NACA 23018 (naca23018-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: NACA 23018 (naca23018-il) Reynolds number: 50,000 Max Cl/Cd: 26.17 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca23018-il-50000-n5.txt Download as CSV file: xf-naca23018-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 23018
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.500 -0.6727 0.10450 0.09564 -0.0399 1.0000 0.0922
-14.250 -0.7432 0.08914 0.08002 -0.0492 1.0000 0.0918
-14.000 -0.7917 0.07969 0.07029 -0.0540 1.0000 0.0916
-13.750 -0.8275 0.07303 0.06335 -0.0562 1.0000 0.0917
-13.500 -0.8560 0.06789 0.05791 -0.0567 1.0000 0.0921
-13.250 -0.8719 0.06413 0.05394 -0.0562 1.0000 0.0928
-13.000 -0.8634 0.06205 0.05185 -0.0555 1.0000 0.0943
-12.750 -0.8635 0.05962 0.04931 -0.0544 1.0000 0.0958
-12.500 -0.8661 0.05713 0.04667 -0.0530 1.0000 0.0973
-12.250 -0.8690 0.05472 0.04406 -0.0513 1.0000 0.0988
-12.000 -0.8714 0.05243 0.04152 -0.0491 1.0000 0.1004
-11.750 -0.8742 0.05031 0.03910 -0.0465 1.0000 0.1020
-11.500 -0.8538 0.04886 0.03775 -0.0459 1.0000 0.1044
-11.250 -0.8416 0.04738 0.03624 -0.0444 1.0000 0.1069
-11.000 -0.8320 0.04584 0.03456 -0.0425 1.0000 0.1097
-10.750 -0.8234 0.04432 0.03281 -0.0403 1.0000 0.1124
-10.500 -0.8019 0.04308 0.03170 -0.0396 1.0000 0.1156
-10.250 -0.7877 0.04191 0.03051 -0.0379 1.0000 0.1192
-10.000 -0.7750 0.04073 0.02919 -0.0359 1.0000 0.1232
-9.750 -0.7585 0.03963 0.02819 -0.0343 1.0000 0.1272
-9.500 -0.7471 0.03863 0.02720 -0.0321 1.0000 0.1317
-9.250 -0.7366 0.03766 0.02615 -0.0296 1.0000 0.1370
-9.000 -0.7285 0.03670 0.02532 -0.0268 1.0000 0.1419
-8.750 -0.7207 0.03577 0.02438 -0.0239 1.0000 0.1484
-8.500 -0.7161 0.03482 0.02353 -0.0206 1.0000 0.1548
-8.250 -0.7117 0.03392 0.02266 -0.0172 1.0000 0.1632
-8.000 -0.7104 0.03298 0.02187 -0.0134 1.0000 0.1717
-7.750 -0.7086 0.03208 0.02109 -0.0097 1.0000 0.1830
-7.500 -0.7074 0.03118 0.02034 -0.0058 1.0000 0.1975
-7.250 -0.7064 0.03030 0.01965 -0.0019 1.0000 0.2165
-7.000 -0.7045 0.02948 0.01905 0.0018 1.0000 0.2430
-6.750 -0.7022 0.02875 0.01857 0.0056 1.0000 0.2760
-6.500 -0.6979 0.02819 0.01822 0.0091 1.0000 0.3127
-6.250 -0.6916 0.02778 0.01797 0.0124 1.0000 0.3482
-6.000 -0.6835 0.02749 0.01777 0.0154 1.0000 0.3806
-5.750 -0.6518 0.02731 0.01768 0.0142 0.9919 0.4214
-5.500 -0.6166 0.02722 0.01766 0.0125 0.9814 0.4604
-5.250 -0.5825 0.02717 0.01764 0.0111 0.9703 0.4953
-5.000 -0.5472 0.02722 0.01776 0.0099 0.9594 0.5241
-4.750 -0.5090 0.02730 0.01787 0.0083 0.9495 0.5529
-4.500 -0.4771 0.02732 0.01791 0.0078 0.9372 0.5815
-4.250 -0.4420 0.02747 0.01810 0.0071 0.9256 0.6053
-4.000 -0.3992 0.02743 0.01803 0.0047 0.9163 0.6251
-3.750 -0.3653 0.02737 0.01793 0.0040 0.9031 0.6401
-3.500 -0.3213 0.02730 0.01784 0.0015 0.8933 0.6552
-3.250 -0.2857 0.02716 0.01765 0.0004 0.8805 0.6706
-3.000 -0.2539 0.02698 0.01742 0.0000 0.8671 0.6871
-2.750 -0.2081 0.02693 0.01736 -0.0023 0.8570 0.7008
-2.500 -0.1770 0.02687 0.01727 -0.0023 0.8418 0.7153
-2.250 -0.1437 0.02671 0.01706 -0.0027 0.8282 0.7312
