NACA 16-018 (naca16018-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 16-018 (naca16018-il) Reynolds number: 200,000 Max Cl/Cd: 37.86 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca16018-il-200000.txt Download as CSV file: xf-naca16018-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 16-018
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.750 -0.7655 0.10989 0.10594 -0.0647 1.0000 0.0442
-15.500 -0.7910 0.10302 0.09901 -0.0663 1.0000 0.0438
-15.250 -0.8229 0.09621 0.09211 -0.0674 1.0000 0.0434
-15.000 -0.8558 0.09015 0.08592 -0.0673 1.0000 0.0429
-14.750 -0.8895 0.08472 0.08035 -0.0661 1.0000 0.0426
-14.500 -0.9237 0.07984 0.07530 -0.0637 1.0000 0.0423
-14.250 -0.9569 0.07548 0.07076 -0.0603 1.0000 0.0420
-14.000 -0.9882 0.07165 0.06672 -0.0561 1.0000 0.0419
-13.750 -1.0182 0.06816 0.06302 -0.0512 1.0000 0.0418
-13.500 -1.0457 0.06507 0.05972 -0.0458 1.0000 0.0418
-13.250 -1.0714 0.06228 0.05670 -0.0400 1.0000 0.0419
-13.000 -1.0951 0.05971 0.05390 -0.0339 1.0000 0.0420
-12.750 -1.1166 0.05736 0.05131 -0.0276 1.0000 0.0421
-12.500 -1.1357 0.05516 0.04886 -0.0213 1.0000 0.0423
-12.250 -1.1527 0.05309 0.04653 -0.0149 1.0000 0.0426
-12.000 -1.1668 0.05118 0.04436 -0.0086 1.0000 0.0429
-11.750 -1.1792 0.04948 0.04239 -0.0023 1.0000 0.0433
-11.500 -1.1921 0.04812 0.04075 0.0044 1.0000 0.0437
-11.250 -1.2068 0.04719 0.03957 0.0117 1.0000 0.0441
-11.000 -1.1859 0.04404 0.03622 0.0115 1.0000 0.0456
-10.750 -1.1756 0.04285 0.03499 0.0139 1.0000 0.0467
-10.500 -1.1660 0.04177 0.03382 0.0165 1.0000 0.0479
-10.250 -1.1535 0.04053 0.03243 0.0188 1.0000 0.0491
-10.000 -1.1398 0.03931 0.03101 0.0209 1.0000 0.0504
-9.750 -1.1315 0.03842 0.02990 0.0242 1.0000 0.0517
-9.500 -1.0896 0.03644 0.02779 0.0206 1.0000 0.0540
-9.250 -1.0638 0.03544 0.02680 0.0202 1.0000 0.0558
-9.000 -1.0454 0.03469 0.02598 0.0214 1.0000 0.0577
-8.750 -1.0283 0.03402 0.02522 0.0229 1.0000 0.0597
-8.500 -1.0129 0.03344 0.02451 0.0249 1.0000 0.0615
-8.250 -0.9774 0.03227 0.02336 0.0228 1.0000 0.0643
-8.000 -0.9620 0.03166 0.02277 0.0245 1.0000 0.0667
-7.750 -0.9484 0.03114 0.02222 0.0266 1.0000 0.0694
-7.500 -0.9351 0.03067 0.02167 0.0290 1.0000 0.0719
-7.250 -0.9209 0.02988 0.02089 0.0310 1.0000 0.0748
-7.000 -0.8667 0.02960 0.02063 0.0246 0.9928 0.0822
-6.750 -0.8453 0.02887 0.01992 0.0250 0.9886 0.0886
-6.500 -0.8263 0.02845 0.01949 0.0260 0.9861 0.0969
-6.250 -0.8069 0.02798 0.01908 0.0268 0.9837 0.1113
-6.000 -0.7998 0.02707 0.01835 0.0303 0.9791 0.1318
-5.750 -0.7911 0.02624 0.01778 0.0333 0.9754 0.1723
-5.500 -0.7858 0.02532 0.01735 0.0369 0.9723 0.2479
-5.250 -0.7979 0.02425 0.01672 0.0444 0.9676 0.3257
-5.000 -0.8172 0.02319 0.01613 0.0537 0.9628 0.4117
-4.750 -0.8338 0.02203 0.01576 0.0628 0.9590 0.5474
-4.500 -0.7502 0.02321 0.01808 0.0525 0.9589 0.7746
-4.250 -0.7150 0.02426 0.01908 0.0515 0.9557 0.8015
-4.000 -0.6935 0.02504 0.01979 0.0533 0.9520 0.8183
-3.750 -0.6346 0.02722 0.02186 0.0480 0.9501 0.8307
-3.500 -0.5790 0.02935 0.02388 0.0435 0.9482 0.8417
-3.250 -0.5091 0.03128 0.02568 0.0355 0.9474 0.8445
-3.000 -0.4770 0.03206 0.02636 0.0346 0.9453 0.8553
-2.750 -0.3697 0.03546 0.02966 0.0203 0.9463 0.8595
-2.500 -0.3285 0.03644 0.03058 0.0176 0.9449 0.8707
-2.250 -0.2772 0.03707 0.03114 0.0125 0.9429 0.8729
-2.000 -0.2491 0.03731 0.03134 0.0119 0.9381 0.8767
-1.750 -0.2361 0.03727 0.03126 0.0141 0.9343 0.8859
-1.500 -0.1886 0.03750 0.03144 0.0094 0.9325 0.8877
-1.250 -0.1421 0.03770 0.03160 0.0048 0.9310 0.8900
-1.000 -0.1472 0.03768 0.03157 0.0107 0.9242 0.9002
