NACA 0018 (naca0018-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 0018 (naca0018-il) Reynolds number: 50,000 Max Cl/Cd: 22.07 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca0018-il-50000.txt Download as CSV file: xf-naca0018-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 0018
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 -0.4876 0.10841 0.09936 -0.0104 1.0000 0.3138
-10.250 -0.5001 0.10247 0.09342 -0.0123 1.0000 0.3114
-10.000 -0.5715 0.08947 0.08050 -0.0181 1.0000 0.3040
-9.750 -0.7409 0.06466 0.05579 -0.0264 1.0000 0.2983
-9.500 -0.8387 0.05594 0.04699 -0.0198 1.0000 0.2967
-9.250 -0.8938 0.05095 0.04176 -0.0127 1.0000 0.2995
-9.000 -0.8627 0.05074 0.04168 -0.0120 1.0000 0.3110
-8.750 -0.8928 0.04743 0.03815 -0.0060 1.0000 0.3176
-8.500 -0.8721 0.04673 0.03754 -0.0044 1.0000 0.3286
-8.250 -0.8918 0.04411 0.03467 0.0010 1.0000 0.3375
-8.000 -0.8647 0.04386 0.03459 0.0022 1.0000 0.3500
-7.750 -0.8747 0.04172 0.03228 0.0068 1.0000 0.3604
-7.500 -0.8589 0.04109 0.03170 0.0091 1.0000 0.3734
-7.250 -0.8422 0.04046 0.03115 0.0113 1.0000 0.3863
-7.000 -0.8427 0.03895 0.02952 0.0151 1.0000 0.3991
-6.750 -0.8313 0.03820 0.02878 0.0178 1.0000 0.4133
-6.500 -0.8113 0.03791 0.02861 0.0198 1.0000 0.4275
-6.250 -0.8007 0.03710 0.02781 0.0226 1.0000 0.4419
-6.000 -0.7947 0.03608 0.02672 0.0257 1.0000 0.4573
-5.750 -0.7827 0.03548 0.02612 0.0283 1.0000 0.4731
-5.500 -0.7627 0.03537 0.02614 0.0303 1.0000 0.4885
-5.250 -0.7478 0.03498 0.02579 0.0327 1.0000 0.5042
-5.000 -0.7354 0.03446 0.02529 0.0352 1.0000 0.5207
-4.750 -0.7240 0.03389 0.02472 0.0378 1.0000 0.5378
-4.500 -0.7125 0.03338 0.02420 0.0402 1.0000 0.5555
-4.250 -0.6963 0.03323 0.02409 0.0424 1.0000 0.5727
-4.000 -0.6783 0.03326 0.02421 0.0445 1.0000 0.5894
-3.750 -0.6624 0.03317 0.02418 0.0467 1.0000 0.6066
-3.500 -0.6476 0.03305 0.02409 0.0488 1.0000 0.6244
-3.250 -0.6335 0.03293 0.02400 0.0510 1.0000 0.6426
-3.000 -0.6196 0.03285 0.02395 0.0532 1.0000 0.6612
-2.750 -0.6058 0.03281 0.02394 0.0553 1.0000 0.6802
-2.500 -0.5919 0.03285 0.02401 0.0574 1.0000 0.6995
-2.250 -0.5780 0.03294 0.02414 0.0595 1.0000 0.7191
-2.000 -0.5636 0.03313 0.02436 0.0615 1.0000 0.7390
-1.750 -0.5487 0.03340 0.02466 0.0634 1.0000 0.7591
-1.500 -0.5311 0.03382 0.02511 0.0649 0.9995 0.7797
-1.250 -0.4625 0.03554 0.02682 0.0580 0.9838 0.8026
-1.000 -0.3872 0.03723 0.02847 0.0498 0.9678 0.8246
-0.750 -0.3016 0.03882 0.03002 0.0397 0.9515 0.8452
