 0.0162 0.3902 1.0000
9.250 0.3819 0.09944 0.09006 0.0159 0.3896 1.0000
9.500 0.3752 0.10386 0.09448 0.0154 0.3901 1.0000
9.750 0.3820 0.10800 0.09863 0.0147 0.3916 1.0000
10.250 0.2855 0.12214 0.11284 0.0090 0.4676 1.0000
10.500 0.3127 0.12563 0.11634 0.0084 0.4566 1.0000
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Polar data table (+)
Polar graphs
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