NACA 23024 (naca23024-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 23024 (naca23024-il) Reynolds number: 100,000 Max Cl/Cd: 28.49 at α=9.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca23024-il-100000-n5.txt Download as CSV file: xf-naca23024-il-100000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-19.500 -0.7868 0.11309 0.10534 -0.0606 1.0000 0.1124
-19.250 -0.8322 0.10310 0.09506 -0.0648 1.0000 0.1160
-19.000 -0.8255 0.10130 0.09330 -0.0648 1.0000 0.1182
-18.750 -0.8231 0.09889 0.09090 -0.0651 1.0000 0.1208
-18.500 -0.8373 0.09401 0.08591 -0.0666 1.0000 0.1240
-18.250 -0.8487 0.08967 0.08146 -0.0676 1.0000 0.1271
-18.000 -0.8428 0.08789 0.07975 -0.0675 1.0000 0.1299
-17.750 -0.8490 0.08439 0.07619 -0.0681 1.0000 0.1332
-17.500 -0.8623 0.08001 0.07167 -0.0689 1.0000 0.1369
-17.250 -0.8569 0.07830 0.07004 -0.0686 1.0000 0.1400
-17.000 -0.8620 0.07519 0.06689 -0.0687 1.0000 0.1437
-16.750 -0.8729 0.07141 0.06298 -0.0690 1.0000 0.1479
-16.500 -0.8697 0.06954 0.06119 -0.0685 1.0000 0.1514
-16.250 -0.8757 0.06659 0.05819 -0.0684 1.0000 0.1557
-16.000 -0.8825 0.06361 0.05514 -0.0680 1.0000 0.1601
-15.750 -0.8828 0.06153 0.05312 -0.0673 1.0000 0.1641
-15.500 -0.8904 0.05870 0.05021 -0.0667 1.0000 0.1691
-15.250 -0.8940 0.05640 0.04790 -0.0658 1.0000 0.1736
-15.000 -0.8973 0.05428 0.04579 -0.0647 1.0000 0.1783
-14.750 -0.9046 0.05182 0.04323 -0.0635 1.0000 0.1836
-14.500 -0.9071 0.05000 0.04147 -0.0619 1.0000 0.1883
-14.250 -0.9125 0.04803 0.03948 -0.0602 1.0000 0.1937
-14.000 -0.9184 0.04609 0.03747 -0.0583 1.0000 0.1990
-13.750 -0.9213 0.04461 0.03605 -0.0561 1.0000 0.2039
-13.500 -0.9274 0.04296 0.03435 -0.0537 1.0000 0.2095
-13.250 -0.9330 0.04150 0.03288 -0.0510 1.0000 0.2149
-13.000 -0.9379 0.04027 0.03168 -0.0481 1.0000 0.2200
-12.750 -0.9455 0.03896 0.03031 -0.0447 1.0000 0.2257
-12.500 -0.9516 0.03791 0.02928 -0.0412 1.0000 0.2309
-12.250 -0.9584 0.03697 0.02836 -0.0375 1.0000 0.2359
-12.000 -0.9674 0.03602 0.02735 -0.0333 1.0000 0.2415
-11.750 -0.9754 0.03523 0.02657 -0.0291 1.0000 0.2464
-11.500 -0.9587 0.03434 0.02568 -0.0291 0.9958 0.2538
-11.250 -0.9366 0.03341 0.02468 -0.0300 0.9896 0.2622
-11.000 -0.9149 0.03265 0.02394 -0.0305 0.9829 0.2700
-10.750 -0.8934 0.03184 0.02302 -0.0311 0.9765 0.2788
-10.500 -0.8719 0.03120 0.02245 -0.0310 0.9685 0.2860
-10.250 -0.8524 0.03048 0.02161 -0.0309 0.9610 0.2947
-10.000 -0.8302 0.02992 0.02111 -0.0306 0.9526 0.3019
-9.750 -0.8098 0.02932 0.02047 -0.0302 0.9448 0.3100
-9.250 -0.7635 0.02826 0.01940 -0.0297 0.9294 0.3257
