AIRFOIL 3024 9.84% (s3024-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: AIRFOIL 3024 9.84% (s3024-il) Reynolds number: 1,000,000 Max Cl/Cd: 110.07 at α=3.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s3024-il-1000000-n5.txt Download as CSV file: xf-s3024-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: AIRFOIL 3024 9.84%
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.3470 0.09825 0.09656 -0.0405 0.9687 0.0049
-10.000 -0.3368 0.09226 0.09054 -0.0460 0.9579 0.0049
-9.750 -0.3270 0.08784 0.08608 -0.0502 0.9438 0.0049
-9.500 -0.3290 0.08219 0.08038 -0.0531 0.9273 0.0051
-9.250 -0.3319 0.07793 0.07608 -0.0550 0.9134 0.0050
-8.750 -0.2914 0.05902 0.05714 -0.0497 0.8600 0.0055
-8.250 -0.4699 0.02910 0.02629 -0.0788 0.8528 0.0050
-8.000 -0.4597 0.02514 0.02188 -0.0787 0.8466 0.0051
-7.750 -0.4487 0.02113 0.01733 -0.0781 0.8413 0.0051
-7.500 -0.4302 0.01875 0.01459 -0.0776 0.8362 0.0052
-7.250 -0.4085 0.01716 0.01273 -0.0772 0.8310 0.0053
-7.000 -0.3850 0.01600 0.01136 -0.0768 0.8264 0.0054
-6.750 -0.3601 0.01514 0.01037 -0.0766 0.8215 0.0055
-6.500 -0.3347 0.01441 0.00949 -0.0764 0.8163 0.0056
-6.250 -0.3088 0.01385 0.00882 -0.0762 0.8116 0.0058
-6.000 -0.2826 0.01322 0.00809 -0.0760 0.8067 0.0059
-5.750 -0.2566 0.01253 0.00726 -0.0758 0.8015 0.0060
-5.500 -0.2305 0.01189 0.00649 -0.0755 0.7968 0.0061
-5.250 -0.2039 0.01129 0.00579 -0.0753 0.7918 0.0063
-5.000 -0.1773 0.01078 0.00518 -0.0751 0.7866 0.0065
-4.750 -0.1505 0.01033 0.00464 -0.0749 0.7818 0.0067
-4.500 -0.1232 0.00994 0.00418 -0.0748 0.7766 0.0069
-4.250 -0.0959 0.00961 0.00379 -0.0747 0.7710 0.0072
-4.000 -0.0684 0.00935 0.00346 -0.0746 0.7658 0.0074
-3.750 -0.0411 0.00899 0.00304 -0.0745 0.7600 0.0076
-3.500 -0.0139 0.00865 0.00264 -0.0743 0.7540 0.0081
-3.250 0.0139 0.00842 0.00237 -0.0743 0.7481 0.0085
-3.000 0.0416 0.00823 0.00214 -0.0742 0.7414 0.0088
-2.750 0.0695 0.00808 0.00195 -0.0742 0.7350 0.0096
-2.500 0.0974 0.00794 0.00176 -0.0742 0.7276 0.0102
-2.250 0.1253 0.00779 0.00157 -0.0741 0.7205 0.0110
-2.000 0.1532 0.00767 0.00141 -0.0741 0.7124 0.0127
-1.750 0.1811 0.00755 0.00128 -0.0740 0.7046 0.0173
-1.500 0.2085 0.00734 0.00116 -0.0740 0.6954 0.0497
-1.250 0.2359 0.00712 0.00108 -0.0740 0.6857 0.0936
-1.000 0.2633 0.00698 0.00101 -0.0739 0.6751 0.1332
-0.750 0.2905 0.00683 0.00096 -0.0739 0.6634 0.1849
-0.500 0.3177 0.00669 0.00093 -0.0738 0.6508 0.2379
-0.250 0.3446 0.00649 0.00092 -0.0738 0.6377 0.3176
0.000 0.3711 0.00626 0.00092 -0.0737 0.6241 0.4175
0.250 0.3977 0.00611 0.00093 -0.0735 0.6096 0.4962
0.500 0.4242 0.00600 0.00096 -0.0734 0.5946 0.5692
0.750 0.4500 0.00584 0.00100 -0.0730 0.5793 0.6599
1.000 0.4744 0.00565 0.00106 -0.0723 0.5633 0.7659
1.250 0.4967 0.00547 0.00114 -0.0710 0.5478 0.8722
1.500 0.5246 0.00547 0.00122 -0.0707 0.5311 0.9528
1.750 0.5609 0.00560 0.00128 -0.0727 0.5125 0.9780
2.000 0.5965 0.00575 0.00134 -0.0745 0.4931 0.9899
2.500 0.6606 0.00610 0.00149 -0.0766 0.4523 1.0000
2.750 0.6853 0.00628 0.00158 -0.0760 0.4327 1.0000
3.000 0.7099 0.00649 0.00169 -0.0754 0.4128 1.0000
3.250 0.7348 0.00669 0.00181 -0.0749 0.3926 1.0000
3.500 0.7595 0.00690 0.00193 -0.0744 0.3725 1.0000
