NACA 23018 (naca23018-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 23018 (naca23018-il) Reynolds number: 200,000 Max Cl/Cd: 49.98 at α=7.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca23018-il-200000.txt Download as CSV file: xf-naca23018-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-17.000 -0.7724 0.11779 0.11327 -0.0324 1.0000 0.0626
-16.750 -0.8487 0.09925 0.09447 -0.0439 1.0000 0.0614
-16.500 -0.9147 0.08553 0.08044 -0.0524 1.0000 0.0606
-16.250 -0.9642 0.07606 0.07066 -0.0574 1.0000 0.0603
-16.000 -1.0009 0.06917 0.06349 -0.0601 1.0000 0.0602
-15.750 -1.0297 0.06377 0.05782 -0.0614 1.0000 0.0604
-15.500 -1.0532 0.05934 0.05313 -0.0615 1.0000 0.0606
-15.250 -1.0733 0.05559 0.04912 -0.0608 1.0000 0.0610
-15.000 -1.0908 0.05237 0.04563 -0.0594 1.0000 0.0614
-14.750 -1.1061 0.04961 0.04259 -0.0572 1.0000 0.0618
-14.500 -1.1207 0.04730 0.03999 -0.0543 1.0000 0.0622
-14.250 -1.1167 0.04504 0.03760 -0.0527 1.0000 0.0629
-14.000 -1.0978 0.04361 0.03622 -0.0522 1.0000 0.0640
-13.750 -1.0840 0.04237 0.03498 -0.0511 1.0000 0.0650
-13.500 -1.0770 0.04097 0.03347 -0.0491 1.0000 0.0660
-13.250 -1.0729 0.03951 0.03185 -0.0466 1.0000 0.0669
-13.000 -1.0703 0.03812 0.03027 -0.0436 1.0000 0.0678
-12.750 -1.0714 0.03697 0.02890 -0.0397 1.0000 0.0686
-12.500 -1.0516 0.03538 0.02727 -0.0391 1.0000 0.0698
-12.250 -1.0318 0.03433 0.02627 -0.0382 1.0000 0.0711
-12.000 -1.0197 0.03343 0.02534 -0.0360 1.0000 0.0723
-11.750 -1.0081 0.03252 0.02436 -0.0336 1.0000 0.0736
-11.500 -0.9978 0.03161 0.02334 -0.0309 1.0000 0.0748
-11.250 -0.9908 0.03086 0.02243 -0.0275 1.0000 0.0759
-11.000 -0.9669 0.02965 0.02132 -0.0272 1.0000 0.0775
-10.750 -0.9525 0.02893 0.02064 -0.0251 1.0000 0.0790
-10.500 -0.9413 0.02827 0.01996 -0.0223 1.0000 0.0805
-10.250 -0.9311 0.02762 0.01926 -0.0194 1.0000 0.0820
-10.000 -0.9225 0.02706 0.01860 -0.0161 1.0000 0.0834
-9.750 -0.9089 0.02623 0.01782 -0.0138 1.0000 0.0851
-9.500 -0.8988 0.02563 0.01729 -0.0110 1.0000 0.0868
-9.250 -0.8902 0.02513 0.01679 -0.0078 1.0000 0.0887
-9.000 -0.8815 0.02465 0.01628 -0.0046 1.0000 0.0906
-8.750 -0.8727 0.02423 0.01578 -0.0013 1.0000 0.0924
-8.500 -0.8639 0.02349 0.01515 0.0016 1.0000 0.0946
-8.250 -0.8554 0.02303 0.01473 0.0047 1.0000 0.0970
-8.000 -0.8404 0.02258 0.01427 0.0066 0.9992 0.1002
-7.750 -0.8027 0.02174 0.01350 0.0041 0.9945 0.1050
-7.500 -0.7647 0.02110 0.01287 0.0017 0.9896 0.1113
-7.250 -0.7290 0.02024 0.01212 -0.0005 0.9835 0.1194
-7.000 -0.6922 0.01939 0.01139 -0.0028 0.9784 0.1316
-6.750 -0.6606 0.01843 0.01059 -0.0041 0.9707 0.1526
-6.500 -0.6278 0.01703 0.00971 -0.0062 0.9658 0.2174