-0.500 -0.2062 0.04015 0.03130 0.0276 0.9348 0.8641
-0.250 -0.1005 0.04102 0.03213 0.0134 0.9175 0.8820
0.000 0.0000 0.04128 0.03238 0.0000 0.8999 0.8999
0.250 0.1005 0.04102 0.03213 -0.0134 0.8820 0.9175
0.500 0.2061 0.04015 0.03130 -0.0276 0.8641 0.9348
0.750 0.3016 0.03882 0.03001 -0.0397 0.8452 0.9515
1.000 0.3873 0.03722 0.02847 -0.0498 0.8247 0.9678
1.250 0.4625 0.03553 0.02681 -0.0580 0.8026 0.9839
1.500 0.5311 0.03381 0.02511 -0.0649 0.7797 0.9996
1.750 0.5486 0.03339 0.02466 -0.0634 0.7592 1.0000
2.000 0.5635 0.03312 0.02436 -0.0615 0.7390 1.0000
2.250 0.5778 0.03294 0.02413 -0.0595 0.7191 1.0000
2.500 0.5918 0.03284 0.02400 -0.0574 0.6996 1.0000
2.750 0.6056 0.03281 0.02394 -0.0553 0.6802 1.0000
3.000 0.6194 0.03285 0.02395 -0.0532 0.6613 1.0000
3.250 0.6333 0.03293 0.02400 -0.0510 0.6426 1.0000
3.500 0.6475 0.03305 0.02409 -0.0488 0.6244 1.0000
3.750 0.6623 0.03316 0.02417 -0.0466 0.6066 1.0000
4.000 0.6782 0.03325 0.02420 -0.0445 0.5895 1.0000
4.250 0.6962 0.03322 0.02408 -0.0424 0.5728 1.0000
4.500 0.7123 0.03338 0.02419 -0.0402 0.5556 1.0000
4.750 0.7237 0.03389 0.02472 -0.0377 0.5378 1.0000
5.000 0.7352 0.03446 0.02529 -0.0352 0.5207 1.0000
5.250 0.7477 0.03498 0.02579 -0.0327 0.5043 1.0000
5.500 0.7626 0.03537 0.02613 -0.0303 0.4885 1.0000
5.750 0.7827 0.03547 0.02610 -0.0283 0.4732 1.0000
6.000 0.7944 0.03608 0.02672 -0.0257 0.4573 1.0000
6.250 0.8005 0.03710 0.02780 -0.0225 0.4420 1.0000
6.500 0.8111 0.03790 0.02860 -0.0198 0.4276 1.0000
6.750 0.8312 0.03819 0.02876 -0.0178 0.4134 1.0000
7.000 0.8424 0.03895 0.02952 -0.0151 0.3992 1.0000
7.250 0.8421 0.04045 0.03114 -0.0113 0.3863 1.0000
7.500 0.8589 0.04107 0.03169 -0.0091 0.3735 1.0000
7.750 0.8745 0.04172 0.03228 -0.0068 0.3604 1.0000
8.000 0.8647 0.04385 0.03458 -0.0021 0.3500 1.0000
8.250 0.8918 0.04410 0.03466 -0.0010 0.3375 1.0000
8.500 0.8722 0.04671 0.03752 0.0044 0.3286 1.0000
8.750 0.8928 0.04742 0.03814 0.0060 0.3176 1.0000
9.000 0.8629 0.05073 0.04166 0.0120 0.3110 1.0000
9.250 0.8938 0.05095 0.04175 0.0127 0.2995 1.0000
9.500 0.8388 0.05594 0.04699 0.0197 0.2966 1.0000
9.750 0.7409 0.06471 0.05583 0.0264 0.2983 1.0000
10.000 0.5703 0.08974 0.08077 0.0178 0.3041 1.0000
10.250 0.5015 0.10242 0.09337 0.0122 0.3111 1.0000
10.500 0.4886 0.10841 0.09937 0.0102 0.3137 1.0000
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Polar data table (+)
Polar graphs
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