AIRFOIL 3024 9.84% (s3024-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: AIRFOIL 3024 9.84% (s3024-il) Reynolds number: 200,000 Max Cl/Cd: 76.1 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s3024-il-200000-n5.txt Download as CSV file: xf-s3024-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.3310 0.09718 0.09370 -0.0389 1.0000 0.0261
-9.000 -0.3300 0.09403 0.09061 -0.0399 1.0000 0.0263
-8.750 -0.3407 0.09079 0.08746 -0.0426 1.0000 0.0292
-8.250 -0.3243 0.08031 0.07703 -0.0564 0.9796 0.0296
-7.750 -0.3070 0.06622 0.06290 -0.0678 0.9620 0.0181
-7.500 -0.2938 0.06186 0.05850 -0.0733 0.9527 0.0177
-7.250 -0.2820 0.05606 0.05261 -0.0799 0.9432 0.0170
-7.000 -0.2733 0.04979 0.04616 -0.0848 0.9331 0.0163
-6.500 -0.2697 0.03195 0.02693 -0.0888 0.9122 0.0140
-6.250 -0.2541 0.02881 0.02334 -0.0883 0.9056 0.0139
-6.000 -0.2359 0.02613 0.02021 -0.0876 0.8999 0.0139
-5.750 -0.2159 0.02386 0.01747 -0.0868 0.8935 0.0139
-5.500 -0.1934 0.02202 0.01521 -0.0860 0.8886 0.0140
-5.250 -0.1709 0.02030 0.01320 -0.0852 0.8830 0.0143
-5.000 -0.1471 0.01900 0.01170 -0.0846 0.8774 0.0146
-4.750 -0.1224 0.01798 0.01052 -0.0840 0.8730 0.0151
-4.500 -0.0976 0.01728 0.00970 -0.0835 0.8671 0.0164
-4.250 -0.0723 0.01652 0.00879 -0.0829 0.8617 0.0176
-4.000 -0.0468 0.01573 0.00787 -0.0822 0.8575 0.0181
-3.750 -0.0222 0.01500 0.00707 -0.0817 0.8511 0.0188
-3.500 0.0033 0.01441 0.00641 -0.0811 0.8458 0.0199
-3.250 0.0294 0.01394 0.00585 -0.0806 0.8413 0.0214
-2.750 0.0817 0.01314 0.00493 -0.0798 0.8296 0.0301
-2.500 0.1076 0.01264 0.00452 -0.0794 0.8242 0.0539
-2.250 0.1333 0.01220 0.00426 -0.0790 0.8178 0.1043
-2.000 0.1587 0.01167 0.00405 -0.0787 0.8129 0.1938
-1.750 0.1832 0.01117 0.00395 -0.0784 0.8059 0.3036
-1.500 0.2082 0.01076 0.00381 -0.0778 0.7999 0.3989
-1.250 0.2318 0.01028 0.00373 -0.0770 0.7934 0.5219
-1.000 0.2530 0.00974 0.00369 -0.0753 0.7865 0.6744
-0.750 0.2776 0.00931 0.00367 -0.0737 0.7805 0.8361
-0.500 0.3304 0.00915 0.00355 -0.0783 0.7736 0.9549
-0.250 0.3780 0.00908 0.00333 -0.0823 0.7674 0.9937
0.000 0.4082 0.00910 0.00326 -0.0829 0.7583 1.0000
0.250 0.4330 0.00912 0.00317 -0.0821 0.7500 1.0000
0.500 0.4578 0.00916 0.00311 -0.0814 0.7406 1.0000
0.750 0.4827 0.00920 0.00308 -0.0808 0.7304 1.0000
1.000 0.5077 0.00925 0.00303 -0.0801 0.7204 1.0000
1.250 0.5329 0.00930 0.00300 -0.0794 0.7098 1.0000
1.500 0.5580 0.00937 0.00300 -0.0788 0.6980 1.0000
1.750 0.5833 0.00944 0.00301 -0.0782 0.6861 1.0000
2.000 0.6086 0.00952 0.00304 -0.0776 0.6737 1.0000
2.250 0.6339 0.00961 0.00306 -0.0770 0.6605 1.0000
2.500 0.6591 0.00972 0.00311 -0.0764 0.6464 1.0000
2.750 0.6843 0.00984 0.00317 -0.0758 0.6312 1.0000
3.000 0.7093 0.00997 0.00325 -0.0752 0.6149 1.0000
3.250 0.7342 0.01013 0.00334 -0.0746 0.5977 1.0000
3.500 0.7588 0.01031 0.00344 -0.0739 0.5796 1.0000
3.750 0.7832 0.01051 0.00358 -0.0732 0.5606 1.0000
4.000 0.8075 0.01073 0.00374 -0.0725 0.5405 1.0000
4.250 0.8313 0.01098 0.00392 -0.0718 0.5199 1.0000
