NACA 23015 (naca23015-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 23015 (naca23015-il) Reynolds number: 50,000 Max Cl/Cd: 27.17 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca23015-il-50000-n5.txt Download as CSV file: xf-naca23015-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 23015
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
------ -------- --------- --------- -------- -------- --------
-12.500 -0.6514 0.09556 0.08743 -0.0353 1.0000 0.0775
-12.250 -0.6838 0.08686 0.07864 -0.0408 1.0000 0.0771
-12.000 -0.7167 0.07977 0.07142 -0.0445 1.0000 0.0768
-11.750 -0.7479 0.07420 0.06567 -0.0459 1.0000 0.0767
-11.500 -0.7769 0.06984 0.06110 -0.0451 1.0000 0.0767
-11.250 -0.8031 0.06634 0.05738 -0.0424 1.0000 0.0769
-11.000 -0.8242 0.06294 0.05366 -0.0395 1.0000 0.0774
-10.750 -0.8220 0.06024 0.05088 -0.0379 1.0000 0.0786
-10.500 -0.8160 0.05788 0.04845 -0.0363 1.0000 0.0799
-10.250 -0.8141 0.05536 0.04575 -0.0342 1.0000 0.0810
-10.000 -0.8114 0.05294 0.04310 -0.0319 1.0000 0.0825
-9.750 -0.8084 0.05057 0.04045 -0.0295 1.0000 0.0842
-9.500 -0.8045 0.04825 0.03777 -0.0268 1.0000 0.0860
-9.250 -0.7987 0.04602 0.03512 -0.0242 1.0000 0.0875
-9.000 -0.7840 0.04402 0.03302 -0.0226 1.0000 0.0892
-8.750 -0.7677 0.04240 0.03137 -0.0212 1.0000 0.0914
-8.500 -0.7519 0.04084 0.02968 -0.0195 1.0000 0.0939
-8.250 -0.7356 0.03926 0.02789 -0.0178 1.0000 0.0963
-8.000 -0.7184 0.03779 0.02615 -0.0160 1.0000 0.0986
-7.750 -0.6983 0.03638 0.02473 -0.0149 1.0000 0.1013
-7.500 -0.6783 0.03519 0.02356 -0.0136 1.0000 0.1044
-7.250 -0.6578 0.03407 0.02237 -0.0123 1.0000 0.1075
-7.000 -0.6374 0.03307 0.02123 -0.0108 1.0000 0.1109
-6.750 -0.6174 0.03206 0.02027 -0.0095 1.0000 0.1146
-6.500 -0.5992 0.03116 0.01942 -0.0078 1.0000 0.1186
-6.250 -0.5815 0.03037 0.01858 -0.0060 1.0000 0.1229
-6.000 -0.5651 0.02962 0.01780 -0.0041 1.0000 0.1277
-5.750 -0.5512 0.02882 0.01708 -0.0019 1.0000 0.1333
-5.500 -0.5369 0.02815 0.01636 0.0002 1.0000 0.1400
-5.250 -0.5240 0.02737 0.01566 0.0025 1.0000 0.1473
-5.000 -0.5108 0.02668 0.01501 0.0046 1.0000 0.1585
-4.750 -0.4983 0.02584 0.01434 0.0066 1.0000 0.1751
-4.500 -0.4865 0.02478 0.01369 0.0086 1.0000 0.2113
-4.250 -0.4775 0.02354 0.01334 0.0109 1.0000 0.3329
-4.000 -0.4551 0.02295 0.01333 0.0115 0.9946 0.4589
-3.750 -0.4186 0.02276 0.01345 0.0101 0.9834 0.5459
-3.500 -0.3824 0.02279 0.01371 0.0091 0.9716 0.6135
-3.250 -0.3471 0.02299 0.01410 0.0088 0.9594 0.6753
-3.000 -0.3123 0.02345 0.01472 0.0094 0.9471 0.7355
-2.750 -0.2700 0.02393 0.01520 0.0084 0.9360 0.7748
-2.500 -0.2233 0.02409 0.01526 0.0056 0.9241 0.7956
-2.250 -0.1793 0.02412 0.01517 0.0030 0.9104 0.8134
-2.000 -0.1339 0.02413 0.01506 0.0002 0.8969 0.8307
-1.750 -0.0821 0.02413 0.01494 -0.0035 0.8841 0.8452
-1.500 -0.0330 0.02407 0.01478 -0.0067 0.8693 0.8592
-1.250 0.0115 0.02398 0.01459 -0.0092 0.8522 0.8737
-1.000 0.0546 0.02385 0.01436 -0.0114 0.8341 0.8883
