NACA 4418 (naca4418-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 4418 (naca4418-il) Reynolds number: 100,000 Max Cl/Cd: 43.3 at α=10° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca4418-il-100000.txt Download as CSV file: xf-naca4418-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 4418
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.6440 0.07629 0.07104 -0.0563 1.0000 0.1198
-10.000 -0.6841 0.07280 0.06755 -0.0528 1.0000 0.1193
-9.750 -0.7313 0.06733 0.06195 -0.0502 1.0000 0.1185
-9.500 -0.7784 0.06061 0.05490 -0.0478 1.0000 0.1180
-9.250 -0.8042 0.05287 0.04645 -0.0481 0.9971 0.1190
-9.000 -0.7860 0.04826 0.04137 -0.0511 0.9908 0.1218
-8.750 -0.7465 0.04809 0.04135 -0.0537 0.9841 0.1256
-8.500 -0.7277 0.04415 0.03671 -0.0559 0.9771 0.1305
-8.250 -0.6965 0.04242 0.03487 -0.0581 0.9702 0.1346
-8.000 -0.6637 0.04153 0.03392 -0.0600 0.9630 0.1397
-7.750 -0.6357 0.03930 0.03120 -0.0618 0.9558 0.1454
-7.500 -0.6012 0.03901 0.03106 -0.0635 0.9486 0.1506
-7.250 -0.5716 0.03747 0.02896 -0.0650 0.9408 0.1574
-7.000 -0.5336 0.03698 0.02870 -0.0673 0.9347 0.1631
-6.750 -0.5064 0.03611 0.02756 -0.0679 0.9257 0.1697
-6.500 -0.4633 0.03520 0.02664 -0.0711 0.9209 0.1765
-6.250 -0.4415 0.03468 0.02602 -0.0705 0.9105 0.1825
-6.000 -0.4010 0.03362 0.02477 -0.0731 0.9049 0.1901
-5.750 -0.3745 0.03320 0.02437 -0.0732 0.8958 0.1966
-5.500 -0.3382 0.03235 0.02325 -0.0750 0.8889 0.2050
-5.250 -0.2920 0.03159 0.02261 -0.0783 0.8850 0.2144
-5.000 -0.2743 0.03121 0.02200 -0.0767 0.8731 0.2221
-4.750 -0.2312 0.03045 0.02141 -0.0794 0.8683 0.2331
-4.500 -0.2064 0.03004 0.02095 -0.0790 0.8587 0.2434
-4.250 -0.1699 0.02957 0.02043 -0.0804 0.8517 0.2577
-4.000 -0.1230 0.02885 0.01979 -0.0835 0.8482 0.2753
-3.750 -0.1072 0.02876 0.01980 -0.0816 0.8360 0.2872
-3.500 -0.0644 0.02809 0.01917 -0.0839 0.8313 0.3076
-3.250 -0.0155 0.02726 0.01839 -0.0872 0.8286 0.3306
-3.000 -0.0033 0.02735 0.01847 -0.0846 0.8154 0.3453
-2.750 0.0422 0.02654 0.01775 -0.0872 0.8118 0.3687
-2.500 0.0882 0.02566 0.01698 -0.0897 0.8089 0.3941
-2.250 0.1013 0.02582 0.01721 -0.0873 0.7958 0.4122
-2.000 0.1430 0.02502 0.01655 -0.0890 0.7917 0.4416
-1.750 0.1873 0.02414 0.01582 -0.0911 0.7888 0.4773
-1.500 0.1983 0.02441 0.01626 -0.0882 0.7754 0.5040
-1.250 0.2385 0.02360 0.01565 -0.0894 0.7713 0.5497
-1.000 0.2575 0.02361 0.01588 -0.0876 0.7612 0.5919
-0.750 0.2882 0.02310 0.01560 -0.0871 0.7544 0.6512
-0.500 0.3254 0.02231 0.01509 -0.0871 0.7505 0.7237
-0.250 0.3356 0.02266 0.01566 -0.0831 0.7389 0.7874
0.000 0.3721 0.02229 0.01541 -0.0826 0.7334 0.8589
0.250 0.4349 0.02184 0.01488 -0.0871 0.7297 0.9174
0.500 0.4863 0.02233 0.01533 -0.0914 0.7184 0.9577
0.750 0.5731 0.02187 0.01468 -0.1019 0.7126 0.9804
1.000 0.6527 0.02173 0.01442 -0.1120 0.7037 1.0000
1.250 0.6634 0.02176 0.01435 -0.1095 0.6946 1.0000
1.500 0.6890 0.02159 0.01402 -0.1092 0.6882 1.0000
1.750 0.6886 0.02213 0.01455 -0.1048 0.6772 1.0000
2.000 0.7207 0.02191 0.01417 -0.1053 0.6710 1.0000
2.250 0.7237 0.02255 0.01481 -0.1013 0.6608 1.0000
2.500 0.7511 0.02253 0.01467 -0.1010 0.6536 1.0000
2.750 0.7714 0.02281 0.01489 -0.0996 0.6459 1.0000
3.000 0.7859 0.02322 0.01526 -0.0973 0.6368 1.0000
3.250 0.8235 0.02305 0.01494 -0.0986 0.6310 1.0000
