NACA 65(2)-415 a=0.5 (naca652415a05-il) Xfoil prediction polar at RE=100,000 Ncrit=5
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Airfoil: NACA 65(2)-415 a=0.5 (naca652415a05-il) Reynolds number: 100,000 Max Cl/Cd: 37.03 at α=8.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca652415a05-il-100000-n5.txt Download as CSV file: xf-naca652415a05-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 65(2)-415 a=0.5
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.500 -0.3789 0.08808 0.08313 -0.0751 0.9349 0.0358
-11.250 -0.3875 0.08011 0.07511 -0.0811 0.9235 0.0356
-11.000 -0.4054 0.07269 0.06759 -0.0868 0.9114 0.0353
-10.750 -0.4239 0.06709 0.06186 -0.0904 0.8997 0.0350
-10.500 -0.4496 0.06208 0.05664 -0.0925 0.8883 0.0351
-10.250 -0.4660 0.05862 0.05301 -0.0925 0.8777 0.0348
-10.000 -0.4899 0.05538 0.04950 -0.0906 0.8670 0.0351
-9.500 -0.5167 0.04932 0.04271 -0.0859 0.8506 0.0357
-9.250 -0.5220 0.04644 0.03933 -0.0834 0.8443 0.0361
-9.000 -0.5155 0.04378 0.03645 -0.0821 0.8382 0.0365
-8.750 -0.5058 0.04150 0.03392 -0.0809 0.8325 0.0369
-8.500 -0.4932 0.03950 0.03167 -0.0796 0.8280 0.0375
-8.250 -0.4781 0.03778 0.02974 -0.0787 0.8224 0.0384
-8.000 -0.4621 0.03624 0.02793 -0.0777 0.8170 0.0398
-7.750 -0.4456 0.03453 0.02586 -0.0764 0.8127 0.0413
-7.500 -0.4268 0.03275 0.02369 -0.0754 0.8085 0.0423
-7.250 -0.4056 0.03117 0.02177 -0.0747 0.8035 0.0431
-7.000 -0.3833 0.02973 0.02008 -0.0741 0.7994 0.0445
-6.750 -0.3603 0.02858 0.01888 -0.0736 0.7961 0.0462
-6.500 -0.3365 0.02758 0.01775 -0.0732 0.7926 0.0480
-6.250 -0.3120 0.02659 0.01665 -0.0729 0.7877 0.0494
-6.000 -0.2874 0.02565 0.01557 -0.0724 0.7837 0.0509
-5.750 -0.2630 0.02490 0.01465 -0.0718 0.7804 0.0531
-5.500 -0.2405 0.02399 0.01381 -0.0712 0.7778 0.0557
-5.250 -0.2184 0.02343 0.01325 -0.0706 0.7733 0.0584
-5.000 -0.1966 0.02289 0.01265 -0.0699 0.7694 0.0610
-4.750 -0.1749 0.02235 0.01204 -0.0690 0.7661 0.0641
-4.500 -0.1536 0.02179 0.01146 -0.0681 0.7632 0.0694
-4.000 -0.1110 0.02099 0.01060 -0.0664 0.7556 0.0848
-3.750 -0.0901 0.02050 0.01021 -0.0656 0.7520 0.1061
-3.500 -0.0726 0.01954 0.00975 -0.0644 0.7492 0.2012
-3.250 -0.0631 0.01805 0.00953 -0.0618 0.7467 0.4717
-3.000 -0.0439 0.01792 0.00978 -0.0598 0.7439 0.5933
-2.750 -0.0244 0.01815 0.01013 -0.0581 0.7394 0.6536
-2.500 -0.0067 0.01853 0.01069 -0.0551 0.7359 0.7219
-2.250 0.0115 0.01903 0.01125 -0.0516 0.7332 0.7706
-2.000 0.0358 0.01923 0.01138 -0.0502 0.7312 0.7891
-1.750 0.0631 0.01926 0.01128 -0.0499 0.7295 0.7978
-1.500 0.0837 0.01953 0.01149 -0.0492 0.7250 0.8069
-1.250 0.1072 0.01970 0.01159 -0.0486 0.7212 0.8150
-1.000 0.1321 0.01976 0.01157 -0.0483 0.7183 0.8236
-0.750 0.1586 0.01983 0.01155 -0.0481 0.7162 0.8315
-0.500 0.1855 0.01985 0.01149 -0.0480 0.7144 0.8400
-0.250 0.2109 0.02000 0.01159 -0.0477 0.7118 0.8482
0.000 0.2290 0.02043 0.01203 -0.0467 0.7067 0.8578
0.250 0.2530 0.02063 0.01220 -0.0464 0.7035 0.8671
0.500 0.2800 0.02076 0.01230 -0.0464 0.7013 0.8756
0.750 0.3075 0.02083 0.01232 -0.0465 0.6993 0.8851
1.000 0.3385 0.02085 0.01231 -0.0471 0.6977 0.8929
1.250 0.3545 0.02148 0.01299 -0.0460 0.6923 0.9051
1.500 0.3789 0.02188 0.01342 -0.0461 0.6886 0.9156
1.750 0.4097 0.02206 0.01360 -0.0470 0.6860 0.9247
