NACA 23024 (naca23024-il) Xfoil prediction polar at RE=100,000 Ncrit=9
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Airfoil: NACA 23024 (naca23024-il) Reynolds number: 100,000 Max Cl/Cd: 34.16 at α=7.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca23024-il-100000.txt Download as CSV file: xf-naca23024-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 23024
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
------ -------- --------- --------- -------- -------- --------
-16.750 -0.9507 0.06823 0.06056 -0.0725 1.0000 0.1800
-16.500 -1.0170 0.06055 0.05253 -0.0718 1.0000 0.1824
-16.250 -1.0641 0.05550 0.04717 -0.0696 1.0000 0.1850
-16.000 -1.0011 0.05805 0.05013 -0.0694 1.0000 0.1915
-15.750 -1.0319 0.05421 0.04610 -0.0672 1.0000 0.1950
-15.500 -1.0763 0.05016 0.04174 -0.0636 1.0000 0.1980
-15.250 -1.0285 0.05136 0.04331 -0.0636 1.0000 0.2049
-15.000 -1.0505 0.04878 0.04059 -0.0605 1.0000 0.2093
-14.750 -1.0913 0.04573 0.03725 -0.0554 1.0000 0.2127
-14.500 -1.0477 0.04644 0.03832 -0.0558 1.0000 0.2200
-14.250 -1.0707 0.04443 0.03619 -0.0514 1.0000 0.2249
-14.000 -1.0901 0.04269 0.03434 -0.0467 1.0000 0.2295
-13.750 -1.0679 0.04272 0.03458 -0.0455 1.0000 0.2365
-13.500 -1.0938 0.04116 0.03288 -0.0397 1.0000 0.2412
-13.250 -1.1004 0.04021 0.03194 -0.0355 1.0000 0.2467
-13.000 -1.0923 0.03994 0.03180 -0.0327 1.0000 0.2533
-12.750 -1.1203 0.03883 0.03056 -0.0256 1.0000 0.2579
-12.500 -1.1296 0.03810 0.02983 -0.0205 1.0000 0.2633
-12.250 -1.1221 0.03795 0.02982 -0.0174 1.0000 0.2698
-12.000 -1.1484 0.03725 0.02901 -0.0097 1.0000 0.2746
-11.750 -1.1884 0.03659 0.02816 0.0003 1.0000 0.2779
-11.500 -1.1585 0.03655 0.02842 0.0001 1.0000 0.2860
-11.250 -1.1796 0.03620 0.02801 0.0076 1.0000 0.2909
-11.000 -1.2134 0.03569 0.02732 0.0171 1.0000 0.2950
-10.750 -1.1997 0.03552 0.02733 0.0192 1.0000 0.3019
-10.500 -1.2053 0.03526 0.02709 0.0243 1.0000 0.3081
-10.250 -1.2279 0.03469 0.02632 0.0321 1.0000 0.3136
-10.000 -1.2147 0.03453 0.02633 0.0342 1.0000 0.3205
-9.750 -1.1927 0.03454 0.02628 0.0344 0.9935 0.3304
-9.500 -1.1539 0.03453 0.02636 0.0319 0.9848 0.3406
-9.250 -1.1277 0.03450 0.02622 0.0315 0.9752 0.3512
-9.000 -1.0879 0.03446 0.02631 0.0290 0.9666 0.3610
-8.750 -1.0673 0.03426 0.02602 0.0298 0.9558 0.3709
-8.500 -1.0211 0.03424 0.02609 0.0263 0.9488 0.3812
-8.250 -1.0043 0.03397 0.02578 0.0280 0.9370 0.3904
-8.000 -0.9672 0.03376 0.02558 0.0262 0.9293 0.4004
-7.750 -0.9415 0.03361 0.02547 0.0265 0.9182 0.4097
-7.500 -0.9091 0.03323 0.02502 0.0255 0.9107 0.4200
-7.250 -0.8827 0.03317 0.02507 0.0259 0.8989 0.4285
-7.000 -0.8527 0.03264 0.02436 0.0254 0.8920 0.4397
-6.750 -0.8275 0.03263 0.02453 0.0260 0.8796 0.4472
-6.500 -0.7991 0.03218 0.02397 0.0261 0.8715 0.4581
-6.250 -0.7361 0.03184 0.02376 0.0202 0.8679 0.4691
-6.000 -0.7417 0.03175 0.02365 0.0261 0.8516 0.4763
-5.750 -0.6978 0.03113 0.02300 0.0236 0.8462 0.4874
-5.500 -0.6810 0.03117 0.02311 0.0258 0.8334 0.4956
-5.250 -0.6631 0.03055 0.02232 0.0279 0.8247 0.5065
-5.000 -0.5909 0.03006 0.02204 0.0208 0.8216 0.5180
-4.750 -0.6027 0.03006 0.02195 0.0278 0.8058 0.5264
-4.500 -0.5451 0.02945 0.02144 0.0233 0.8012 0.5375
-4.250 -0.5005 0.02861 0.02052 0.0212 0.7973 0.5510
