NACA 23015 (naca23015-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 23015 (naca23015-il) Reynolds number: 200,000 Max Cl/Cd: 48.38 at α=9.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca23015-il-200000.txt Download as CSV file: xf-naca23015-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.250 -0.7990 0.07899 0.07467 -0.0453 0.9999 0.0567
-13.000 -0.8153 0.07362 0.06921 -0.0469 0.9999 0.0565
-12.750 -0.8369 0.06855 0.06400 -0.0478 0.9999 0.0562
-12.500 -0.8612 0.06401 0.05930 -0.0474 0.9999 0.0560
-12.250 -0.8871 0.06013 0.05523 -0.0453 0.9999 0.0558
-12.000 -0.9120 0.05671 0.05157 -0.0417 0.9999 0.0557
-11.750 -0.9322 0.05293 0.04747 -0.0383 0.9999 0.0558
-11.500 -0.9484 0.04925 0.04334 -0.0348 0.9999 0.0563
-11.250 -0.9593 0.04594 0.03948 -0.0312 0.9999 0.0571
-11.000 -0.9305 0.04467 0.03854 -0.0319 0.9999 0.0587
-10.750 -0.9169 0.04314 0.03693 -0.0306 0.9999 0.0601
-10.500 -0.9086 0.04078 0.03429 -0.0286 0.9999 0.0614
-10.250 -0.8998 0.03838 0.03150 -0.0264 0.9999 0.0628
-10.000 -0.8911 0.03674 0.02931 -0.0239 0.9999 0.0643
-9.750 -0.8710 0.03421 0.02683 -0.0234 0.9999 0.0659
-9.500 -0.8493 0.03304 0.02568 -0.0227 0.9999 0.0676
-9.250 -0.8299 0.03173 0.02421 -0.0216 0.9999 0.0694
-9.000 -0.8110 0.03045 0.02267 -0.0202 0.9999 0.0714
-8.750 -0.7922 0.02932 0.02123 -0.0186 0.9999 0.0729
-8.500 -0.7699 0.02750 0.01948 -0.0180 0.9999 0.0748
-8.250 -0.7482 0.02658 0.01857 -0.0171 0.9999 0.0768
-8.000 -0.7271 0.02567 0.01759 -0.0159 0.9999 0.0787
-7.750 -0.7066 0.02485 0.01663 -0.0145 0.9999 0.0806
-7.500 -0.6866 0.02424 0.01586 -0.0130 0.9999 0.0822
-7.250 -0.6658 0.02284 0.01457 -0.0120 0.9999 0.0842
-7.000 -0.6461 0.02211 0.01388 -0.0106 0.9999 0.0860
-6.750 -0.6272 0.02153 0.01329 -0.0090 0.9999 0.0882
-6.500 -0.6089 0.02102 0.01275 -0.0074 0.9999 0.0904
-6.250 -0.5911 0.02062 0.01229 -0.0056 0.9999 0.0922
-6.000 -0.5741 0.01983 0.01157 -0.0039 0.9999 0.0943
-5.750 -0.5578 0.01935 0.01117 -0.0022 0.9999 0.0968
-5.500 -0.5414 0.01903 0.01089 -0.0005 0.9999 0.0996
-5.250 -0.5248 0.01878 0.01064 0.0012 0.9999 0.1024
-5.000 -0.4929 0.01814 0.01004 0.0002 0.9969 0.1062
-4.750 -0.4524 0.01749 0.00947 -0.0024 0.9927 0.1126
-4.500 -0.4131 0.01681 0.00883 -0.0046 0.9866 0.1203
-4.250 -0.3713 0.01616 0.00826 -0.0073 0.9821 0.1333
-4.000 -0.3349 0.01507 0.00753 -0.0092 0.9748 0.1821
-3.750 -0.3034 0.01310 0.00705 -0.0108 0.9702 0.4880