-9.000 -0.7500 0.02771 0.01873 -0.0277 0.9187 0.3337
-8.750 -0.7163 0.02724 0.01835 -0.0290 0.9137 0.3416
-8.500 -0.7041 0.02683 0.01790 -0.0264 0.9022 0.3491
-8.250 -0.6766 0.02630 0.01736 -0.0265 0.8955 0.3572
-8.000 -0.6415 0.02578 0.01685 -0.0279 0.8912 0.3657
-7.750 -0.6368 0.02547 0.01646 -0.0238 0.8769 0.3730
-7.500 -0.6002 0.02499 0.01605 -0.0253 0.8712 0.3808
-7.250 -0.5793 0.02463 0.01566 -0.0240 0.8615 0.3888
-7.000 -0.5601 0.02425 0.01521 -0.0224 0.8510 0.3967
-6.750 -0.5172 0.02377 0.01480 -0.0250 0.8455 0.4052
-6.500 -0.5077 0.02354 0.01451 -0.0215 0.8324 0.4128
-6.250 -0.4716 0.02311 0.01410 -0.0229 0.8242 0.4212
-6.000 -0.4386 0.02275 0.01373 -0.0237 0.8157 0.4301
-5.750 -0.4266 0.02248 0.01337 -0.0206 0.8028 0.4383
-5.500 -0.3764 0.02204 0.01299 -0.0246 0.7959 0.4473
-5.250 -0.3691 0.02191 0.01283 -0.0205 0.7816 0.4551
-5.000 -0.3294 0.02151 0.01240 -0.0226 0.7730 0.4646
-4.750 -0.3140 0.02139 0.01231 -0.0199 0.7595 0.4724
-4.500 -0.2849 0.02107 0.01187 -0.0200 0.7497 0.4827
-4.250 -0.2626 0.02096 0.01184 -0.0186 0.7368 0.4903
-4.000 -0.2323 0.02072 0.01154 -0.0188 0.7261 0.5002
-3.750 -0.2173 0.02062 0.01142 -0.0162 0.7136 0.5088
-3.500 -0.1857 0.02046 0.01126 -0.0166 0.7026 0.5180
-3.250 -0.1734 0.02037 0.01111 -0.0134 0.6906 0.5277
-3.000 -0.1440 0.02026 0.01103 -0.0133 0.6793 0.5367
-2.750 -0.1247 0.02019 0.01093 -0.0114 0.6680 0.5464
-2.500 -0.1062 0.02011 0.01083 -0.0094 0.6564 0.5560
-2.250 -0.0790 0.02007 0.01078 -0.0089 0.6459 0.5658
-2.000 -0.0704 0.02002 0.01068 -0.0050 0.6344 0.5762
-1.750 -0.0356 0.01998 0.01066 -0.0060 0.6240 0.5856
-1.500 -0.0262 0.01999 0.01067 -0.0022 0.6125 0.5963
-1.250 0.0034 0.01995 0.01059 -0.0022 0.6023 0.6064
-1.000 0.0167 0.01999 0.01068 0.0009 0.5908 0.6168
-0.750 0.0372 0.01997 0.01061 0.0026 0.5806 0.6278
-0.500 0.0587 0.02004 0.01071 0.0041 0.5696 0.6383
-0.250 0.0709 0.02002 0.01065 0.0073 0.5595 0.6501
0.000 0.1006 0.02012 0.01078 0.0073 0.5487 0.6602
0.250 0.1090 0.02013 0.01077 0.0113 0.5385 0.6728
0.500 0.1430 0.02025 0.01088 0.0104 0.5283 0.6829
0.750 0.1524 0.02031 0.01098 0.0141 0.5181 0.6954
1.000 0.1850 0.02045 0.01108 0.0135 0.5083 0.7061
1.250 0.1978 0.02056 0.01123 0.0165 0.4984 0.7186
1.500 0.2253 0.02073 0.01140 0.0168 0.4884 0.7295
1.750 0.2459 0.02088 0.01155 0.0184 0.4791 0.7418
2.000 0.2696 0.02109 0.01179 0.0193 0.4690 0.7528
2.250 0.2977 0.02131 0.01195 0.0195 0.4602 0.7646
2.500 0.3167 0.02155 0.01226 0.0213 0.4503 0.7760
2.750 0.3469 0.02182 0.01247 0.0210 0.4409 0.7868
