AIRFOIL 3024 9.84% (s3024-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: AIRFOIL 3024 9.84% (s3024-il) Reynolds number: 1,000,000 Max Cl/Cd: 129.05 at α=3.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s3024-il-1000000.txt Download as CSV file: xf-s3024-il-1000000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.2462 0.09666 0.09513 -0.0415 0.9669 0.0106
-10.250 -0.2424 0.09261 0.09106 -0.0431 0.9588 0.0109
-9.250 -0.3324 0.09077 0.08921 -0.0408 0.9889 0.0108
-9.000 -0.3184 0.08530 0.08374 -0.0470 0.9798 0.0111
-8.750 -0.3011 0.07843 0.07685 -0.0558 0.9691 0.0118
-8.500 -0.2875 0.07354 0.07192 -0.0616 0.9546 0.0119
-8.250 -0.2880 0.06900 0.06733 -0.0646 0.9350 0.0119
-8.000 -0.2959 0.06526 0.06354 -0.0659 0.9182 0.0119
-7.750 -0.3030 0.06072 0.05896 -0.0692 0.9044 0.0119
-7.500 -0.3041 0.05419 0.05236 -0.0745 0.8935 0.0120
-7.250 -0.3089 0.02835 0.02637 -0.0730 0.8672 0.0122
-7.000 -0.3131 0.02212 0.01988 -0.0750 0.8608 0.0124
-6.750 -0.3009 0.01948 0.01710 -0.0754 0.8555 0.0126
-6.500 -0.2871 0.01653 0.01397 -0.0759 0.8501 0.0128
-6.250 -0.2708 0.01414 0.01138 -0.0760 0.8451 0.0132
-6.000 -0.2535 0.01159 0.00857 -0.0760 0.8404 0.0137
-5.750 -0.2417 0.01779 0.01351 -0.0794 0.8466 0.0114
-5.500 -0.2192 0.01552 0.01086 -0.0786 0.8420 0.0112
-5.250 -0.1940 0.01415 0.00927 -0.0782 0.8372 0.0113
-5.000 -0.1683 0.01303 0.00796 -0.0778 0.8324 0.0113
-4.750 -0.1424 0.01212 0.00688 -0.0773 0.8279 0.0113
-4.500 -0.1158 0.01131 0.00597 -0.0771 0.8231 0.0114
-4.250 -0.0887 0.01084 0.00541 -0.0769 0.8181 0.0117
-4.000 -0.0616 0.01047 0.00495 -0.0766 0.8135 0.0119
-3.750 -0.0347 0.00985 0.00428 -0.0764 0.8084 0.0120
-3.500 -0.0085 0.00914 0.00348 -0.0760 0.8031 0.0122
-3.250 0.0180 0.00859 0.00282 -0.0757 0.7981 0.0129
-3.000 0.0457 0.00826 0.00248 -0.0756 0.7926 0.0139
-2.750 0.0734 0.00803 0.00219 -0.0755 0.7870 0.0149
-2.500 0.1013 0.00785 0.00196 -0.0754 0.7816 0.0158
-2.250 0.1292 0.00761 0.00170 -0.0753 0.7755 0.0187
-2.000 0.1562 0.00726 0.00148 -0.0751 0.7697 0.0589
-1.750 0.1836 0.00692 0.00136 -0.0751 0.7633 0.1190
-1.500 0.2108 0.00668 0.00126 -0.0751 0.7566 0.1782
-1.250 0.2382 0.00643 0.00120 -0.0751 0.7498 0.2446
-1.000 0.2649 0.00613 0.00114 -0.0750 0.7422 0.3373
-0.750 0.2915 0.00578 0.00111 -0.0749 0.7345 0.4508
-0.500 0.3173 0.00543 0.00110 -0.0746 0.7265 0.5770
-0.250 0.3420 0.00503 0.00110 -0.0740 0.7181 0.7186
0.000 0.3625 0.00461 0.00115 -0.0721 0.7098 0.8814
0.250 0.3947 0.00454 0.00119 -0.0726 0.7005 0.9627
0.500 0.4328 0.00459 0.00117 -0.0748 0.6908 0.9840
0.750 0.4765 0.00464 0.00115 -0.0782 0.6799 0.9936
1.000 0.5198 0.00469 0.00112 -0.0817 0.6676 1.0000
1.250 0.5453 0.00475 0.00113 -0.0812 0.6552 1.0000
1.500 0.5706 0.00484 0.00115 -0.0806 0.6413 1.0000
1.750 0.5960 0.00493 0.00117 -0.0801 0.6266 1.0000
2.000 0.6212 0.00505 0.00121 -0.0796 0.6111 1.0000
2.500 0.6716 0.00531 0.00133 -0.0785 0.5772 1.0000
2.750 0.6967 0.00545 0.00140 -0.0780 0.5591 1.0000
3.000 0.7217 0.00562 0.00149 -0.0775 0.5401 1.0000
3.500 0.7717 0.00598 0.00169 -0.0764 0.5016 1.0000
3.750 0.7966 0.00618 0.00181 -0.0759 0.4806 1.0000
