NACA 23018 (naca23018-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 23018 (naca23018-il) Reynolds number: 100,000 Max Cl/Cd: 36.13 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca23018-il-100000.txt Download as CSV file: xf-naca23018-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.250 -0.8239 0.08224 0.07579 -0.0553 1.0000 0.1017
-14.000 -0.8531 0.07594 0.06934 -0.0570 1.0000 0.1012
-13.750 -0.8851 0.07040 0.06361 -0.0575 1.0000 0.1008
-13.500 -0.9149 0.06582 0.05882 -0.0566 1.0000 0.1004
-13.250 -0.9419 0.06204 0.05481 -0.0544 1.0000 0.1003
-13.000 -0.9658 0.05891 0.05145 -0.0509 1.0000 0.1003
-12.750 -0.9872 0.05628 0.04860 -0.0464 1.0000 0.1004
-12.500 -1.0030 0.05373 0.04578 -0.0422 1.0000 0.1006
-12.250 -1.0158 0.05140 0.04315 -0.0378 1.0000 0.1011
-12.000 -1.0268 0.04936 0.04077 -0.0331 1.0000 0.1018
-11.750 -1.0198 0.04688 0.03820 -0.0309 1.0000 0.1031
-11.500 -1.0024 0.04508 0.03643 -0.0298 1.0000 0.1049
-11.250 -0.9925 0.04343 0.03470 -0.0274 1.0000 0.1064
-11.000 -0.9855 0.04179 0.03289 -0.0246 1.0000 0.1078
-10.750 -0.9796 0.04027 0.03117 -0.0214 1.0000 0.1095
-10.500 -0.9749 0.03890 0.02953 -0.0179 1.0000 0.1113
-10.250 -0.9682 0.03752 0.02789 -0.0146 1.0000 0.1129
-10.000 -0.9462 0.03583 0.02633 -0.0139 1.0000 0.1154
-9.750 -0.9305 0.03465 0.02512 -0.0120 1.0000 0.1178
-9.500 -0.9162 0.03357 0.02394 -0.0098 1.0000 0.1207
-9.250 -0.9046 0.03262 0.02280 -0.0071 1.0000 0.1235
-9.000 -0.8831 0.03126 0.02155 -0.0061 1.0000 0.1268
-8.750 -0.8655 0.03029 0.02065 -0.0045 1.0000 0.1304
-8.500 -0.8511 0.02946 0.01974 -0.0022 1.0000 0.1345
-8.250 -0.8341 0.02847 0.01879 -0.0005 1.0000 0.1390
-8.000 -0.8186 0.02763 0.01809 0.0015 1.0000 0.1441
-7.750 -0.8052 0.02697 0.01733 0.0039 1.0000 0.1500
-7.500 -0.7917 0.02604 0.01665 0.0060 1.0000 0.1568
-7.250 -0.7801 0.02533 0.01598 0.0086 1.0000 0.1655
-7.000 -0.7704 0.02455 0.01536 0.0114 1.0000 0.1761
-6.750 -0.7620 0.02373 0.01473 0.0142 1.0000 0.1911
-6.500 -0.7549 0.02282 0.01412 0.0172 1.0000 0.2153
-6.250 -0.7497 0.02176 0.01355 0.0204 1.0000 0.2663
-6.000 -0.7444 0.02098 0.01332 0.0236 1.0000 0.3459
-5.750 -0.7276 0.02080 0.01338 0.0250 0.9982 0.4057
-5.500 -0.6838 0.02099 0.01359 0.0216 0.9889 0.4559
-5.250 -0.6373 0.02123 0.01393 0.0180 0.9799 0.4913
-5.000 -0.5962 0.02132 0.01403 0.0153 0.9688 0.5199
-4.750 -0.5556 0.02141 0.01420 0.0130 0.9576 0.5446
-4.500 -0.5120 0.02151 0.01436 0.0103 0.9474 0.5698
-4.250 -0.4705 0.02160 0.01451 0.0081 0.9363 0.5964
-4.000 -0.4347 0.02165 0.01461 0.0071 0.9237 0.6206
-3.750 -0.3843 0.02172 0.01476 0.0038 0.9161 0.6467
-3.500 -0.3511 0.02178 0.01490 0.0036 0.9023 0.6685
-3.250 -0.2951 0.02168 0.01484 -0.0006 0.8964 0.6896
-3.000 -0.2636 0.02154 0.01472 -0.0005 0.8816 0.7055
-2.750 -0.2186 0.02136 0.01458 -0.0026 0.8720 0.7201
-2.500 -0.1796 0.02110 0.01432 -0.0036 0.8598 0.7356
-2.250 -0.1477 0.02088 0.01407 -0.0034 0.8459 0.7522
-2.000 -0.1012 0.02063 0.01381 -0.0052 0.8363 0.7663
-1.750 -0.0693 0.02055 0.01374 -0.0046 0.8200 0.7799
-1.500 -0.0383 0.02039 0.01353 -0.0040 0.8048 0.7956