-0.750 -0.1051 0.03777 0.03164 0.0069 0.9212 0.9018
-0.500 -0.0621 0.03785 0.03171 0.0030 0.9189 0.9039
-0.250 -0.0197 0.03790 0.03175 -0.0008 0.9169 0.9066
0.000 0.0000 0.03794 0.03178 0.0000 0.9127 0.9127
0.250 0.0197 0.03790 0.03175 0.0008 0.9066 0.9169
0.500 0.0620 0.03785 0.03171 -0.0030 0.9039 0.9189
0.750 0.1051 0.03777 0.03164 -0.0069 0.9018 0.9212
1.000 0.1471 0.03768 0.03157 -0.0106 0.9002 0.9243
1.250 0.1422 0.03769 0.03160 -0.0048 0.8901 0.9310
1.500 0.1886 0.03749 0.03143 -0.0094 0.8877 0.9325
1.750 0.2361 0.03726 0.03125 -0.0141 0.8859 0.9343
2.000 0.2490 0.03730 0.03133 -0.0119 0.8767 0.9382
2.250 0.2710 0.03713 0.03119 -0.0112 0.8727 0.9441
2.500 0.3285 0.03643 0.03056 -0.0176 0.8708 0.9449
2.750 0.3698 0.03544 0.02965 -0.0203 0.8595 0.9463
3.000 0.4771 0.03204 0.02634 -0.0346 0.8553 0.9453
3.250 0.5091 0.03127 0.02567 -0.0355 0.8446 0.9474
3.500 0.5789 0.02935 0.02387 -0.0435 0.8417 0.9483
3.750 0.6350 0.02719 0.02183 -0.0481 0.8308 0.9501
4.000 0.6937 0.02502 0.01976 -0.0533 0.8182 0.9520
4.250 0.7151 0.02425 0.01906 -0.0515 0.8014 0.9557
4.500 0.7504 0.02319 0.01806 -0.0525 0.7745 0.9589
4.750 0.8337 0.02202 0.01574 -0.0628 0.5470 0.9590
5.000 0.8173 0.02317 0.01611 -0.0537 0.4116 0.9628
5.250 0.7980 0.02424 0.01670 -0.0444 0.3256 0.9677
5.500 0.7860 0.02530 0.01733 -0.0369 0.2476 0.9723
5.750 0.7914 0.02622 0.01777 -0.0333 0.1719 0.9754
6.000 0.8000 0.02705 0.01833 -0.0303 0.1317 0.9792
6.250 0.8070 0.02796 0.01906 -0.0269 0.1113 0.9837
6.500 0.8264 0.02842 0.01946 -0.0260 0.0969 0.9861
6.750 0.8456 0.02885 0.01990 -0.0251 0.0885 0.9887
7.000 0.8674 0.02958 0.02061 -0.0247 0.0822 0.9930
7.250 0.9211 0.02985 0.02087 -0.0311 0.0748 1.0000
7.500 0.9353 0.03065 0.02164 -0.0290 0.0719 1.0000
7.750 0.9486 0.03112 0.02220 -0.0267 0.0693 1.0000
8.000 0.9621 0.03164 0.02275 -0.0245 0.0666 1.0000
8.250 0.9778 0.03224 0.02334 -0.0228 0.0643 1.0000
8.500 1.0134 0.03343 0.02449 -0.0250 0.0615 1.0000
8.750 1.0288 0.03400 0.02520 -0.0230 0.0598 1.0000
9.000 1.0459 0.03467 0.02596 -0.0215 0.0577 1.0000
9.250 1.0643 0.03543 0.02679 -0.0203 0.0558 1.0000
9.500 1.0905 0.03644 0.02778 -0.0208 0.0540 1.0000
9.750 1.1325 0.03842 0.02991 -0.0244 0.0517 1.0000
10.000 1.1406 0.03931 0.03101 -0.0210 0.0504 1.0000
10.250 1.1539 0.04052 0.03242 -0.0189 0.0490 1.0000
10.500 1.1667 0.04177 0.03383 -0.0167 0.0479 1.0000
10.750 1.1760 0.04283 0.03497 -0.0139 0.0467 1.0000
11.000 1.1864 0.04403 0.03621 -0.0116 0.0456 1.0000
11.250 1.2066 0.04713 0.03950 -0.0116 0.0441 1.0000
11.500 1.1923 0.04810 0.04073 -0.0044 0.0437 1.0000
11.750 1.1796 0.04946 0.04237 0.0023 0.0433 1.0000
12.000 1.1673 0.05118 0.04435 0.0085 0.0429 1.0000
12.250 1.1529 0.05308 0.04652 0.0148 0.0426 1.0000
12.500 1.1363 0.05514 0.04883 0.0212 0.0423 1.0000
12.750 1.1171 0.05732 0.05126 0.0276 0.0421 1.0000
13.000 1.0955 0.05966 0.05385 0.0339 0.0419 1.0000
13.250 1.0719 0.06222 0.05664 0.0400 0.0418 1.0000
13.500 1.0463 0.06500 0.05965 0.0458 0.0418 1.0000
13.750 1.0186 0.06811 0.06297 0.0512 0.0418 1.0000
14.000 0.9889 0.07154 0.06662 0.0561 0.0418 1.0000
14.250 0.9573 0.07543 0.07070 0.0603 0.0420 1.0000
14.500 0.9240 0.07975 0.07521 0.0637 0.0422 1.0000
14.750 0.8900 0.08463 0.08026 0.0661 0.0425 1.0000
15.000 0.8559 0.09012 0.08589 0.0673 0.0429 1.0000
15.250 0.8221 0.09627 0.09217 0.0673 0.0433 1.0000
15.500 0.7910 0.10300 0.09899 0.0663 0.0437 1.0000
15.750 0.7643 0.11008 0.10613 0.0646 0.0442 1.0000
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