NACA 1-H-15 AIRFOIL (n1h15-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 1-H-15 AIRFOIL (n1h15-il) Reynolds number: 500,000 Max Cl/Cd: 103.65 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-n1h15-il-500000.txt Download as CSV file: xf-n1h15-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 1-H-15 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.2454 0.09090 0.08791 -0.0560 0.7196 0.0300
-9.250 -0.2529 0.08620 0.08325 -0.0603 0.7183 0.0301
-9.000 -0.2591 0.08179 0.07886 -0.0643 0.7170 0.0301
-8.750 -0.2697 0.07731 0.07435 -0.0675 0.7158 0.0302
-8.500 -0.2723 0.07380 0.07086 -0.0664 0.7149 0.0305
-8.250 -0.2731 0.07160 0.06864 -0.0656 0.7139 0.0307
-8.000 -0.2716 0.06896 0.06595 -0.0658 0.7131 0.0309
-7.750 -0.2669 0.06659 0.06354 -0.0658 0.7122 0.0313
-7.500 -0.2628 0.06393 0.06082 -0.0662 0.7112 0.0316
-7.250 -0.2547 0.06112 0.05799 -0.0674 0.7096 0.0321
-7.000 -0.2454 0.05817 0.05500 -0.0686 0.7075 0.0329
-6.750 -0.2458 0.05168 0.04796 -0.0692 0.7053 0.0359
-6.500 -0.2419 0.04696 0.04320 -0.0688 0.7038 0.0365
-6.250 -0.2266 0.04514 0.04135 -0.0684 0.7025 0.0369
-6.000 -0.2105 0.04349 0.03963 -0.0678 0.7015 0.0373
-5.750 -0.1943 0.04173 0.03778 -0.0670 0.7005 0.0380
-5.500 -0.1779 0.03984 0.03575 -0.0661 0.6997 0.0391
-5.250 -0.1605 0.03843 0.03371 -0.0633 0.6989 0.0427
-5.000 -0.1519 0.03375 0.02892 -0.0619 0.6982 0.0439
-4.750 -0.1314 0.03253 0.02767 -0.0614 0.6975 0.0447
-4.500 -0.1106 0.03145 0.02653 -0.0607 0.6968 0.0457
-4.250 -0.0866 0.03063 0.02560 -0.0611 0.6942 0.0481
-4.000 -0.0671 0.02902 0.02361 -0.0602 0.6905 0.0524
-3.750 -0.0438 0.02793 0.02252 -0.0601 0.6889 0.0535
-3.500 -0.0204 0.02706 0.02159 -0.0598 0.6877 0.0552
-3.250 0.0044 0.02672 0.02106 -0.0590 0.6867 0.0592
-3.000 0.0248 0.02504 0.01915 -0.0579 0.6858 0.0632
-2.750 0.0513 0.02156 0.01492 -0.0555 0.6851 0.0432
-2.500 0.0787 0.01999 0.01329 -0.0554 0.6845 0.0413
-2.250 0.1060 0.01903 0.01222 -0.0552 0.6840 0.0409
-2.000 0.1334 0.01826 0.01136 -0.0550 0.6834 0.0406
-1.750 0.1605 0.01765 0.01069 -0.0548 0.6828 0.0408
-1.500 0.1872 0.01713 0.01012 -0.0545 0.6822 0.0409
-1.250 0.2111 0.01865 0.01178 -0.0569 0.6739 0.0414
-1.000 0.2369 0.01844 0.01155 -0.0567 0.6728 0.0421
-0.750 0.2624 0.01821 0.01130 -0.0564 0.6718 0.0427
-0.500 0.2870 0.01775 0.01083 -0.0558 0.6711 0.0432
-0.250 0.3114 0.01731 0.01038 -0.0550 0.6704 0.0442
0.000 0.3124 0.02029 0.01345 -0.0547 0.6589 0.0450
0.250 0.3361 0.02015 0.01332 -0.0541 0.6578 0.0466
0.500 0.3617 0.01991 0.01308 -0.0536 0.6573 0.0483
0.750 0.3879 0.01966 0.01282 -0.0532 0.6567 0.0504
1.000 0.4140 0.01938 0.01256 -0.0528 0.6562 0.0557
1.250 0.4400 0.01909 0.01234 -0.0524 0.6557 0.0745
1.500 0.4318 0.01707 0.01216 -0.0455 0.6548 0.6904
1.750 0.7365 0.01397 0.00961 -0.0975 0.6688 1.0000
2.000 0.7607 0.01390 0.00951 -0.0969 0.6681 1.0000
2.250 0.7849 0.01386 0.00944 -0.0963 0.6674 1.0000
2.500 0.8125 0.01625 0.01200 -0.1002 0.6592 1.0000
2.750 0.8365 0.01637 0.01212 -0.1000 0.6578 1.0000
3.000 0.8607 0.01631 0.01206 -0.0995 0.6569 1.0000
3.250 0.8850 0.01619 0.01193 -0.0989 0.6561 1.0000
3.500 0.9111 0.01536 0.01106 -0.0977 0.6557 1.0000
3.750 0.9367 0.01474 0.01042 -0.0968 0.6551 1.0000