-0.750 0.1002 0.02370 0.01410 -0.0141 0.8150 0.9013
-0.500 0.1492 0.02349 0.01377 -0.0173 0.7940 0.9123
-0.250 0.1894 0.02332 0.01349 -0.0191 0.7688 0.9255
0.000 0.2282 0.02314 0.01317 -0.0206 0.7431 0.9390
0.250 0.2725 0.02293 0.01280 -0.0231 0.7161 0.9498
0.500 0.3123 0.02280 0.01254 -0.0252 0.6877 0.9617
0.750 0.3521 0.02268 0.01224 -0.0273 0.6605 0.9735
1.000 0.3921 0.02260 0.01203 -0.0297 0.6313 0.9850
1.250 0.4331 0.02251 0.01177 -0.0323 0.6034 0.9957
1.500 0.4607 0.02252 0.01165 -0.0327 0.5771 1.0000
1.750 0.4787 0.02259 0.01157 -0.0311 0.5544 1.0000
2.000 0.4972 0.02270 0.01153 -0.0296 0.5330 1.0000
2.250 0.5158 0.02286 0.01155 -0.0282 0.5123 1.0000
2.500 0.5341 0.02308 0.01165 -0.0267 0.4916 1.0000
2.750 0.5525 0.02332 0.01179 -0.0252 0.4723 1.0000
3.000 0.5711 0.02361 0.01196 -0.0238 0.4545 1.0000
3.250 0.5899 0.02393 0.01216 -0.0223 0.4379 1.0000
3.500 0.6084 0.02428 0.01244 -0.0208 0.4219 1.0000
3.750 0.6270 0.02467 0.01278 -0.0194 0.4069 1.0000
4.000 0.6459 0.02510 0.01314 -0.0180 0.3935 1.0000
4.250 0.6652 0.02553 0.01347 -0.0166 0.3817 1.0000
4.500 0.6841 0.02601 0.01392 -0.0152 0.3698 1.0000
4.750 0.7032 0.02653 0.01441 -0.0138 0.3593 1.0000
5.000 0.7230 0.02704 0.01486 -0.0125 0.3500 1.0000
5.250 0.7419 0.02764 0.01549 -0.0112 0.3405 1.0000
5.500 0.7619 0.02820 0.01598 -0.0099 0.3323 1.0000
5.750 0.7807 0.02887 0.01670 -0.0086 0.3241 1.0000
6.000 0.8002 0.02952 0.01736 -0.0073 0.3166 1.0000
6.250 0.8204 0.03019 0.01799 -0.0062 0.3100 1.0000
6.500 0.8378 0.03098 0.01892 -0.0047 0.3025 1.0000
6.750 0.8583 0.03164 0.01953 -0.0036 0.2963 1.0000
7.000 0.8758 0.03253 0.02053 -0.0022 0.2900 1.0000
7.250 0.8932 0.03341 0.02150 -0.0008 0.2835 1.0000
7.500 0.9149 0.03408 0.02211 0.0001 0.2780 1.0000
7.750 0.9287 0.03520 0.02343 0.0018 0.2716 1.0000
8.000 0.9454 0.03616 0.02449 0.0032 0.2655 1.0000
8.250 0.9682 0.03681 0.02506 0.0039 0.2603 1.0000
8.500 0.9771 0.03823 0.02676 0.0060 0.2540 1.0000
8.750 0.9926 0.03925 0.02787 0.0074 0.2480 1.0000
9.000 1.0156 0.03990 0.02844 0.0080 0.2429 1.0000
9.250 1.0182 0.04167 0.03056 0.0106 0.2367 1.0000
9.500 1.0318 0.04277 0.03175 0.0121 0.2309 1.0000
9.750 1.0535 0.04348 0.03238 0.0128 0.2258 1.0000
10.000 1.0481 0.04570 0.03497 0.0158 0.2201 1.0000
10.250 1.0574 0.04699 0.03637 0.0175 0.2145 1.0000
10.500 1.0802 0.04756 0.03684 0.0181 0.2094 1.0000
10.750 1.0597 0.05060 0.04027 0.0218 0.2046 1.0000
11.000 1.0501 0.05284 0.04268 0.0246 0.2000 1.0000
11.250 1.0811 0.05273 0.04246 0.0248 0.1946 1.0000
11.500 1.0492 0.05674 0.04673 0.0279 0.1913 1.0000
11.750 0.9886 0.06441 0.05473 0.0285 0.1884 1.0000
12.000 0.8454 0.08771 0.07826 0.0177 0.1827 1.0000
12.250 0.9133 0.07976 0.07032 0.0235 0.1799 1.0000
12.500 0.7734 0.10859 0.09917 0.0080 0.1683 1.0000
12.750 0.7940 0.10842 0.09904 0.0092 0.1650 1.0000
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Polar data table (+)
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