-3.500 -0.2657 0.01261 0.00686 -0.0124 0.9626 0.5657
-3.250 -0.2261 0.01225 0.00667 -0.0141 0.9559 0.6180
-3.000 -0.1924 0.01199 0.00654 -0.0147 0.9447 0.6577
-2.750 -0.1591 0.01177 0.00641 -0.0150 0.9337 0.6927
-2.500 -0.1294 0.01160 0.00634 -0.0145 0.9206 0.7272
-2.250 -0.1047 0.01148 0.00631 -0.0129 0.9028 0.7583
-2.000 -0.0811 0.01139 0.00622 -0.0110 0.8831 0.7855
-1.750 -0.0586 0.01133 0.00618 -0.0089 0.8630 0.8091
-1.500 -0.0362 0.01133 0.00617 -0.0068 0.8434 0.8328
-1.250 -0.0138 0.01137 0.00618 -0.0048 0.8235 0.8563
-1.000 0.0087 0.01143 0.00619 -0.0028 0.8031 0.8784
-0.750 0.0326 0.01151 0.00621 -0.0011 0.7821 0.8970
-0.500 0.0593 0.01161 0.00622 0.0000 0.7607 0.9122
-0.250 0.0881 0.01173 0.00623 0.0005 0.7385 0.9262
0.000 0.1187 0.01187 0.00624 0.0006 0.7157 0.9397
0.250 0.1547 0.01208 0.00631 -0.0004 0.6923 0.9496
0.500 0.1929 0.01230 0.00640 -0.0020 0.6664 0.9580
0.750 0.2336 0.01255 0.00650 -0.0042 0.6393 0.9651
1.000 0.2749 0.01280 0.00659 -0.0065 0.6119 0.9714
1.250 0.3166 0.01306 0.00669 -0.0090 0.5837 0.9774
1.500 0.3571 0.01332 0.00679 -0.0113 0.5555 0.9838
1.750 0.3985 0.01357 0.00688 -0.0140 0.5258 0.9896
2.000 0.4395 0.01384 0.00699 -0.0165 0.4966 0.9951
2.250 0.4802 0.01411 0.00709 -0.0191 0.4683 1.0001
2.500 0.5005 0.01412 0.00695 -0.0182 0.4462 1.0001
2.750 0.5209 0.01414 0.00686 -0.0173 0.4244 1.0001
3.000 0.5410 0.01422 0.00681 -0.0162 0.4042 1.0001
3.250 0.5608 0.01434 0.00681 -0.0151 0.3863 1.0001
3.500 0.5807 0.01452 0.00686 -0.0139 0.3709 1.0001
3.750 0.6006 0.01470 0.00694 -0.0127 0.3570 1.0001
4.000 0.6209 0.01488 0.00707 -0.0115 0.3443 1.0001
4.250 0.6411 0.01514 0.00722 -0.0104 0.3336 1.0001
4.500 0.6619 0.01536 0.00739 -0.0092 0.3236 1.0001
4.750 0.6831 0.01567 0.00762 -0.0082 0.3153 1.0001
5.000 0.7047 0.01592 0.00785 -0.0072 0.3072 1.0001
5.250 0.7266 0.01631 0.00813 -0.0062 0.3001 1.0001
5.500 0.7490 0.01656 0.00842 -0.0053 0.2928 1.0001
5.750 0.7716 0.01691 0.00870 -0.0045 0.2866 1.0001
6.000 0.7948 0.01731 0.00908 -0.0038 0.2805 1.0001
6.250 0.8182 0.01762 0.00942 -0.0031 0.2741 1.0001
6.500 0.8420 0.01804 0.00976 -0.0025 0.2685 1.0001
6.750 0.8658 0.01846 0.01021 -0.0019 0.2628 1.0001
7.000 0.8898 0.01881 0.01060 -0.0014 0.2570 1.0001
7.250 0.9140 0.01925 0.01098 -0.0009 0.2518 1.0001
7.500 0.9379 0.01975 0.01152 -0.0004 0.2465 1.0001
7.750 0.9616 0.02010 0.01194 0.0001 0.2408 1.0001