2.000 0.4408 0.02215 0.01370 -0.0479 0.6840 0.9349
2.250 0.4789 0.02222 0.01376 -0.0501 0.6824 0.9418
2.500 0.5095 0.02265 0.01423 -0.0516 0.6792 0.9518
2.750 0.5363 0.02344 0.01512 -0.0531 0.6735 0.9633
3.000 0.5740 0.02371 0.01544 -0.0557 0.6707 0.9711
3.250 0.6141 0.02384 0.01561 -0.0585 0.6686 0.9780
3.500 0.6543 0.02386 0.01570 -0.0612 0.6669 0.9853
3.750 0.6959 0.02383 0.01572 -0.0641 0.6654 0.9919
4.000 0.6867 0.02532 0.01730 -0.0602 0.6557 1.0000
4.250 0.7031 0.02541 0.01742 -0.0584 0.6526 1.0000
4.500 0.7282 0.02530 0.01733 -0.0578 0.6506 1.0000
5.000 0.7383 0.02682 0.01893 -0.0519 0.6372 1.0000
5.250 0.7704 0.02656 0.01875 -0.0523 0.6351 1.0000
5.750 0.7937 0.02774 0.02008 -0.0483 0.6212 1.0000
6.000 0.8104 0.02807 0.02051 -0.0469 0.6148 1.0000
6.250 0.8237 0.02841 0.02093 -0.0449 0.6069 1.0000
6.500 0.8684 0.02731 0.01997 -0.0463 0.6042 1.0000
6.750 0.8585 0.02870 0.02141 -0.0418 0.5919 1.0000
7.000 0.9142 0.02635 0.01923 -0.0436 0.5857 1.0000
7.250 0.9178 0.02628 0.01920 -0.0397 0.5683 1.0000
7.500 0.9180 0.02664 0.01961 -0.0360 0.5472 1.0000
7.750 0.9218 0.02708 0.02009 -0.0330 0.5217 1.0000
8.000 0.9263 0.02786 0.02091 -0.0306 0.4924 1.0000
8.250 0.9526 0.02688 0.01981 -0.0290 0.4418 1.0000
8.500 0.9723 0.02626 0.01842 -0.0263 0.3436 1.0000
8.750 0.9634 0.02832 0.02003 -0.0229 0.2806 1.0000
9.000 0.9536 0.03071 0.02202 -0.0200 0.2227 1.0000
9.250 0.9470 0.03306 0.02400 -0.0176 0.1677 1.0000
9.500 0.9435 0.03531 0.02587 -0.0155 0.1189 1.0000
9.750 0.9452 0.03726 0.02757 -0.0139 0.0880 1.0000
10.000 0.9499 0.03904 0.02923 -0.0125 0.0715 1.0000
10.250 0.9562 0.04073 0.03090 -0.0113 0.0624 1.0000
10.500 0.9619 0.04252 0.03265 -0.0101 0.0561 1.0000
10.750 0.9698 0.04416 0.03435 -0.0091 0.0514 1.0000
11.000 0.9754 0.04603 0.03623 -0.0081 0.0482 1.0000
11.250 0.9840 0.04768 0.03798 -0.0072 0.0455 1.0000
11.500 0.9926 0.04935 0.03973 -0.0064 0.0431 1.0000
11.750 1.0011 0.05107 0.04148 -0.0056 0.0412 1.0000
12.000 1.0100 0.05279 0.04320 -0.0048 0.0394 1.0000
12.250 1.0225 0.05423 0.04479 -0.0041 0.0376 1.0000
12.500 1.0351 0.05573 0.04637 -0.0034 0.0359 1.0000
12.750 1.0489 0.05715 0.04785 -0.0027 0.0349 1.0000
13.000 1.0633 0.05861 0.04932 -0.0021 0.0337 1.0000
13.250 1.0819 0.05990 0.05060 -0.0014 0.0328 1.0000
13.500 1.0984 0.06148 0.05236 -0.0008 0.0320 1.0000
13.750 1.1113 0.06338 0.05448 -0.0003 0.0309 1.0000
14.000 1.1233 0.06542 0.05672 0.0001 0.0300 1.0000
14.250 1.1319 0.06772 0.05920 0.0004 0.0291 1.0000
14.500 1.1394 0.07015 0.06180 0.0007 0.0284 1.0000
14.750 1.1460 0.07278 0.06461 0.0009 0.0280 1.0000
15.000 1.1505 0.07567 0.06769 0.0010 0.0277 1.0000
15.250 1.1529 0.07877 0.07095 0.0010 0.0273 1.0000
15.500 1.1529 0.08220 0.07458 0.0008 0.0271 1.0000
15.750 1.1511 0.08591 0.07848 0.0004 0.0269 1.0000
16.000 1.1452 0.09019 0.08295 -0.0002 0.0267 1.0000
16.250 1.1324 0.09521 0.08825 -0.0014 0.0266 1.0000
16.500 1.1188 0.10056 0.09386 -0.0030 0.0266 1.0000
16.750 1.1025 0.10650 0.10005 -0.0052 0.0266 1.0000
17.000 1.0850 0.11293 0.10672 -0.0080 0.0266 1.0000
17.250 1.0660 0.12000 0.11402 -0.0116 0.0266 1.0000
17.500 1.0462 0.12772 0.12195 -0.0158 0.0267 1.0000
17.750 1.0005 0.14215 0.13677 -0.0252 0.0271 1.0000
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