AIRFOIL 3024 9.84% (s3024-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: AIRFOIL 3024 9.84% (s3024-il) Reynolds number: 500,000 Max Cl/Cd: 96.8 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s3024-il-500000-n5.txt Download as CSV file: xf-s3024-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 -0.3658 0.11467 0.11231 -0.0316 1.0000 0.0104
-10.750 -0.3615 0.11090 0.10855 -0.0331 1.0000 0.0104
-10.500 -0.3599 0.10673 0.10441 -0.0346 1.0000 0.0105
-10.250 -0.3531 0.10370 0.10139 -0.0360 1.0000 0.0104
-9.750 -0.3466 0.09643 0.09417 -0.0388 1.0000 0.0104
-9.250 -0.3256 0.08970 0.08745 -0.0442 0.9753 0.0095
-9.000 -0.3140 0.08455 0.08228 -0.0495 0.9644 0.0089
-8.750 -0.3045 0.07927 0.07698 -0.0549 0.9516 0.0089
-8.500 -0.3057 0.07315 0.07084 -0.0595 0.9349 0.0082
-8.250 -0.3075 0.06924 0.06690 -0.0617 0.9199 0.0083
-8.000 -0.3250 0.06362 0.06126 -0.0648 0.9033 0.0080
-7.500 -0.3618 0.03764 0.03475 -0.0801 0.8772 0.0073
-7.250 -0.3634 0.02970 0.02613 -0.0811 0.8698 0.0074
-7.000 -0.3526 0.02525 0.02109 -0.0809 0.8632 0.0076
-6.750 -0.3350 0.02283 0.01833 -0.0805 0.8583 0.0078
-6.500 -0.3138 0.02099 0.01621 -0.0801 0.8531 0.0080
-6.250 -0.2916 0.01924 0.01414 -0.0797 0.8478 0.0081
-6.000 -0.2686 0.01766 0.01223 -0.0791 0.8432 0.0081
-5.750 -0.2441 0.01639 0.01073 -0.0787 0.8381 0.0082
-5.500 -0.2190 0.01533 0.00945 -0.0783 0.8329 0.0083
-5.250 -0.1936 0.01444 0.00837 -0.0779 0.8283 0.0085
-5.000 -0.1677 0.01365 0.00745 -0.0775 0.8233 0.0087
-4.750 -0.1415 0.01296 0.00664 -0.0772 0.8180 0.0090
-4.500 -0.1153 0.01236 0.00592 -0.0769 0.8133 0.0093
-4.250 -0.0887 0.01183 0.00530 -0.0766 0.8082 0.0097
-4.000 -0.0620 0.01137 0.00476 -0.0764 0.8028 0.0101
-3.750 -0.0352 0.01099 0.00429 -0.0761 0.7980 0.0104
-3.500 -0.0085 0.01049 0.00374 -0.0760 0.7925 0.0111
-3.250 0.0187 0.01019 0.00339 -0.0758 0.7869 0.0122
-3.000 0.0459 0.00992 0.00305 -0.0756 0.7817 0.0128
-2.750 0.0736 0.00967 0.00275 -0.0755 0.7755 0.0136
-2.500 0.1010 0.00945 0.00245 -0.0753 0.7696 0.0150
-2.250 0.1286 0.00924 0.00222 -0.0752 0.7634 0.0179
-2.000 0.1557 0.00894 0.00202 -0.0751 0.7567 0.0427
-1.750 0.1827 0.00863 0.00187 -0.0750 0.7502 0.0916
-1.500 0.2098 0.00838 0.00176 -0.0749 0.7427 0.1395
-1.250 0.2369 0.00816 0.00166 -0.0749 0.7357 0.1920
-1.000 0.2635 0.00784 0.00160 -0.0748 0.7275 0.2798
-0.750 0.2900 0.00755 0.00155 -0.0746 0.7193 0.3692
-0.500 0.3157 0.00721 0.00151 -0.0744 0.7102 0.4828
-0.250 0.3410 0.00688 0.00150 -0.0739 0.7004 0.5949
0.000 0.3655 0.00660 0.00150 -0.0732 0.6901 0.6995
0.250 0.3876 0.00629 0.00152 -0.0717 0.6794 0.8208
0.500 0.4188 0.00614 0.00157 -0.0718 0.6675 0.9342
0.750 0.4598 0.00618 0.00155 -0.0746 0.6543 0.9745
1.000 0.4991 0.00625 0.00152 -0.0771 0.6401 0.9909
1.250 0.5353 0.00634 0.00152 -0.0790 0.6251 1.0000
1.500 0.5604 0.00645 0.00154 -0.0784 0.6100 1.0000
1.750 0.5852 0.00658 0.00158 -0.0778 0.5938 1.0000
2.000 0.6100 0.00673 0.00164 -0.0772 0.5768 1.0000
2.250 0.6348 0.00688 0.00171 -0.0766 0.5597 1.0000
2.500 0.6597 0.00705 0.00179 -0.0760 0.5417 1.0000
2.750 0.6844 0.00723 0.00188 -0.0754 0.5228 1.0000