3.500 0.8271 0.02387 0.01581 -0.0947 0.6209 1.0000
3.750 0.8578 0.02388 0.01573 -0.0949 0.6139 1.0000
4.000 0.8797 0.02427 0.01608 -0.0938 0.6063 1.0000
4.250 0.8962 0.02474 0.01656 -0.0919 0.5974 1.0000
4.500 0.9357 0.02459 0.01626 -0.0935 0.5914 1.0000
4.750 0.9403 0.02550 0.01726 -0.0898 0.5816 1.0000
5.000 0.9723 0.02551 0.01719 -0.0902 0.5743 1.0000
5.250 0.9933 0.02598 0.01765 -0.0891 0.5663 1.0000
5.500 1.0123 0.02639 0.01807 -0.0875 0.5574 1.0000
5.750 1.0563 0.02613 0.01764 -0.0898 0.5510 1.0000
6.000 1.0559 0.02714 0.01882 -0.0854 0.5406 1.0000
6.250 1.0935 0.02698 0.01854 -0.0866 0.5334 1.0000
6.500 1.1032 0.02779 0.01944 -0.0838 0.5242 1.0000
6.750 1.1309 0.02792 0.01953 -0.0836 0.5161 1.0000
7.000 1.1559 0.02829 0.01989 -0.0830 0.5083 1.0000
7.250 1.1698 0.02886 0.02053 -0.0808 0.4990 1.0000
7.500 1.2135 0.02865 0.02015 -0.0830 0.4920 1.0000
7.750 1.2104 0.02974 0.02144 -0.0783 0.4820 1.0000
8.000 1.2512 0.02949 0.02105 -0.0800 0.4743 1.0000
8.250 1.2522 0.03051 0.02223 -0.0760 0.4648 1.0000
8.500 1.2862 0.03039 0.02203 -0.0767 0.4563 1.0000
8.750 1.2934 0.03121 0.02296 -0.0736 0.4470 1.0000
9.000 1.3221 0.03120 0.02289 -0.0735 0.4379 1.0000
9.250 1.3310 0.03191 0.02367 -0.0706 0.4285 1.0000
9.500 1.3598 0.03181 0.02350 -0.0705 0.4188 1.0000
9.750 1.3629 0.03261 0.02440 -0.0668 0.4090 1.0000
10.000 1.3985 0.03230 0.02394 -0.0676 0.3989 1.0000
10.250 1.3875 0.03340 0.02522 -0.0619 0.3895 1.0000
10.500 1.4265 0.03307 0.02469 -0.0633 0.3790 1.0000
10.750 1.4084 0.03437 0.02621 -0.0567 0.3699 1.0000
11.000 1.4356 0.03434 0.02605 -0.0564 0.3596 1.0000
11.250 1.4278 0.03549 0.02733 -0.0518 0.3499 1.0000
11.500 1.4415 0.03596 0.02775 -0.0499 0.3399 1.0000
11.750 1.4464 0.03672 0.02852 -0.0471 0.3297 1.0000
12.000 1.4462 0.03789 0.02975 -0.0440 0.3201 1.0000
12.250 1.4658 0.03810 0.02981 -0.0429 0.3095 1.0000
12.500 1.4506 0.04015 0.03206 -0.0387 0.3004 1.0000
12.750 1.4662 0.04066 0.03243 -0.0375 0.2903 1.0000
13.000 1.4549 0.04274 0.03467 -0.0342 0.2811 1.0000
13.250 1.4612 0.04392 0.03580 -0.0324 0.2717 1.0000
13.500 1.4590 0.04567 0.03760 -0.0303 0.2622 1.0000
13.750 1.4563 0.04765 0.03962 -0.0283 0.2533 1.0000
14.000 1.4640 0.04885 0.04072 -0.0269 0.2437 1.0000
14.250 1.4507 0.05182 0.04386 -0.0249 0.2352 1.0000
14.500 1.4617 0.05289 0.04478 -0.0238 0.2257 1.0000
14.750 1.4453 0.05637 0.04845 -0.0222 0.2175 1.0000
15.000 1.4497 0.05814 0.05015 -0.0211 0.2087 1.0000
15.250 1.4417 0.06114 0.05322 -0.0201 0.2004 1.0000
15.500 1.4392 0.06379 0.05588 -0.0193 0.1923 1.0000
15.750 1.4414 0.06593 0.05796 -0.0186 0.1839 1.0000
16.000 1.4304 0.06967 0.06182 -0.0180 0.1768 1.0000
16.250 1.4444 0.07066 0.06261 -0.0173 0.1686 1.0000
16.500 1.4242 0.07566 0.06787 -0.0173 0.1629 1.0000
16.750 1.4403 0.07642 0.06844 -0.0166 0.1554 1.0000
17.000 1.4202 0.08164 0.07391 -0.0169 0.1506 1.0000
17.250 1.4216 0.08426 0.07653 -0.0168 0.1449 1.0000
17.500 1.4243 0.08685 0.07912 -0.0167 0.1399 1.0000
17.750 1.4051 0.09231 0.08482 -0.0176 0.1361 1.0000
18.000 1.4467 0.08992 0.08206 -0.0159 0.1301 1.0000
18.250 1.4135 0.09724 0.08977 -0.0177 0.1280 1.0000
18.500 1.3857 0.10428 0.09710 -0.0198 0.1255 1.0000
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