NACA CYH (nacacyh-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA CYH (nacacyh-il) Reynolds number: 100,000 Max Cl/Cd: 47.83 at α=6.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-nacacyh-il-100000.txt Download as CSV file: xf-nacacyh-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: NACA CYH
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.4312 0.10035 0.09547 -0.0156 1.0000 0.1287
-9.750 -0.4601 0.09680 0.09206 -0.0246 1.0000 0.1338
-9.500 -0.4523 0.09207 0.08736 -0.0243 1.0000 0.1363
-9.250 -0.4282 0.08960 0.08487 -0.0206 1.0000 0.1417
-9.000 -0.4446 0.08587 0.08124 -0.0260 1.0000 0.1477
-8.750 -0.4676 0.08093 0.07637 -0.0319 1.0000 0.1511
-8.500 -0.4416 0.07845 0.07392 -0.0274 1.0000 0.1549
-8.250 -0.4438 0.07531 0.07082 -0.0290 1.0000 0.1615
-8.000 -0.4656 0.07144 0.06697 -0.0313 1.0000 0.1671
-7.750 -0.4562 0.06928 0.06491 -0.0280 1.0000 0.1703
-7.500 -0.4696 0.06796 0.06366 -0.0241 1.0000 0.1738
-7.250 -0.5211 0.06765 0.06314 -0.0217 1.0000 0.1815
-7.000 -0.5157 0.06474 0.06038 -0.0182 1.0000 0.1833
-6.750 -0.4968 0.06216 0.05784 -0.0180 0.9967 0.1892
-6.500 -0.4682 0.05847 0.05403 -0.0221 0.9891 0.2051
-6.250 -0.4431 0.03983 0.03337 -0.0333 0.9790 0.1082
-6.000 -0.4091 0.03529 0.02815 -0.0354 0.9723 0.0991
-5.750 -0.3755 0.03200 0.02428 -0.0370 0.9654 0.0964
-5.500 -0.3384 0.02988 0.02173 -0.0391 0.9586 0.0981
-5.250 -0.3000 0.02790 0.01934 -0.0411 0.9525 0.0989
-5.000 -0.2634 0.02629 0.01737 -0.0426 0.9451 0.1001
-4.750 -0.2175 0.02482 0.01557 -0.0457 0.9406 0.1029
-4.500 -0.1849 0.02362 0.01432 -0.0467 0.9322 0.1077
-4.250 -0.1417 0.02258 0.01324 -0.0494 0.9267 0.1155
-4.000 -0.1072 0.02156 0.01226 -0.0505 0.9192 0.1236
-3.750 -0.0717 0.02062 0.01145 -0.0518 0.9119 0.1404
-3.500 -0.0401 0.01965 0.01077 -0.0523 0.9044 0.1836
-3.250 -0.0120 0.01840 0.01027 -0.0523 0.8957 0.3082
-3.000 0.0095 0.01684 0.01001 -0.0508 0.8861 0.5612
-2.750 0.2003 0.01589 0.00953 -0.0762 0.8900 1.0000
-2.500 0.2235 0.01582 0.00927 -0.0749 0.8764 1.0000
-2.250 0.2455 0.01588 0.00916 -0.0738 0.8632 1.0000
-2.000 0.2677 0.01595 0.00908 -0.0726 0.8511 1.0000
-1.750 0.2902 0.01599 0.00899 -0.0714 0.8400 1.0000
-1.500 0.3127 0.01603 0.00889 -0.0701 0.8290 1.0000
-1.250 0.3347 0.01616 0.00891 -0.0690 0.8167 1.0000
-1.000 0.3569 0.01627 0.00892 -0.0677 0.8054 1.0000
-0.750 0.3794 0.01630 0.00881 -0.0662 0.7955 1.0000
-0.500 0.4014 0.01645 0.00890 -0.0650 0.7826 1.0000
-0.250 0.4234 0.01658 0.00896 -0.0638 0.7703 1.0000
0.000 0.4459 0.01667 0.00896 -0.0625 0.7591 1.0000
0.250 0.4686 0.01673 0.00893 -0.0611 0.7479 1.0000
0.500 0.4906 0.01687 0.00902 -0.0599 0.7345 1.0000
0.750 0.5128 0.01699 0.00909 -0.0586 0.7213 1.0000
1.000 0.5353 0.01707 0.00910 -0.0572 0.7083 1.0000
1.250 0.5583 0.01711 0.00908 -0.0559 0.6957 1.0000
1.500 0.5815 0.01714 0.00903 -0.0546 0.6828 1.0000
1.750 0.6040 0.01722 0.00906 -0.0534 0.6678 1.0000
2.000 0.6266 0.01727 0.00908 -0.0521 0.6524 1.0000
2.250 0.6494 0.01733 0.00909 -0.0509 0.6369 1.0000
2.500 0.6724 0.01740 0.00911 -0.0497 0.6213 1.0000