8.000 0.9855 0.02052 0.01231 0.0006 0.2355 1.0001
8.250 1.0092 0.02109 0.01290 0.0011 0.2302 1.0001
8.500 1.0320 0.02144 0.01336 0.0017 0.2246 1.0001
8.750 1.0553 0.02184 0.01374 0.0022 0.2192 1.0001
9.000 1.0782 0.02245 0.01436 0.0027 0.2140 1.0001
9.250 1.0997 0.02280 0.01484 0.0036 0.2082 1.0001
9.500 1.1219 0.02319 0.01521 0.0042 0.2029 1.0001
9.750 1.1434 0.02379 0.01584 0.0049 0.1975 1.0001
10.000 1.1632 0.02415 0.01633 0.0059 0.1916 1.0001
10.250 1.1839 0.02456 0.01671 0.0067 0.1864 1.0001
10.500 1.2026 0.02514 0.01740 0.0078 0.1807 1.0001
10.750 1.2205 0.02553 0.01787 0.0090 0.1748 1.0001
11.000 1.2397 0.02614 0.01837 0.0099 0.1694 1.0001
11.250 1.2532 0.02661 0.01909 0.0117 0.1634 1.0001
11.500 1.2678 0.02708 0.01956 0.0133 0.1579 1.0001
11.750 1.2804 0.02781 0.02036 0.0150 0.1523 1.0001
12.000 1.2906 0.02843 0.02107 0.0171 0.1466 1.0001
12.250 1.3004 0.02923 0.02180 0.0192 0.1418 1.0001
12.500 1.3030 0.03013 0.02290 0.0222 0.1367 1.0001
12.750 1.3083 0.03105 0.02384 0.0245 0.1322 1.0001
13.000 1.3137 0.03227 0.02510 0.0264 0.1276 1.0001
13.250 1.3177 0.03354 0.02650 0.0283 0.1230 1.0001
13.500 1.3230 0.03487 0.02780 0.0298 0.1192 1.0001
13.750 1.3268 0.03653 0.02957 0.0312 0.1153 1.0001
14.000 1.3298 0.03824 0.03139 0.0324 0.1117 1.0001
14.250 1.3340 0.03994 0.03309 0.0334 0.1086 1.0001
14.500 1.3381 0.04187 0.03505 0.0343 0.1056 1.0001
14.750 1.3376 0.04418 0.03754 0.0349 0.1028 1.0001
15.000 1.3394 0.04635 0.03978 0.0353 0.1002 1.0001
15.250 1.3438 0.04834 0.04175 0.0357 0.0979 1.0001
15.500 1.3470 0.05061 0.04407 0.0362 0.0957 1.0001
15.750 1.3422 0.05370 0.04737 0.0360 0.0939 1.0001
16.000 1.3394 0.05668 0.05049 0.0358 0.0921 1.0001
16.250 1.3388 0.05945 0.05334 0.0355 0.0903 1.0001
16.500 1.3433 0.06162 0.05550 0.0355 0.0885 1.0001
16.750 1.3513 0.06350 0.05735 0.0360 0.0867 1.0001
17.000 1.3371 0.06810 0.06220 0.0345 0.0857 1.0001
17.250 1.3232 0.07293 0.06725 0.0328 0.0846 1.0001
17.500 1.3097 0.07788 0.07239 0.0309 0.0836 1.0001
17.750 1.2971 0.08287 0.07755 0.0289 0.0825 1.0001
18.000 1.2878 0.08750 0.08230 0.0269 0.0814 1.0001
18.250 1.2877 0.09068 0.08552 0.0258 0.0801 1.0001
18.500 1.3084 0.09047 0.08519 0.0273 0.0784 1.0001
18.750 1.2814 0.09805 0.09300 0.0233 0.0778 1.0001
19.000 1.2403 0.10857 0.10382 0.0170 0.0775 1.0001
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