4.000 0.9624 0.01407 0.00972 -0.0957 0.6542 1.0000
4.250 0.9879 0.01344 0.00904 -0.0946 0.6533 1.0000
4.500 1.0128 0.01429 0.01001 -0.0958 0.6487 1.0000
4.750 1.0382 0.01439 0.01015 -0.0960 0.6451 1.0000
5.000 1.0656 0.01362 0.00937 -0.0952 0.6429 1.0000
5.250 1.0922 0.01300 0.00873 -0.0945 0.6411 1.0000
5.500 1.1188 0.01198 0.00763 -0.0931 0.6384 1.0000
5.750 1.1475 0.01210 0.00787 -0.0943 0.6293 1.0000
6.000 1.1744 0.01133 0.00703 -0.0934 0.6238 1.0000
6.250 1.2047 0.01181 0.00763 -0.0956 0.6127 1.0000
6.500 1.2326 0.01219 0.00807 -0.0970 0.5992 1.0000
6.750 1.2562 0.01272 0.00857 -0.0976 0.5782 1.0000
7.000 1.2629 0.01401 0.00972 -0.0960 0.5383 1.0000
7.250 1.2389 0.01559 0.01113 -0.0885 0.5066 1.0000
7.500 1.2074 0.01698 0.01239 -0.0792 0.4833 1.0000
7.750 1.1747 0.01902 0.01422 -0.0707 0.4481 1.0000
8.000 1.1438 0.02153 0.01647 -0.0633 0.4060 1.0000
8.250 1.1124 0.02448 0.01913 -0.0565 0.3555 1.0000
8.500 1.0798 0.02786 0.02212 -0.0501 0.2906 1.0000
9.000 1.0335 0.03408 0.02748 -0.0405 0.1464 1.0000
9.250 1.0216 0.03664 0.02963 -0.0370 0.0839 1.0000
9.500 1.0233 0.03835 0.03119 -0.0348 0.0625 1.0000
9.750 1.0322 0.03956 0.03237 -0.0333 0.0559 1.0000
10.000 1.0403 0.04086 0.03365 -0.0318 0.0515 1.0000
10.250 1.0496 0.04211 0.03493 -0.0304 0.0492 1.0000
10.500 1.0605 0.04326 0.03612 -0.0292 0.0475 1.0000
10.750 1.0711 0.04443 0.03731 -0.0280 0.0458 1.0000
11.000 1.0802 0.04572 0.03862 -0.0268 0.0441 1.0000
11.250 1.0867 0.04727 0.04018 -0.0253 0.0425 1.0000
11.500 1.0922 0.04892 0.04187 -0.0239 0.0413 1.0000
11.750 1.1036 0.05009 0.04309 -0.0229 0.0404 1.0000
12.000 1.1141 0.05133 0.04438 -0.0219 0.0394 1.0000
12.250 1.1243 0.05262 0.04571 -0.0208 0.0384 1.0000
12.500 1.1339 0.05398 0.04709 -0.0199 0.0372 1.0000
12.750 1.1425 0.05542 0.04856 -0.0188 0.0362 1.0000
13.000 1.1495 0.05694 0.05009 -0.0176 0.0352 1.0000
13.250 1.1564 0.05837 0.05155 -0.0162 0.0341 1.0000
13.500 1.1684 0.05956 0.05280 -0.0155 0.0334 1.0000
13.750 1.1793 0.06081 0.05410 -0.0146 0.0326 1.0000
14.000 1.1901 0.06209 0.05543 -0.0138 0.0317 1.0000
14.250 1.2008 0.06335 0.05673 -0.0130 0.0309 1.0000
14.500 1.2114 0.06461 0.05801 -0.0122 0.0301 1.0000
14.750 1.2218 0.06579 0.05917 -0.0113 0.0292 1.0000
15.000 1.2345 0.06650 0.05991 -0.0100 0.0281 1.0000
15.250 1.2454 0.06784 0.06134 -0.0093 0.0276 1.0000
15.500 1.2559 0.06921 0.06279 -0.0087 0.0268 1.0000
15.750 1.2658 0.07065 0.06430 -0.0081 0.0260 1.0000
16.000 1.2755 0.07210 0.06581 -0.0075 0.0254 1.0000
16.250 1.2845 0.07361 0.06736 -0.0069 0.0247 1.0000
16.500 1.2936 0.07513 0.06889 -0.0064 0.0242 1.0000
16.750 1.3093 0.07543 0.06919 -0.0051 0.0232 1.0000
17.000 1.3146 0.07755 0.07144 -0.0047 0.0228 1.0000
17.250 1.3211 0.07947 0.07349 -0.0042 0.0223 1.0000
17.500 1.3268 0.08151 0.07564 -0.0038 0.0217 1.0000
17.750 1.3324 0.08352 0.07775 -0.0034 0.0212 1.0000
18.000 1.3372 0.08566 0.07998 -0.0031 0.0207 1.0000
18.250 1.3415 0.08788 0.08228 -0.0029 0.0203 1.0000
18.500 1.3455 0.09018 0.08464 -0.0028 0.0200 1.0000
18.750 1.3505 0.09228 0.08676 -0.0027 0.0195 1.0000
19.000 1.3558 0.09409 0.08865 -0.0018 0.0189 1.0000
19.250 1.3536 0.09731 0.09204 -0.0019 0.0188 1.0000
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