2.750 0.6955 0.01749 0.00916 -0.0486 0.6057 1.0000
3.000 0.7186 0.01760 0.00921 -0.0476 0.5901 1.0000
3.250 0.7418 0.01776 0.00932 -0.0466 0.5748 1.0000
3.500 0.7649 0.01798 0.00951 -0.0456 0.5601 1.0000
3.750 0.7879 0.01822 0.00972 -0.0447 0.5458 1.0000
4.000 0.8109 0.01847 0.00993 -0.0438 0.5318 1.0000
4.250 0.8339 0.01873 0.01016 -0.0429 0.5184 1.0000
4.500 0.8573 0.01900 0.01039 -0.0420 0.5059 1.0000
4.750 0.8814 0.01927 0.01059 -0.0413 0.4942 1.0000
5.000 0.9031 0.01963 0.01099 -0.0404 0.4811 1.0000
5.250 0.9249 0.01994 0.01132 -0.0394 0.4674 1.0000
5.500 0.9467 0.02022 0.01160 -0.0383 0.4534 1.0000
5.750 0.9686 0.02053 0.01191 -0.0374 0.4400 1.0000
6.000 0.9911 0.02089 0.01225 -0.0366 0.4277 1.0000
6.250 1.0143 0.02124 0.01256 -0.0358 0.4156 1.0000
6.500 1.0355 0.02165 0.01303 -0.0349 0.4026 1.0000
6.750 1.0561 0.02210 0.01354 -0.0339 0.3890 1.0000
7.000 1.0768 0.02256 0.01406 -0.0329 0.3750 1.0000
7.250 1.0971 0.02307 0.01460 -0.0319 0.3604 1.0000
7.500 1.1169 0.02359 0.01515 -0.0308 0.3449 1.0000
7.750 1.1359 0.02414 0.01571 -0.0296 0.3281 1.0000
8.000 1.1541 0.02472 0.01629 -0.0283 0.3103 1.0000
8.250 1.1718 0.02538 0.01688 -0.0270 0.2919 1.0000
8.500 1.1850 0.02609 0.01774 -0.0251 0.2721 1.0000
8.750 1.1982 0.02675 0.01844 -0.0232 0.2530 1.0000
9.000 1.2108 0.02739 0.01908 -0.0213 0.2357 1.0000
9.250 1.2222 0.02808 0.01975 -0.0194 0.2199 1.0000
9.500 1.2326 0.02888 0.02055 -0.0175 0.2056 1.0000
9.750 1.2432 0.02983 0.02153 -0.0157 0.1932 1.0000
10.000 1.2532 0.03088 0.02260 -0.0139 0.1823 1.0000
10.250 1.2620 0.03195 0.02364 -0.0120 0.1725 1.0000
10.500 1.2673 0.03305 0.02479 -0.0097 0.1631 1.0000
10.750 1.2711 0.03435 0.02620 -0.0076 0.1541 1.0000
11.000 1.2748 0.03572 0.02754 -0.0058 0.1452 1.0000
11.250 1.2757 0.03727 0.02924 -0.0041 0.1367 1.0000
11.500 1.2762 0.03909 0.03117 -0.0026 0.1282 1.0000
11.750 1.2754 0.04106 0.03311 -0.0014 0.1191 1.0000
12.000 1.2682 0.04363 0.03587 -0.0004 0.1093 1.0000
12.250 1.2588 0.04672 0.03905 0.0004 0.0983 1.0000
12.500 1.2481 0.05022 0.04257 0.0009 0.0876 1.0000
12.750 1.2398 0.05368 0.04600 0.0013 0.0788 1.0000
13.000 1.2339 0.05699 0.04932 0.0014 0.0721 1.0000
13.250 1.2308 0.06029 0.05273 0.0018 0.0668 1.0000
13.500 1.2296 0.06334 0.05585 0.0019 0.0628 1.0000
13.750 1.2352 0.06574 0.05815 0.0027 0.0593 1.0000
14.000 1.2302 0.06953 0.06223 0.0024 0.0572 1.0000
14.250 1.2260 0.07321 0.06609 0.0020 0.0551 1.0000
14.500 1.2238 0.07660 0.06958 0.0015 0.0532 1.0000
14.750 1.2340 0.07853 0.07135 0.0022 0.0506 1.0000
15.000 1.2214 0.08354 0.07666 0.0008 0.0499 1.0000
15.250 1.2078 0.08895 0.08235 -0.0009 0.0493 1.0000
15.500 1.1921 0.09493 0.08859 -0.0031 0.0488 1.0000
15.750 1.1735 0.10167 0.09558 -0.0059 0.0486 1.0000
16.000 1.1509 0.10945 0.10360 -0.0096 0.0487 1.0000
16.250 1.1239 0.11855 0.11292 -0.0144 0.0490 1.0000
16.500 1.0931 0.12907 0.12365 -0.0201 0.0496 1.0000
16.750 1.0605 0.14076 0.13549 -0.0266 0.0503 1.0000
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