-4.000 -0.4919 0.02875 0.02075 0.0248 0.7826 0.5586
-3.750 -0.4412 0.02809 0.02011 0.0216 0.7775 0.5717
-3.500 -0.3627 0.02731 0.01941 0.0134 0.7747 0.5849
-3.250 -0.3696 0.02742 0.01952 0.0200 0.7601 0.5941
-3.000 -0.3040 0.02677 0.01890 0.0139 0.7546 0.6072
-2.750 -0.2353 0.02600 0.01809 0.0074 0.7502 0.6222
-2.500 -0.2230 0.02616 0.01834 0.0106 0.7363 0.6309
-2.250 -0.1638 0.02567 0.01783 0.0057 0.7289 0.6446
-2.000 -0.1006 0.02542 0.01759 0.0000 0.7197 0.6561
-1.750 -0.0836 0.02541 0.01760 0.0025 0.7072 0.6674
-1.500 0.0008 0.02504 0.01716 -0.0070 0.6985 0.6796
-1.250 0.0044 0.02533 0.01753 -0.0020 0.6844 0.6897
-1.000 0.0711 0.02499 0.01705 -0.0084 0.6749 0.7022
-0.750 0.0959 0.02547 0.01764 -0.0072 0.6600 0.7106
-0.500 0.1283 0.02510 0.01709 -0.0075 0.6508 0.7246
-0.250 0.1784 0.02576 0.01786 -0.0108 0.6351 0.7308
0.000 0.2435 0.02606 0.01804 -0.0168 0.6226 0.7395
0.250 0.2464 0.02612 0.01813 -0.0119 0.6108 0.7514
0.500 0.3317 0.02679 0.01870 -0.0214 0.5956 0.7552
0.750 0.3778 0.02718 0.01903 -0.0240 0.5823 0.7631
1.000 0.3912 0.02726 0.01909 -0.0211 0.5720 0.7748
1.250 0.4578 0.02794 0.01965 -0.0271 0.5572 0.7781
1.500 0.4905 0.02853 0.02027 -0.0274 0.5443 0.7855
1.750 0.5060 0.02841 0.02005 -0.0250 0.5344 0.7980
2.000 0.5522 0.02921 0.02086 -0.0275 0.5206 0.8022
2.250 0.6051 0.02961 0.02106 -0.0314 0.5084 0.8085
2.500 0.6005 0.02970 0.02125 -0.0257 0.4988 0.8223
2.750 0.6599 0.03018 0.02155 -0.0308 0.4859 0.8267
3.000 0.6458 0.03020 0.02167 -0.0234 0.4781 0.8436
3.250 0.7031 0.03066 0.02199 -0.0283 0.4648 0.8473
3.500 0.7367 0.03121 0.02259 -0.0292 0.4527 0.8544
3.750 0.7442 0.03123 0.02255 -0.0257 0.4446 0.8687
4.000 0.7900 0.03176 0.02306 -0.0288 0.4327 0.8740
4.250 0.8230 0.03200 0.02322 -0.0298 0.4224 0.8834
4.500 0.8442 0.03233 0.02351 -0.0289 0.4139 0.8940
4.750 0.8795 0.03269 0.02389 -0.0305 0.4032 0.9019
5.250 0.9349 0.03341 0.02462 -0.0312 0.3856 0.9211
5.500 0.9635 0.03362 0.02467 -0.0317 0.3782 0.9320
5.750 0.9969 0.03411 0.02526 -0.0334 0.3692 0.9399
6.000 1.0213 0.03441 0.02556 -0.0333 0.3615 0.9503
6.250 1.0692 0.03470 0.02569 -0.0376 0.3537 0.9576
6.500 1.0857 0.03521 0.02641 -0.0365 0.3462 0.9682
6.750 1.1219 0.03546 0.02655 -0.0387 0.3392 0.9776
7.000 1.1627 0.03578 0.02687 -0.0421 0.3320 0.9852
7.250 1.1900 0.03614 0.02738 -0.0433 0.3246 0.9950
7.500 1.2342 0.03613 0.02718 -0.0471 0.3182 1.0000
7.750 1.2368 0.03682 0.02790 -0.0436 0.3141 1.0000
8.000 1.2189 0.03756 0.02884 -0.0368 0.3102 1.0000
8.250 1.2088 0.03818 0.02954 -0.0313 0.3064 1.0000
8.500 1.2134 0.03854 0.02987 -0.0280 0.3022 1.0000
8.750 1.2517 0.03894 0.03000 -0.0303 0.2974 1.0000
9.000 1.2199 0.03986 0.03115 -0.0214 0.2949 1.0000
9.250 1.1876 0.04068 0.03214 -0.0124 0.2922 1.0000
9.500 1.1556 0.04142 0.03300 -0.0035 0.2898 1.0000
9.750 1.1340 0.04220 0.03385 0.0035 0.2871 1.0000
10.000 1.1394 0.04259 0.03419 0.0066 0.2834 1.0000
10.250 1.1808 0.04306 0.03446 0.0042 0.2786 1.0000
10.500 1.1296 0.04442 0.03602 0.0151 0.2771 1.0000
10.750 1.0748 0.04648 0.03828 0.0251 0.2752 1.0000
11.000 1.0132 0.04960 0.04161 0.0343 0.2731 1.0000
11.250 0.4140 0.11903 0.11196 0.0340 0.2602 1.0000
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