NACA 23015 (naca23015-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 23015 (naca23015-il) Reynolds number: 200,000 Max Cl/Cd: 52.62 at α=8.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca23015-il-200000-n5.txt Download as CSV file: xf-naca23015-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.500 -0.9350 0.07554 0.07059 -0.0413 1.0000 0.0300
-15.250 -0.9674 0.06721 0.06199 -0.0462 1.0000 0.0302
-15.000 -0.9904 0.06092 0.05543 -0.0493 1.0000 0.0305
-14.750 -1.0102 0.05555 0.04977 -0.0513 1.0000 0.0310
-14.500 -1.0292 0.05067 0.04453 -0.0523 1.0000 0.0316
-14.250 -1.0357 0.04753 0.04119 -0.0522 1.0000 0.0321
-14.000 -1.0307 0.04587 0.03949 -0.0518 1.0000 0.0324
-13.750 -1.0265 0.04423 0.03779 -0.0512 1.0000 0.0328
-13.500 -1.0228 0.04259 0.03606 -0.0502 1.0000 0.0333
-13.250 -1.0197 0.04091 0.03426 -0.0490 1.0000 0.0339
-13.000 -1.0171 0.03919 0.03236 -0.0474 1.0000 0.0346
-12.750 -1.0155 0.03735 0.03027 -0.0453 1.0000 0.0356
-12.500 -1.0123 0.03568 0.02835 -0.0431 1.0000 0.0364
-12.250 -1.0021 0.03485 0.02753 -0.0412 1.0000 0.0370
-12.000 -0.9929 0.03408 0.02672 -0.0391 1.0000 0.0376
-11.750 -0.9837 0.03325 0.02581 -0.0367 1.0000 0.0383
-11.500 -0.9727 0.03228 0.02473 -0.0346 1.0000 0.0392
-11.250 -0.9612 0.03119 0.02344 -0.0325 1.0000 0.0404
-11.000 -0.9486 0.03014 0.02221 -0.0304 1.0000 0.0414
-10.750 -0.9333 0.02944 0.02154 -0.0287 1.0000 0.0421
-10.500 -0.9186 0.02879 0.02086 -0.0268 1.0000 0.0430
-10.250 -0.9040 0.02809 0.02010 -0.0248 1.0000 0.0440
-10.000 -0.8894 0.02736 0.01926 -0.0227 1.0000 0.0452
-9.750 -0.8749 0.02662 0.01835 -0.0205 1.0000 0.0464
-9.500 -0.8593 0.02586 0.01757 -0.0186 1.0000 0.0474
-9.250 -0.8438 0.02525 0.01698 -0.0166 1.0000 0.0483
-9.000 -0.8287 0.02468 0.01641 -0.0145 1.0000 0.0493
-8.750 -0.8135 0.02412 0.01580 -0.0123 1.0000 0.0505
-8.500 -0.7984 0.02356 0.01516 -0.0101 1.0000 0.0518
-8.250 -0.7831 0.02303 0.01453 -0.0079 1.0000 0.0529
-8.000 -0.7684 0.02238 0.01390 -0.0057 1.0000 0.0539
-7.750 -0.7383 0.02170 0.01326 -0.0066 0.9968 0.0553
-7.500 -0.7036 0.02106 0.01261 -0.0083 0.9930 0.0571
-7.250 -0.6705 0.02041 0.01192 -0.0096 0.9878 0.0587
-7.000 -0.6353 0.01982 0.01126 -0.0113 0.9834 0.0604
-6.750 -0.6036 0.01908 0.01059 -0.0125 0.9776 0.0622
-6.500 -0.5697 0.01850 0.01002 -0.0140 0.9721 0.0642
-6.250 -0.5360 0.01794 0.00945 -0.0154 0.9666 0.0662
-6.000 -0.5042 0.01747 0.00893 -0.0162 0.9590 0.0684
-5.750 -0.4734 0.01685 0.00836 -0.0170 0.9516 0.0709