3.750 0.7842 0.00714 0.00208 -0.0739 0.3512 1.0000
4.000 0.8091 0.00737 0.00222 -0.0734 0.3320 1.0000
4.250 0.8339 0.00761 0.00238 -0.0729 0.3127 1.0000
4.500 0.8586 0.00786 0.00255 -0.0725 0.2936 1.0000
4.750 0.8830 0.00815 0.00274 -0.0720 0.2716 1.0000
5.000 0.9068 0.00849 0.00296 -0.0714 0.2459 1.0000
5.250 0.9308 0.00880 0.00317 -0.0708 0.2251 1.0000
5.500 0.9547 0.00913 0.00341 -0.0703 0.2036 1.0000
5.750 0.9775 0.00955 0.00369 -0.0696 0.1761 1.0000
6.000 0.9997 0.01001 0.00400 -0.0688 0.1476 1.0000
6.250 1.0220 0.01046 0.00432 -0.0680 0.1241 1.0000
6.500 1.0448 0.01085 0.00463 -0.0673 0.1063 1.0000
6.750 1.0667 0.01131 0.00498 -0.0665 0.0873 1.0000
7.000 1.0883 0.01180 0.00536 -0.0657 0.0680 1.0000
7.250 1.1080 0.01241 0.00584 -0.0645 0.0458 1.0000
7.500 1.1271 0.01306 0.00637 -0.0633 0.0258 1.0000
7.750 1.1449 0.01380 0.00700 -0.0618 0.0091 1.0000
8.000 1.1664 0.01421 0.00742 -0.0609 0.0078 1.0000
8.250 1.1877 0.01460 0.00785 -0.0600 0.0071 1.0000
8.500 1.2088 0.01499 0.00828 -0.0591 0.0068 1.0000
8.750 1.2292 0.01541 0.00873 -0.0581 0.0065 1.0000
9.000 1.2489 0.01585 0.00921 -0.0569 0.0062 1.0000
9.250 1.2676 0.01631 0.00972 -0.0556 0.0060 1.0000
9.500 1.2838 0.01680 0.01025 -0.0539 0.0058 1.0000
9.750 1.2986 0.01733 0.01083 -0.0519 0.0056 1.0000
10.000 1.3124 0.01793 0.01148 -0.0499 0.0054 1.0000
10.250 1.3251 0.01863 0.01224 -0.0478 0.0051 1.0000
10.500 1.3362 0.01944 0.01312 -0.0456 0.0049 1.0000
10.750 1.3476 0.02027 0.01402 -0.0436 0.0048 1.0000
11.000 1.3620 0.02091 0.01471 -0.0420 0.0047 1.0000
11.250 1.3741 0.02172 0.01559 -0.0403 0.0046 1.0000
11.500 1.3858 0.02258 0.01652 -0.0385 0.0045 1.0000
11.750 1.3965 0.02353 0.01754 -0.0368 0.0045 1.0000
12.000 1.4062 0.02459 0.01867 -0.0351 0.0044 1.0000
12.250 1.4160 0.02566 0.01981 -0.0335 0.0043 1.0000
12.500 1.4228 0.02700 0.02124 -0.0318 0.0042 1.0000
12.750 1.4295 0.02838 0.02272 -0.0302 0.0042 1.0000
13.000 1.4363 0.02981 0.02423 -0.0287 0.0041 1.0000
13.250 1.4409 0.03147 0.02598 -0.0273 0.0040 1.0000
13.500 1.4459 0.03317 0.02776 -0.0260 0.0039 1.0000
13.750 1.4495 0.03505 0.02973 -0.0249 0.0039 1.0000
14.000 1.4528 0.03704 0.03181 -0.0239 0.0038 1.0000
14.250 1.4548 0.03922 0.03409 -0.0231 0.0037 1.0000
14.500 1.4540 0.04180 0.03677 -0.0224 0.0038 1.0000
14.750 1.4526 0.04456 0.03964 -0.0219 0.0037 1.0000
15.000 1.4508 0.04751 0.04269 -0.0217 0.0037 1.0000
15.250 1.4496 0.05054 0.04582 -0.0218 0.0036 1.0000
15.500 1.4494 0.05358 0.04896 -0.0220 0.0035 1.0000
15.750 1.4411 0.05784 0.05335 -0.0227 0.0036 1.0000
16.000 1.4379 0.06160 0.05721 -0.0236 0.0035 1.0000
16.250 1.4320 0.06591 0.06163 -0.0248 0.0035 1.0000
16.500 1.4235 0.07079 0.06664 -0.0264 0.0035 1.0000
16.750 1.4146 0.07589 0.07185 -0.0283 0.0034 1.0000
17.000 1.4043 0.08144 0.07753 -0.0305 0.0034 1.0000
17.250 1.3931 0.08732 0.08352 -0.0330 0.0033 1.0000
17.500 1.3817 0.09340 0.08972 -0.0358 0.0034 1.0000
17.750 1.3667 0.10030 0.09675 -0.0390 0.0033 1.0000
18.000 1.3548 0.10682 0.10339 -0.0422 0.0033 1.0000
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Polar data table (+)
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