NACA 16-012 (naca16012-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 16-012 (naca16012-il) Reynolds number: 500,000 Max Cl/Cd: 44.51 at α=8° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca16012-il-500000-n5.txt Download as CSV file: xf-naca16012-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 16-012
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.750 -0.9003 0.06613 0.06331 -0.0621 1.0000 0.0047
-14.500 -0.9255 0.05930 0.05630 -0.0649 1.0000 0.0047
-14.250 -0.9497 0.05397 0.05079 -0.0652 1.0000 0.0047
-14.000 -0.9711 0.04980 0.04643 -0.0639 1.0000 0.0047
-13.750 -0.9924 0.04621 0.04265 -0.0613 1.0000 0.0047
-13.500 -1.0114 0.04324 0.03949 -0.0578 1.0000 0.0048
-13.250 -1.0281 0.04075 0.03683 -0.0536 1.0000 0.0048
-13.000 -1.0423 0.03868 0.03459 -0.0490 1.0000 0.0049
-12.750 -1.0542 0.03694 0.03270 -0.0441 1.0000 0.0049
-12.500 -1.0644 0.03543 0.03102 -0.0391 1.0000 0.0050
-12.250 -1.0660 0.03393 0.02937 -0.0356 0.9994 0.0051
-12.000 -1.0568 0.03231 0.02757 -0.0341 0.9980 0.0052
-11.750 -1.0459 0.03085 0.02594 -0.0326 0.9965 0.0053
-11.500 -1.0328 0.02947 0.02437 -0.0314 0.9952 0.0055
-11.250 -1.0190 0.02814 0.02287 -0.0300 0.9937 0.0057
-11.000 -1.0047 0.02688 0.02142 -0.0286 0.9916 0.0059
-10.750 -0.9882 0.02571 0.02008 -0.0275 0.9899 0.0061
-10.500 -0.9693 0.02465 0.01885 -0.0267 0.9884 0.0064
-10.250 -0.9479 0.02369 0.01772 -0.0263 0.9872 0.0067
-10.000 -0.9265 0.02253 0.01637 -0.0260 0.9862 0.0070
-9.750 -0.9091 0.02153 0.01526 -0.0247 0.9840 0.0075
-9.500 -0.8900 0.02081 0.01445 -0.0237 0.9817 0.0079
-9.250 -0.8680 0.02010 0.01365 -0.0232 0.9800 0.0083
-9.000 -0.8440 0.01939 0.01284 -0.0231 0.9787 0.0088
-8.750 -0.8188 0.01868 0.01203 -0.0232 0.9776 0.0094
-8.500 -0.7926 0.01804 0.01127 -0.0235 0.9767 0.0099
-8.250 -0.7672 0.01726 0.01044 -0.0237 0.9759 0.0112
-8.000 -0.7513 0.01689 0.01002 -0.0216 0.9720 0.0123
-7.750 -0.7274 0.01645 0.00954 -0.0212 0.9699 0.0135
-7.500 -0.7015 0.01598 0.00900 -0.0213 0.9684 0.0148
-7.250 -0.6755 0.01545 0.00846 -0.0215 0.9672 0.0173
-7.000 -0.6470 0.01512 0.00812 -0.0222 0.9663 0.0203
-6.750 -0.6176 0.01484 0.00778 -0.0230 0.9655 0.0225
-6.500 -0.5899 0.01436 0.00725 -0.0235 0.9646 0.0253
-6.250 -0.5740 0.01414 0.00702 -0.0212 0.9603 0.0277
-6.000 -0.5502 0.01388 0.00673 -0.0207 0.9579 0.0301
-5.750 -0.5237 0.01361 0.00641 -0.0208 0.9561 0.0318
-5.500 -0.4970 0.01327 0.00602 -0.0209 0.9546 0.0340
-5.250 -0.4702 0.01290 0.00564 -0.0211 0.9534 0.0375
-5.000 -0.4423 0.01260 0.00532 -0.0215 0.9523 0.0410
-4.750 -0.4155 0.01233 0.00503 -0.0216 0.9508 0.0447
-4.500 -0.4008 0.01215 0.00486 -0.0189 0.9458 0.0504
-4.250 -0.3769 0.01187 0.00462 -0.0184 0.9433 0.0622
-4.000 -0.3519 0.01153 0.00437 -0.0182 0.9414 0.0865
-3.750 -0.3267 0.01114 0.00411 -0.0180 0.9397 0.1232
-3.500 -0.3016 0.01069 0.00386 -0.0178 0.9383 0.1738
-3.250 -0.2848 0.01028 0.00368 -0.0158 0.9347 0.2367
-3.000 -0.2706 0.00981 0.00350 -0.0132 0.9302 0.3134
-2.750 -0.2560 0.00911 0.00324 -0.0108 0.9270 0.4246
-2.500 -0.2474 0.00817 0.00289 -0.0070 0.9241 0.5730
-2.250 -0.2466 0.00757 0.00279 -0.0010 0.9184 0.6908
-2.000 -0.2296 0.00729 0.00281 0.0015 0.9148 0.7635
-1.750 -0.2026 0.00719 0.00286 0.0018 0.9129 0.8100
-1.500 -0.1721 0.00730 0.00311 0.0015 0.9115 0.8558
-1.250 -0.1412 0.00746 0.00331 0.0011 0.9101 0.8765