4.000 0.8215 0.00639 0.00195 -0.0754 0.4597 1.0000
4.250 0.8463 0.00662 0.00209 -0.0749 0.4364 1.0000
4.500 0.8711 0.00686 0.00224 -0.0744 0.4136 1.0000
4.750 0.8956 0.00713 0.00241 -0.0739 0.3907 1.0000
5.000 0.9202 0.00740 0.00260 -0.0734 0.3671 1.0000
5.250 0.9444 0.00770 0.00280 -0.0729 0.3435 1.0000
5.500 0.9678 0.00806 0.00303 -0.0722 0.3130 1.0000
5.750 0.9908 0.00846 0.00328 -0.0715 0.2816 1.0000
6.000 1.0138 0.00886 0.00355 -0.0709 0.2529 1.0000
6.250 1.0368 0.00925 0.00382 -0.0702 0.2280 1.0000
6.500 1.0596 0.00965 0.00411 -0.0695 0.2038 1.0000
6.750 1.0826 0.01003 0.00441 -0.0688 0.1826 1.0000
7.000 1.1047 0.01047 0.00473 -0.0680 0.1606 1.0000
7.250 1.1267 0.01091 0.00508 -0.0672 0.1394 1.0000
7.500 1.1469 0.01148 0.00550 -0.0662 0.1124 1.0000
7.750 1.1670 0.01204 0.00594 -0.0651 0.0900 1.0000
8.000 1.1858 0.01269 0.00644 -0.0639 0.0663 1.0000
8.250 1.1997 0.01369 0.00719 -0.0619 0.0322 1.0000
8.500 1.2143 0.01460 0.00796 -0.0600 0.0130 1.0000
8.750 1.2333 0.01515 0.00852 -0.0587 0.0110 1.0000
9.000 1.2512 0.01574 0.00916 -0.0572 0.0097 1.0000
9.250 1.2695 0.01624 0.00972 -0.0558 0.0094 1.0000
9.500 1.2854 0.01675 0.01029 -0.0540 0.0091 1.0000
9.750 1.2993 0.01734 0.01093 -0.0518 0.0086 1.0000
10.000 1.3125 0.01797 0.01163 -0.0497 0.0084 1.0000
10.250 1.3249 0.01868 0.01240 -0.0476 0.0080 1.0000
10.500 1.3350 0.01956 0.01334 -0.0452 0.0076 1.0000
10.750 1.3404 0.02077 0.01466 -0.0424 0.0073 1.0000
11.000 1.3445 0.02210 0.01610 -0.0396 0.0071 1.0000
11.250 1.3529 0.02319 0.01727 -0.0375 0.0070 1.0000
11.500 1.3603 0.02439 0.01855 -0.0355 0.0070 1.0000
11.750 1.3697 0.02548 0.01972 -0.0338 0.0069 1.0000
12.000 1.3787 0.02664 0.02095 -0.0321 0.0068 1.0000
12.250 1.3827 0.02823 0.02265 -0.0302 0.0068 1.0000
12.500 1.3874 0.02984 0.02435 -0.0285 0.0067 1.0000
12.750 1.3903 0.03165 0.02626 -0.0269 0.0066 1.0000
13.000 1.3958 0.03331 0.02800 -0.0257 0.0064 1.0000
13.250 1.3971 0.03542 0.03021 -0.0243 0.0064 1.0000
13.500 1.3977 0.03770 0.03259 -0.0232 0.0063 1.0000
13.750 1.4005 0.03984 0.03481 -0.0224 0.0061 1.0000
14.000 1.3996 0.04245 0.03753 -0.0216 0.0061 1.0000
14.250 1.3983 0.04522 0.04041 -0.0210 0.0060 1.0000
14.500 1.3975 0.04806 0.04335 -0.0208 0.0060 1.0000
14.750 1.3941 0.05134 0.04674 -0.0206 0.0060 1.0000
15.000 1.3913 0.05472 0.05024 -0.0208 0.0058 1.0000
15.250 1.3906 0.05794 0.05355 -0.0214 0.0057 1.0000
15.500 1.3853 0.06193 0.05765 -0.0220 0.0057 1.0000
15.750 1.3838 0.06554 0.06133 -0.0231 0.0055 1.0000
16.000 1.3754 0.07025 0.06620 -0.0242 0.0056 1.0000
16.250 1.3715 0.07448 0.07050 -0.0257 0.0054 1.0000
16.500 1.3632 0.07947 0.07559 -0.0274 0.0053 1.0000
16.750 1.3559 0.08449 0.08072 -0.0293 0.0053 1.0000
17.000 1.3481 0.08971 0.08606 -0.0314 0.0053 1.0000
17.250 1.3384 0.09535 0.09182 -0.0338 0.0052 1.0000
17.500 1.3293 0.10108 0.09766 -0.0364 0.0052 1.0000
17.750 1.3204 0.10699 0.10370 -0.0393 0.0052 1.0000
18.000 1.3102 0.11315 0.10998 -0.0423 0.0052 1.0000
18.250 1.2961 0.12012 0.11708 -0.0458 0.0051 1.0000
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