-6.250 -0.6041 0.01602 0.00922 -0.0060 0.9558 0.3084
-6.000 -0.5634 0.01550 0.00894 -0.0087 0.9514 0.3668
-5.750 -0.5328 0.01521 0.00872 -0.0092 0.9418 0.3993
-5.500 -0.4908 0.01488 0.00847 -0.0118 0.9369 0.4285
-5.250 -0.4552 0.01462 0.00824 -0.0131 0.9297 0.4519
-5.000 -0.4218 0.01434 0.00800 -0.0138 0.9209 0.4723
-4.750 -0.3828 0.01402 0.00771 -0.0156 0.9157 0.4925
-4.500 -0.3577 0.01379 0.00753 -0.0146 0.9028 0.5088
-4.250 -0.3234 0.01349 0.00726 -0.0152 0.8955 0.5272
-4.000 -0.2991 0.01330 0.00709 -0.0140 0.8818 0.5452
-3.750 -0.2721 0.01309 0.00693 -0.0132 0.8700 0.5654
-3.500 -0.2447 0.01287 0.00674 -0.0123 0.8578 0.5858
-3.250 -0.2201 0.01272 0.00662 -0.0111 0.8427 0.6051
-3.000 -0.1940 0.01256 0.00645 -0.0100 0.8283 0.6238
-2.750 -0.1662 0.01237 0.00627 -0.0093 0.8140 0.6399
-2.500 -0.1404 0.01222 0.00614 -0.0083 0.7964 0.6548
-2.250 -0.1145 0.01210 0.00600 -0.0074 0.7786 0.6702
-2.000 -0.0886 0.01202 0.00586 -0.0065 0.7608 0.6863
-1.750 -0.0617 0.01195 0.00580 -0.0057 0.7431 0.7013
-1.500 -0.0351 0.01192 0.00574 -0.0049 0.7257 0.7170
-1.250 -0.0088 0.01192 0.00567 -0.0040 0.7086 0.7336
-1.000 0.0166 0.01194 0.00565 -0.0031 0.6906 0.7509
-0.750 0.0432 0.01198 0.00570 -0.0023 0.6726 0.7664
-0.500 0.0697 0.01205 0.00575 -0.0015 0.6551 0.7819
-0.250 0.0959 0.01214 0.00579 -0.0006 0.6382 0.7979
0.000 0.1211 0.01225 0.00582 0.0004 0.6216 0.8145
0.250 0.1487 0.01241 0.00594 0.0010 0.6046 0.8279
0.500 0.1754 0.01257 0.00607 0.0018 0.5872 0.8417
0.750 0.2004 0.01273 0.00617 0.0028 0.5706 0.8567
1.000 0.2297 0.01298 0.00637 0.0031 0.5536 0.8675
1.250 0.2565 0.01321 0.00651 0.0038 0.5372 0.8799
1.500 0.2851 0.01350 0.00669 0.0041 0.5207 0.8911
1.750 0.3154 0.01375 0.00689 0.0041 0.5030 0.9007
2.000 0.3456 0.01403 0.00710 0.0040 0.4853 0.9109
2.250 0.3787 0.01433 0.00732 0.0033 0.4673 0.9190
2.500 0.4152 0.01467 0.00756 0.0017 0.4491 0.9261
2.750 0.4467 0.01496 0.00775 0.0012 0.4320 0.9352
3.000 0.4902 0.01533 0.00799 -0.0019 0.4129 0.9394
3.250 0.5265 0.01567 0.00820 -0.0037 0.3961 0.9471
3.500 0.5655 0.01598 0.00842 -0.0060 0.3798 0.9530
3.750 0.6079 0.01630 0.00867 -0.0090 0.3642 0.9580
4.000 0.6415 0.01663 0.00892 -0.0104 0.3514 0.9663
4.250 0.6851 0.01700 0.00914 -0.0138 0.3388 0.9704
4.500 0.7242 0.01725 0.00941 -0.0163 0.3276 0.9769
4.750 0.7640 0.01762 0.00965 -0.0191 0.3179 0.9822
5.000 0.8058 0.01784 0.00988 -0.0222 0.3079 0.9874
5.250 0.8446 0.01822 0.01015 -0.0249 0.2992 0.9929
5.500 0.8868 0.01837 0.01032 -0.0282 0.2893 0.9975
5.750 0.9178 0.01873 0.01056 -0.0294 0.2818 1.0000
6.000 0.9343 0.01889 0.01079 -0.0277 0.2760 1.0000
6.250 0.9507 0.01911 0.01100 -0.0260 0.2707 1.0000