-2.000 -0.1023 0.02662 0.01693 -0.0041 0.8159 0.7451
-1.750 -0.0695 0.02659 0.01689 -0.0042 0.7997 0.7587
-1.500 -0.0381 0.02647 0.01671 -0.0042 0.7844 0.7741
-1.250 0.0020 0.02638 0.01655 -0.0053 0.7701 0.7871
-1.000 0.0382 0.02632 0.01642 -0.0058 0.7538 0.8000
-0.750 0.0664 0.02625 0.01629 -0.0052 0.7359 0.8154
-0.500 0.1052 0.02629 0.01625 -0.0062 0.7178 0.8266
-0.250 0.1387 0.02626 0.01614 -0.0065 0.6999 0.8399
0.000 0.1695 0.02622 0.01599 -0.0064 0.6820 0.8543
0.250 0.2111 0.02627 0.01594 -0.0081 0.6628 0.8641
0.500 0.2425 0.02626 0.01580 -0.0082 0.6446 0.8780
0.750 0.2834 0.02632 0.01575 -0.0101 0.6248 0.8882
1.000 0.3185 0.02639 0.01572 -0.0112 0.6050 0.9003
1.250 0.3529 0.02648 0.01571 -0.0123 0.5855 0.9128
1.500 0.3937 0.02656 0.01570 -0.0147 0.5653 0.9227
1.750 0.4273 0.02668 0.01573 -0.0158 0.5465 0.9352
2.000 0.4664 0.02680 0.01575 -0.0181 0.5270 0.9457
2.250 0.5045 0.02693 0.01578 -0.0203 0.5082 0.9563
2.500 0.5410 0.02709 0.01586 -0.0222 0.4905 0.9673
2.750 0.5805 0.02723 0.01590 -0.0248 0.4727 0.9773
3.000 0.6205 0.02737 0.01593 -0.0276 0.4561 0.9865
3.250 0.6601 0.02756 0.01606 -0.0305 0.4397 0.9959
3.500 0.6867 0.02783 0.01631 -0.0310 0.4253 1.0000
3.750 0.7030 0.02807 0.01646 -0.0294 0.4146 1.0000
4.000 0.7179 0.02840 0.01678 -0.0276 0.4034 1.0000
4.250 0.7337 0.02874 0.01705 -0.0259 0.3938 1.0000
4.500 0.7482 0.02913 0.01744 -0.0240 0.3837 1.0000
4.750 0.7641 0.02952 0.01774 -0.0223 0.3753 1.0000
5.000 0.7777 0.03002 0.01829 -0.0203 0.3661 1.0000
5.250 0.7952 0.03039 0.01853 -0.0186 0.3590 1.0000
5.500 0.8067 0.03104 0.01928 -0.0164 0.3504 1.0000
5.750 0.8219 0.03152 0.01972 -0.0144 0.3431 1.0000
6.000 0.8372 0.03209 0.02026 -0.0126 0.3364 1.0000
6.250 0.8484 0.03281 0.02107 -0.0102 0.3291 1.0000
6.500 0.8649 0.03333 0.02152 -0.0085 0.3228 1.0000
6.750 0.8776 0.03407 0.02228 -0.0063 0.3165 1.0000
7.000 0.8878 0.03490 0.02321 -0.0039 0.3099 1.0000
7.250 0.9044 0.03547 0.02373 -0.0022 0.3041 1.0000
7.500 0.9165 0.03630 0.02458 0.0000 0.2983 1.0000
7.750 0.9233 0.03730 0.02572 0.0028 0.2920 1.0000
8.000 0.9384 0.03795 0.02634 0.0046 0.2863 1.0000
8.250 0.9516 0.03876 0.02713 0.0066 0.2808 1.0000
8.500 0.9526 0.04002 0.02856 0.0099 0.2747 1.0000
8.750 0.9654 0.04079 0.02933 0.0118 0.2691 1.0000
9.000 0.9829 0.04147 0.02994 0.0132 0.2639 1.0000
9.250 0.9754 0.04318 0.03189 0.0171 0.2584 1.0000
9.500 0.9815 0.04432 0.03309 0.0195 0.2530 1.0000
9.750 1.0069 0.04470 0.03335 0.0199 0.2481 1.0000
10.000 0.9903 0.04687 0.03574 0.0244 0.2437 1.0000
10.250 0.9745 0.04913 0.03818 0.0282 0.2391 1.0000
10.500 0.9806 0.05047 0.03955 0.0300 0.2345 1.0000
10.750 1.0095 0.05071 0.03967 0.0301 0.2301 1.0000
11.000 0.9576 0.05592 0.04524 0.0341 0.2264 1.0000
11.250 0.8904 0.06433 0.05394 0.0347 0.2217 1.0000
11.500 0.8927 0.06671 0.05635 0.0350 0.2173 1.0000
11.750 0.9522 0.06330 0.05280 0.0365 0.2138 1.0000
12.000 0.7374 0.09584 0.08577 0.0239 0.2006 1.0000
12.250 0.7665 0.09433 0.08426 0.0257 0.1987 1.0000
|
Polar data table (+)
Polar graphs
<< Back to NACA 23018 (naca23018-il)