3.000 0.7091 0.00743 0.00200 -0.0749 0.5039 1.0000
3.250 0.7338 0.00763 0.00212 -0.0743 0.4845 1.0000
3.500 0.7584 0.00785 0.00226 -0.0738 0.4637 1.0000
4.000 0.8073 0.00834 0.00258 -0.0726 0.4213 1.0000
4.500 0.8555 0.00890 0.00295 -0.0715 0.3769 1.0000
4.750 0.8793 0.00920 0.00318 -0.0709 0.3556 1.0000
5.000 0.9032 0.00950 0.00340 -0.0703 0.3340 1.0000
5.250 0.9268 0.00983 0.00364 -0.0696 0.3128 1.0000
5.500 0.9502 0.01017 0.00391 -0.0690 0.2914 1.0000
5.750 0.9727 0.01058 0.00420 -0.0682 0.2660 1.0000
6.000 0.9948 0.01102 0.00452 -0.0674 0.2393 1.0000
6.250 1.0174 0.01141 0.00483 -0.0667 0.2174 1.0000
6.500 1.0383 0.01194 0.00521 -0.0658 0.1877 1.0000
6.750 1.0584 0.01251 0.00562 -0.0647 0.1573 1.0000
7.000 1.0791 0.01302 0.00603 -0.0638 0.1350 1.0000
7.250 1.0996 0.01355 0.00646 -0.0628 0.1152 1.0000
7.500 1.1200 0.01405 0.00690 -0.0618 0.0988 1.0000
7.750 1.1383 0.01470 0.00743 -0.0605 0.0768 1.0000
8.000 1.1566 0.01533 0.00797 -0.0592 0.0588 1.0000
8.250 1.1738 0.01601 0.00856 -0.0577 0.0428 1.0000
8.500 1.1867 0.01696 0.00937 -0.0557 0.0202 1.0000
8.750 1.2000 0.01777 0.01013 -0.0536 0.0114 1.0000
9.000 1.2143 0.01841 0.01080 -0.0516 0.0097 1.0000
9.250 1.2297 0.01897 0.01143 -0.0498 0.0092 1.0000
9.500 1.2445 0.01958 0.01211 -0.0480 0.0087 1.0000
9.750 1.2587 0.02026 0.01287 -0.0462 0.0083 1.0000
10.000 1.2718 0.02102 0.01371 -0.0444 0.0080 1.0000
10.250 1.2844 0.02184 0.01460 -0.0425 0.0077 1.0000
10.500 1.2954 0.02279 0.01563 -0.0407 0.0074 1.0000
10.750 1.3049 0.02386 0.01680 -0.0387 0.0072 1.0000
11.000 1.3126 0.02510 0.01812 -0.0367 0.0070 1.0000
11.250 1.3220 0.02623 0.01935 -0.0349 0.0069 1.0000
11.500 1.3312 0.02741 0.02063 -0.0333 0.0068 1.0000
11.750 1.3393 0.02870 0.02202 -0.0318 0.0066 1.0000
12.000 1.3459 0.03017 0.02359 -0.0302 0.0064 1.0000
12.250 1.3528 0.03163 0.02515 -0.0288 0.0062 1.0000
12.500 1.3567 0.03344 0.02706 -0.0274 0.0061 1.0000
12.750 1.3602 0.03533 0.02905 -0.0261 0.0061 1.0000
13.000 1.3628 0.03738 0.03121 -0.0250 0.0059 1.0000
13.250 1.3641 0.03965 0.03359 -0.0240 0.0058 1.0000
13.500 1.3641 0.04214 0.03620 -0.0232 0.0057 1.0000
13.750 1.3642 0.04473 0.03890 -0.0227 0.0057 1.0000
14.000 1.3627 0.04760 0.04189 -0.0224 0.0056 1.0000
14.250 1.3610 0.05064 0.04504 -0.0223 0.0055 1.0000
14.500 1.3581 0.05398 0.04849 -0.0224 0.0055 1.0000
14.750 1.3546 0.05753 0.05216 -0.0228 0.0054 1.0000
15.000 1.3499 0.06142 0.05618 -0.0235 0.0054 1.0000
15.250 1.3455 0.06544 0.06031 -0.0245 0.0053 1.0000
15.500 1.3395 0.06982 0.06480 -0.0257 0.0052 1.0000
15.750 1.3335 0.07434 0.06946 -0.0271 0.0052 1.0000
16.000 1.3265 0.07920 0.07444 -0.0289 0.0052 1.0000
16.250 1.3187 0.08429 0.07964 -0.0308 0.0051 1.0000
16.500 1.3121 0.08934 0.08482 -0.0328 0.0051 1.0000
16.750 1.3032 0.09487 0.09047 -0.0352 0.0050 1.0000
17.000 1.2941 0.10057 0.09629 -0.0377 0.0050 1.0000
17.250 1.2853 0.10633 0.10217 -0.0403 0.0049 1.0000
17.500 1.2774 0.11203 0.10801 -0.0430 0.0049 1.0000
17.750 1.2675 0.11817 0.11428 -0.0460 0.0049 1.0000
18.000 1.2594 0.12417 0.12040 -0.0491 0.0049 1.0000
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