-1.000 -0.1102 0.00748 0.00330 0.0003 0.9087 0.8826
-0.750 -0.0843 0.00757 0.00340 0.0006 0.9051 0.8869
-0.500 -0.0609 0.00758 0.00339 0.0015 0.9014 0.8917
-0.250 -0.0334 0.00754 0.00334 0.0014 0.8987 0.8952
0.000 0.0000 0.00755 0.00334 0.0000 0.8969 0.8969
0.250 0.0334 0.00754 0.00334 -0.0014 0.8952 0.8987
0.500 0.0609 0.00758 0.00339 -0.0015 0.8918 0.9014
0.750 0.0843 0.00757 0.00340 -0.0006 0.8869 0.9051
1.000 0.1102 0.00748 0.00330 -0.0003 0.8826 0.9087
1.250 0.1412 0.00746 0.00331 -0.0011 0.8765 0.9101
1.500 0.1720 0.00730 0.00311 -0.0015 0.8560 0.9115
1.750 0.2026 0.00719 0.00286 -0.0017 0.8098 0.9129
2.000 0.2296 0.00728 0.00281 -0.0015 0.7640 0.9148
2.250 0.2463 0.00757 0.00279 0.0011 0.6892 0.9185
2.500 0.2472 0.00818 0.00289 0.0071 0.5713 0.9241
2.750 0.2560 0.00911 0.00324 0.0108 0.4246 0.9270
3.000 0.2707 0.00981 0.00350 0.0132 0.3136 0.9302
3.250 0.2848 0.01028 0.00368 0.0158 0.2363 0.9347
3.500 0.3017 0.01069 0.00385 0.0178 0.1742 0.9383
3.750 0.3267 0.01114 0.00411 0.0180 0.1229 0.9397
4.000 0.3519 0.01153 0.00436 0.0182 0.0866 0.9414
4.250 0.3769 0.01187 0.00461 0.0184 0.0620 0.9433
4.500 0.4009 0.01215 0.00486 0.0189 0.0504 0.9458
4.750 0.4159 0.01233 0.00503 0.0215 0.0447 0.9508
5.000 0.4423 0.01259 0.00532 0.0215 0.0410 0.9523
5.250 0.4702 0.01290 0.00564 0.0211 0.0376 0.9534
5.500 0.4971 0.01327 0.00602 0.0209 0.0340 0.9546
5.750 0.5238 0.01361 0.00641 0.0208 0.0318 0.9561
6.000 0.5503 0.01388 0.00672 0.0207 0.0301 0.9579
6.250 0.5740 0.01414 0.00702 0.0212 0.0277 0.9604
6.500 0.5900 0.01436 0.00725 0.0234 0.0252 0.9646
6.750 0.6177 0.01484 0.00778 0.0230 0.0226 0.9655
7.000 0.6470 0.01512 0.00812 0.0222 0.0203 0.9663
7.250 0.6756 0.01545 0.00845 0.0215 0.0172 0.9673
7.500 0.7016 0.01598 0.00900 0.0213 0.0148 0.9685
7.750 0.7275 0.01644 0.00953 0.0212 0.0136 0.9700
8.000 0.7514 0.01688 0.01002 0.0215 0.0123 0.9721
8.250 0.7675 0.01726 0.01044 0.0236 0.0112 0.9759
8.500 0.7929 0.01804 0.01128 0.0234 0.0099 0.9767
8.750 0.8191 0.01868 0.01203 0.0231 0.0094 0.9776
9.000 0.8443 0.01938 0.01283 0.0230 0.0088 0.9787
9.250 0.8683 0.02010 0.01365 0.0231 0.0083 0.9801
9.500 0.8904 0.02081 0.01445 0.0236 0.0079 0.9818
9.750 0.9095 0.02154 0.01526 0.0246 0.0075 0.9841
10.000 0.9270 0.02252 0.01636 0.0259 0.0071 0.9862
10.250 0.9484 0.02369 0.01772 0.0262 0.0067 0.9872
10.500 0.9699 0.02465 0.01885 0.0266 0.0064 0.9884
10.750 0.9890 0.02568 0.02005 0.0273 0.0061 0.9899
11.000 1.0054 0.02690 0.02144 0.0284 0.0059 0.9917
11.250 1.0199 0.02814 0.02287 0.0299 0.0056 0.9938
11.500 1.0338 0.02946 0.02437 0.0312 0.0055 0.9953
11.750 1.0468 0.03085 0.02594 0.0324 0.0053 0.9966
12.000 1.0576 0.03232 0.02759 0.0339 0.0052 0.9980
12.250 1.0666 0.03396 0.02940 0.0354 0.0051 0.9995
12.500 1.0641 0.03546 0.03106 0.0392 0.0050 1.0000
12.750 1.0544 0.03693 0.03269 0.0441 0.0049 1.0000
13.000 1.0424 0.03868 0.03459 0.0490 0.0049 1.0000
13.250 1.0284 0.04073 0.03681 0.0536 0.0048 1.0000
13.500 1.0116 0.04323 0.03949 0.0578 0.0048 1.0000
13.750 0.9928 0.04620 0.04264 0.0613 0.0047 1.0000
14.000 0.9720 0.04976 0.04639 0.0639 0.0047 1.0000
14.250 0.9500 0.05401 0.05083 0.0651 0.0047 1.0000
14.500 0.9263 0.05930 0.05630 0.0647 0.0047 1.0000
14.750 0.9010 0.06619 0.06338 0.0619 0.0047 1.0000
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