-5.500 -0.4432 0.01638 0.00789 -0.0176 0.9426 0.0736
-5.250 -0.4135 0.01596 0.00744 -0.0179 0.9328 0.0765
-5.000 -0.3829 0.01548 0.00698 -0.0184 0.9233 0.0803
-4.750 -0.3556 0.01510 0.00660 -0.0182 0.9107 0.0851
-4.500 -0.3273 0.01470 0.00620 -0.0182 0.8984 0.0912
-4.250 -0.2989 0.01429 0.00582 -0.0181 0.8856 0.1018
-4.000 -0.2735 0.01380 0.00544 -0.0175 0.8703 0.1271
-3.750 -0.2537 0.01280 0.00495 -0.0163 0.8540 0.2315
-3.500 -0.2331 0.01205 0.00466 -0.0150 0.8373 0.3454
-3.250 -0.2099 0.01163 0.00447 -0.0139 0.8203 0.4109
-3.000 -0.1857 0.01134 0.00431 -0.0129 0.8032 0.4601
-2.750 -0.1610 0.01112 0.00418 -0.0119 0.7856 0.4999
-2.500 -0.1366 0.01093 0.00408 -0.0109 0.7675 0.5424
-2.250 -0.1124 0.01077 0.00400 -0.0097 0.7460 0.5840
-2.000 -0.0878 0.01068 0.00392 -0.0086 0.7219 0.6154
-1.750 -0.0628 0.01064 0.00384 -0.0076 0.6979 0.6437
-1.500 -0.0377 0.01059 0.00382 -0.0067 0.6756 0.6724
-1.250 -0.0124 0.01057 0.00381 -0.0057 0.6550 0.7015
-1.000 0.0132 0.01058 0.00381 -0.0049 0.6341 0.7270
-0.750 0.0392 0.01062 0.00381 -0.0041 0.6130 0.7486
-0.500 0.0654 0.01068 0.00381 -0.0034 0.5918 0.7667
-0.250 0.0918 0.01076 0.00382 -0.0028 0.5704 0.7835
0.000 0.1182 0.01086 0.00385 -0.0022 0.5494 0.7999
0.250 0.1448 0.01097 0.00389 -0.0016 0.5290 0.8161
0.500 0.1715 0.01110 0.00395 -0.0011 0.5085 0.8322
0.750 0.1984 0.01126 0.00403 -0.0006 0.4876 0.8473
1.000 0.2262 0.01143 0.00413 -0.0003 0.4671 0.8611
1.250 0.2542 0.01161 0.00423 -0.0001 0.4480 0.8743
1.500 0.2817 0.01180 0.00433 0.0002 0.4289 0.8876
1.750 0.3112 0.01203 0.00447 0.0001 0.4092 0.8989
2.000 0.3406 0.01226 0.00460 -0.0001 0.3898 0.9096
2.250 0.3683 0.01248 0.00473 0.0000 0.3720 0.9215
2.500 0.4014 0.01274 0.00491 -0.0010 0.3548 0.9290
2.750 0.4298 0.01297 0.00506 -0.0011 0.3395 0.9396
3.000 0.4642 0.01325 0.00525 -0.0024 0.3235 0.9459
3.250 0.4932 0.01352 0.00543 -0.0027 0.3095 0.9551
3.500 0.5290 0.01381 0.00563 -0.0045 0.2957 0.9600
3.750 0.5621 0.01406 0.00584 -0.0057 0.2844 0.9668
4.000 0.5971 0.01435 0.00606 -0.0073 0.2742 0.9717
4.250 0.6327 0.01462 0.00628 -0.0091 0.2642 0.9766
4.500 0.6657 0.01490 0.00652 -0.0104 0.2560 0.9824
4.750 0.7022 0.01517 0.00676 -0.0124 0.2481 0.9863
5.000 0.7365 0.01549 0.00703 -0.0141 0.2419 0.9911
5.250 0.7718 0.01575 0.00729 -0.0159 0.2355 0.9950
5.500 0.8069 0.01606 0.00757 -0.0177 0.2294 0.9989
5.750 0.8305 0.01636 0.00784 -0.0172 0.2249 1.0000