-1.250 0.0022 0.02030 0.01339 -0.0046 0.7913 0.8083
-1.000 0.0381 0.02028 0.01331 -0.0046 0.7747 0.8206
-0.750 0.0651 0.02025 0.01321 -0.0034 0.7567 0.8362
-0.500 0.1082 0.02046 0.01335 -0.0048 0.7382 0.8449
-0.250 0.1398 0.02051 0.01331 -0.0045 0.7201 0.8587
0.000 0.1826 0.02071 0.01339 -0.0062 0.7008 0.8682
0.250 0.2191 0.02081 0.01338 -0.0070 0.6818 0.8801
0.500 0.2624 0.02098 0.01342 -0.0091 0.6612 0.8901
0.750 0.3038 0.02109 0.01339 -0.0111 0.6404 0.9005
1.000 0.3422 0.02120 0.01337 -0.0127 0.6196 0.9125
1.250 0.3881 0.02130 0.01334 -0.0158 0.5969 0.9213
1.500 0.4228 0.02141 0.01331 -0.0170 0.5762 0.9344
1.750 0.4700 0.02150 0.01327 -0.0206 0.5529 0.9433
2.000 0.5101 0.02160 0.01323 -0.0230 0.5312 0.9543
2.250 0.5492 0.02174 0.01323 -0.0254 0.5102 0.9661
2.500 0.5967 0.02178 0.01313 -0.0296 0.4882 0.9748
2.750 0.6417 0.02184 0.01306 -0.0333 0.4679 0.9844
3.000 0.6870 0.02191 0.01302 -0.0372 0.4493 0.9936
3.250 0.7288 0.02197 0.01295 -0.0406 0.4328 1.0000
3.500 0.7470 0.02212 0.01300 -0.0395 0.4207 1.0000
3.750 0.7649 0.02237 0.01324 -0.0384 0.4093 1.0000
4.000 0.7841 0.02259 0.01332 -0.0373 0.3995 1.0000
4.250 0.8015 0.02291 0.01368 -0.0361 0.3892 1.0000
4.500 0.8210 0.02317 0.01382 -0.0350 0.3804 1.0000
4.750 0.8384 0.02357 0.01427 -0.0336 0.3718 1.0000
5.000 0.8568 0.02390 0.01456 -0.0323 0.3636 1.0000
5.250 0.8759 0.02436 0.01493 -0.0312 0.3565 1.0000
5.500 0.8910 0.02480 0.01549 -0.0293 0.3485 1.0000
5.750 0.9105 0.02520 0.01576 -0.0281 0.3418 1.0000
6.000 0.9261 0.02577 0.01639 -0.0263 0.3348 1.0000
6.250 0.9411 0.02620 0.01687 -0.0244 0.3272 1.0000
6.500 0.9626 0.02666 0.01713 -0.0235 0.3208 1.0000
6.750 0.9731 0.02728 0.01795 -0.0208 0.3140 1.0000
7.000 0.9885 0.02776 0.01844 -0.0189 0.3074 1.0000
7.250 1.0117 0.02836 0.01883 -0.0182 0.3016 1.0000
7.500 1.0190 0.02908 0.01981 -0.0150 0.2956 1.0000
7.750 1.0327 0.02968 0.02046 -0.0128 0.2896 1.0000
8.000 1.0557 0.03024 0.02085 -0.0121 0.2841 1.0000
8.250 1.0636 0.03115 0.02195 -0.0091 0.2786 1.0000
8.500 1.0739 0.03189 0.02280 -0.0065 0.2728 1.0000
8.750 1.0952 0.03242 0.02321 -0.0055 0.2673 1.0000
9.000 1.1064 0.03344 0.02433 -0.0031 0.2621 1.0000
9.250 1.1122 0.03437 0.02543 0.0001 0.2564 1.0000
9.500 1.1301 0.03497 0.02599 0.0016 0.2510 1.0000
9.750 1.1479 0.03598 0.02696 0.0028 0.2459 1.0000
10.000 1.1467 0.03717 0.02840 0.0069 0.2406 1.0000
10.250 1.1595 0.03794 0.02921 0.0089 0.2353 1.0000
10.500 1.1890 0.03879 0.02985 0.0084 0.2301 1.0000
10.750 1.1767 0.04041 0.03184 0.0136 0.2257 1.0000
11.000 1.1808 0.04160 0.03316 0.0165 0.2207 1.0000
11.250 1.2097 0.04206 0.03346 0.0162 0.2157 1.0000
11.500 1.2066 0.04390 0.03548 0.0196 0.2118 1.0000
11.750 1.1874 0.04600 0.03786 0.0247 0.2082 1.0000
12.000 1.1851 0.04742 0.03938 0.0279 0.2043 1.0000
12.250 1.2457 0.04724 0.03885 0.0239 0.1984 1.0000
12.500 1.2034 0.05001 0.04199 0.0310 0.1966 1.0000
12.750 1.1554 0.05413 0.04645 0.0362 0.1948 1.0000
13.000 1.0715 0.06257 0.05529 0.0389 0.1941 1.0000
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Polar data table (+)
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