3.000 0.3641 0.02206 0.01276 0.0230 0.4317 0.7987
3.250 0.3958 0.02242 0.01310 0.0224 0.4220 0.8083
3.500 0.4121 0.02264 0.01329 0.0246 0.4141 0.8210
3.750 0.4494 0.02311 0.01379 0.0227 0.4034 0.8284
4.000 0.4599 0.02326 0.01385 0.0261 0.3968 0.8430
4.250 0.4989 0.02381 0.01447 0.0237 0.3859 0.8486
4.500 0.5313 0.02423 0.01483 0.0228 0.3773 0.8565
4.750 0.5439 0.02453 0.01516 0.0255 0.3697 0.8691
5.000 0.5788 0.02507 0.01569 0.0239 0.3604 0.8747
5.250 0.6053 0.02552 0.01607 0.0239 0.3529 0.8834
5.500 0.6227 0.02594 0.01655 0.0255 0.3449 0.8935
5.750 0.6556 0.02648 0.01703 0.0243 0.3373 0.8990
6.000 0.6739 0.02696 0.01752 0.0256 0.3303 0.9093
6.500 0.7305 0.02801 0.01848 0.0243 0.3163 0.9226
6.750 0.7465 0.02857 0.01912 0.0257 0.3095 0.9328
7.000 0.7754 0.02914 0.01970 0.0247 0.3024 0.9389
7.250 0.7964 0.02965 0.02009 0.0253 0.2973 0.9487
7.500 0.8233 0.03032 0.02088 0.0242 0.2904 0.9546
7.750 0.8424 0.03096 0.02152 0.0248 0.2848 0.9640
8.000 0.8746 0.03146 0.02190 0.0230 0.2794 0.9690
8.250 0.8940 0.03226 0.02283 0.0230 0.2737 0.9775
8.500 0.9213 0.03291 0.02351 0.0216 0.2679 0.9828
8.750 0.9498 0.03349 0.02402 0.0202 0.2632 0.9887
9.000 0.9746 0.03432 0.02492 0.0190 0.2578 0.9947
9.250 1.0011 0.03514 0.02580 0.0174 0.2524 0.9999
9.500 0.9998 0.03572 0.02636 0.0209 0.2493 1.0000
9.750 1.0025 0.03622 0.02677 0.0240 0.2463 1.0000
10.000 0.9981 0.03703 0.02765 0.0278 0.2430 1.0000
10.250 0.9926 0.03797 0.02866 0.0315 0.2396 1.0000
10.500 0.9901 0.03887 0.02958 0.0347 0.2363 1.0000
10.750 0.9914 0.03968 0.03038 0.0375 0.2332 1.0000
11.000 0.9991 0.04031 0.03093 0.0396 0.2303 1.0000
11.250 0.9955 0.04156 0.03225 0.0424 0.2272 1.0000
11.500 0.9895 0.04303 0.03382 0.0452 0.2238 1.0000
11.750 0.9883 0.04434 0.03516 0.0475 0.2206 1.0000
12.000 0.9919 0.04542 0.03623 0.0494 0.2176 1.0000
12.250 1.0033 0.04609 0.03682 0.0507 0.2148 1.0000
12.500 0.9941 0.04818 0.03903 0.0529 0.2118 1.0000
12.750 0.9837 0.05048 0.04146 0.0549 0.2085 1.0000
13.000 0.9809 0.05234 0.04338 0.0563 0.2054 1.0000
13.250 0.9854 0.05368 0.04471 0.0575 0.2026 1.0000
13.500 1.0012 0.05420 0.04513 0.0583 0.2001 1.0000
13.750 0.9772 0.05811 0.04926 0.0596 0.1971 1.0000
14.000 0.9553 0.06216 0.05348 0.0604 0.1938 1.0000
14.250 0.9475 0.06503 0.05642 0.0609 0.1907 1.0000
14.500 0.9571 0.06618 0.05753 0.0615 0.1882 1.0000
14.750 0.9687 0.06717 0.05847 0.0621 0.1858 1.0000
15.000 0.8161 0.08813 0.08010 0.0574 0.1782 1.0000
15.250 0.8239 0.08970 0.08165 0.0576 0.1758 1.0000
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