4.500 0.8549 0.01125 0.00412 -0.0710 0.4987 1.0000
4.750 0.8782 0.01154 0.00436 -0.0702 0.4764 1.0000
5.000 0.9011 0.01186 0.00461 -0.0694 0.4536 1.0000
5.250 0.9235 0.01222 0.00489 -0.0685 0.4297 1.0000
5.500 0.9458 0.01258 0.00521 -0.0676 0.4062 1.0000
5.750 0.9674 0.01299 0.00554 -0.0666 0.3830 1.0000
6.000 0.9890 0.01340 0.00589 -0.0656 0.3593 1.0000
6.250 1.0100 0.01385 0.00628 -0.0646 0.3365 1.0000
6.500 1.0307 0.01431 0.00671 -0.0636 0.3143 1.0000
6.750 1.0511 0.01479 0.00715 -0.0625 0.2937 1.0000
7.000 1.0709 0.01531 0.00761 -0.0613 0.2711 1.0000
7.250 1.0893 0.01590 0.00812 -0.0600 0.2452 1.0000
7.500 1.1068 0.01655 0.00868 -0.0586 0.2178 1.0000
7.750 1.1235 0.01725 0.00925 -0.0571 0.1903 1.0000
8.250 1.1568 0.01862 0.01049 -0.0542 0.1469 1.0000
8.500 1.1713 0.01941 0.01118 -0.0525 0.1248 1.0000
8.750 1.1848 0.02019 0.01191 -0.0506 0.1049 1.0000
9.000 1.1960 0.02108 0.01271 -0.0484 0.0846 1.0000
9.250 1.2067 0.02203 0.01358 -0.0462 0.0665 1.0000
9.500 1.2169 0.02305 0.01454 -0.0441 0.0500 1.0000
9.750 1.2249 0.02427 0.01568 -0.0418 0.0344 1.0000
10.000 1.2321 0.02558 0.01696 -0.0396 0.0234 1.0000
10.250 1.2408 0.02681 0.01826 -0.0376 0.0193 1.0000
10.750 1.2572 0.02943 0.02104 -0.0339 0.0155 1.0000
11.000 1.2650 0.03081 0.02254 -0.0322 0.0144 1.0000
11.250 1.2702 0.03244 0.02426 -0.0305 0.0134 1.0000
11.500 1.2744 0.03420 0.02614 -0.0289 0.0129 1.0000
11.750 1.2790 0.03598 0.02807 -0.0274 0.0126 1.0000
12.000 1.2825 0.03791 0.03018 -0.0261 0.0122 1.0000
12.250 1.2849 0.04001 0.03241 -0.0249 0.0121 1.0000
12.500 1.2857 0.04236 0.03492 -0.0239 0.0118 1.0000
12.750 1.2859 0.04485 0.03755 -0.0231 0.0116 1.0000
13.000 1.2849 0.04758 0.04042 -0.0225 0.0114 1.0000
13.250 1.2835 0.05046 0.04344 -0.0221 0.0112 1.0000
13.500 1.2807 0.05363 0.04675 -0.0219 0.0110 1.0000
13.750 1.2782 0.05688 0.05013 -0.0219 0.0109 1.0000
14.000 1.2751 0.06035 0.05374 -0.0222 0.0107 1.0000
14.250 1.2715 0.06404 0.05756 -0.0227 0.0106 1.0000
14.500 1.2684 0.06779 0.06144 -0.0234 0.0105 1.0000
14.750 1.2645 0.07174 0.06555 -0.0243 0.0104 1.0000
15.000 1.2600 0.07595 0.06988 -0.0253 0.0103 1.0000
15.250 1.2558 0.08021 0.07426 -0.0266 0.0101 1.0000
15.500 1.2503 0.08472 0.07888 -0.0280 0.0099 1.0000
15.750 1.2457 0.08923 0.08353 -0.0295 0.0099 1.0000
16.000 1.2398 0.09407 0.08849 -0.0312 0.0097 1.0000
16.250 1.2337 0.09925 0.09386 -0.0335 0.0096 1.0000
16.500 1.2277 0.10446 0.09924 -0.0358 0.0095 1.0000
16.750 1.2200 0.11022 0.10519 -0.0387 0.0094 1.0000
17.000 1.2116 0.11626 0.11141 -0.0418 0.0093 1.0000
17.250 1.2033 0.12241 0.11773 -0.0451 0.0093 1.0000
17.500 1.1945 0.12877 0.12426 -0.0486 0.0093 1.0000
17.750 1.1843 0.13567 0.13133 -0.0526 0.0092 1.0000
18.000 1.1744 0.14271 0.13853 -0.0568 0.0092 1.0000
18.250 1.1631 0.15034 0.14632 -0.0615 0.0092 1.0000
18.500 1.1518 0.15820 0.15434 -0.0664 0.0093 1.0000
18.750 1.1397 0.16658 0.16287 -0.0717 0.0093 1.0000
|
Polar data table (+)
Polar graphs
<< Back to AIRFOIL 3024 9.84% (s3024-il)