6.500 0.9682 0.01951 0.01128 -0.0245 0.2657 1.0000
6.750 0.9837 0.01975 0.01160 -0.0225 0.2610 1.0000
7.000 0.9989 0.02000 0.01189 -0.0205 0.2561 1.0000
7.250 1.0140 0.02029 0.01215 -0.0184 0.2515 1.0000
7.500 1.0311 0.02079 0.01256 -0.0168 0.2469 1.0000
7.750 1.0439 0.02104 0.01293 -0.0143 0.2426 1.0000
8.000 1.0577 0.02135 0.01327 -0.0119 0.2381 1.0000
8.250 1.0721 0.02170 0.01358 -0.0098 0.2339 1.0000
8.500 1.0887 0.02224 0.01406 -0.0080 0.2295 1.0000
8.750 1.0993 0.02254 0.01448 -0.0051 0.2252 1.0000
9.000 1.1115 0.02287 0.01484 -0.0025 0.2208 1.0000
9.250 1.1257 0.02327 0.01519 -0.0003 0.2167 1.0000
9.500 1.1409 0.02385 0.01576 0.0016 0.2124 1.0000
9.750 1.1501 0.02421 0.01625 0.0047 0.2081 1.0000
10.000 1.1615 0.02458 0.01663 0.0073 0.2037 1.0000
10.250 1.1780 0.02513 0.01707 0.0089 0.1994 1.0000
10.500 1.1863 0.02566 0.01772 0.0119 0.1952 1.0000
10.750 1.1936 0.02610 0.01824 0.0150 0.1909 1.0000
11.000 1.2039 0.02656 0.01868 0.0176 0.1868 1.0000
11.250 1.2184 0.02727 0.01933 0.0192 0.1824 1.0000
11.500 1.2212 0.02785 0.02007 0.0226 0.1781 1.0000
11.750 1.2296 0.02841 0.02065 0.0249 0.1737 1.0000
12.000 1.2449 0.02914 0.02126 0.0261 0.1692 1.0000
12.250 1.2468 0.03001 0.02233 0.0289 0.1651 1.0000
12.500 1.2548 0.03084 0.02321 0.0306 0.1610 1.0000
12.750 1.2674 0.03166 0.02396 0.0318 0.1574 1.0000
13.000 1.2741 0.03285 0.02526 0.0334 0.1538 1.0000
13.250 1.2799 0.03405 0.02657 0.0348 0.1502 1.0000
13.500 1.2888 0.03514 0.02768 0.0359 0.1470 1.0000
13.750 1.3030 0.03618 0.02862 0.0366 0.1438 1.0000
14.000 1.3032 0.03792 0.03058 0.0379 0.1409 1.0000
14.250 1.3075 0.03950 0.03227 0.0387 0.1378 1.0000
14.500 1.3150 0.04091 0.03369 0.0394 0.1350 1.0000
14.750 1.3272 0.04215 0.03485 0.0399 0.1321 1.0000
15.000 1.3232 0.04457 0.03750 0.0404 0.1296 1.0000
15.250 1.3237 0.04675 0.03979 0.0407 0.1268 1.0000
15.500 1.3285 0.04858 0.04164 0.0408 0.1242 1.0000
15.750 1.3411 0.04982 0.04278 0.0412 0.1215 1.0000
16.000 1.3310 0.05321 0.04642 0.0409 0.1193 1.0000
16.250 1.3265 0.05624 0.04960 0.0404 0.1169 1.0000
16.500 1.3283 0.05866 0.05206 0.0401 0.1145 1.0000
16.750 1.3418 0.05978 0.05305 0.0403 0.1119 1.0000
17.000 1.3284 0.06409 0.05759 0.0391 0.1099 1.0000
17.250 1.3163 0.06844 0.06214 0.0377 0.1077 1.0000
17.500 1.3135 0.07171 0.06547 0.0367 0.1054 1.0000
17.750 1.3264 0.07287 0.06652 0.0367 0.1029 1.0000
18.000 1.3125 0.07770 0.07153 0.0350 0.1010 1.0000
18.250 1.2903 0.08395 0.07800 0.0323 0.0991 1.0000
18.500 1.2798 0.08862 0.08278 0.0302 0.0970 1.0000
18.750 1.2945 0.08951 0.08358 0.0303 0.0947 1.0000
19.000 1.2897 0.09330 0.08742 0.0289 0.0928 1.0000
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