6.000 0.8498 0.01658 0.00809 -0.0157 0.2205 1.0000
6.250 0.8684 0.01684 0.00836 -0.0142 0.2160 1.0000
6.500 0.8862 0.01716 0.00864 -0.0125 0.2118 1.0000
6.750 0.9047 0.01746 0.00894 -0.0109 0.2079 1.0000
7.000 0.9239 0.01771 0.00925 -0.0094 0.2036 1.0000
7.250 0.9424 0.01801 0.00956 -0.0078 0.1995 1.0000
7.500 0.9601 0.01837 0.00989 -0.0061 0.1956 1.0000
7.750 0.9786 0.01871 0.01025 -0.0046 0.1917 1.0000
8.000 0.9978 0.01899 0.01060 -0.0031 0.1874 1.0000
8.250 1.0160 0.01931 0.01094 -0.0015 0.1830 1.0000
8.500 1.0331 0.01972 0.01131 0.0002 0.1791 1.0000
8.750 1.0521 0.02005 0.01172 0.0016 0.1750 1.0000
9.000 1.0709 0.02038 0.01212 0.0030 0.1705 1.0000
9.250 1.0885 0.02077 0.01252 0.0045 0.1662 1.0000
9.500 1.1060 0.02121 0.01297 0.0060 0.1621 1.0000
9.750 1.1249 0.02158 0.01343 0.0073 0.1573 1.0000
10.000 1.1418 0.02201 0.01390 0.0088 0.1528 1.0000
10.250 1.1575 0.02250 0.01441 0.0104 0.1486 1.0000
10.500 1.1744 0.02294 0.01494 0.0119 0.1437 1.0000
10.750 1.1878 0.02345 0.01549 0.0139 0.1390 1.0000
11.000 1.2009 0.02403 0.01611 0.0158 0.1347 1.0000
11.250 1.2155 0.02461 0.01678 0.0173 0.1296 1.0000
11.500 1.2271 0.02534 0.01752 0.0191 0.1250 1.0000
11.750 1.2405 0.02607 0.01834 0.0205 0.1202 1.0000
12.000 1.2520 0.02692 0.01924 0.0220 0.1152 1.0000
12.250 1.2620 0.02791 0.02027 0.0235 0.1106 1.0000
12.500 1.2725 0.02895 0.02138 0.0247 0.1057 1.0000
13.000 1.2883 0.03154 0.02409 0.0270 0.0974 1.0000
13.250 1.2942 0.03310 0.02571 0.0280 0.0937 1.0000
13.500 1.2979 0.03493 0.02759 0.0287 0.0907 1.0000
13.750 1.3032 0.03674 0.02951 0.0293 0.0875 1.0000
14.000 1.3054 0.03892 0.03176 0.0296 0.0846 1.0000
14.250 1.3042 0.04153 0.03442 0.0296 0.0823 1.0000
14.500 1.3057 0.04402 0.03702 0.0295 0.0799 1.0000
14.750 1.3050 0.04683 0.03995 0.0292 0.0777 1.0000
15.000 1.3015 0.05005 0.04326 0.0285 0.0758 1.0000
15.250 1.2953 0.05371 0.04699 0.0276 0.0742 1.0000
15.500 1.2887 0.05750 0.05087 0.0265 0.0728 1.0000
15.750 1.2839 0.06122 0.05474 0.0253 0.0712 1.0000
16.000 1.2770 0.06532 0.05896 0.0239 0.0698 1.0000
16.250 1.2684 0.06973 0.06348 0.0223 0.0686 1.0000
16.500 1.2587 0.07441 0.06825 0.0205 0.0674 1.0000
16.750 1.2485 0.07920 0.07311 0.0185 0.0663 1.0000
17.000 1.2392 0.08386 0.07781 0.0167 0.0653 1.0000
17.250 1.2299 0.08877 0.08288 0.0146 0.0642 1.0000
17.500 1.2202 0.09380 0.08804 0.0124 0.0631 1.0000
17.750 1.2103 0.09890 0.09326 0.0102 0.0620 1.0000
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