NACA CYH (nacacyh-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA CYH (nacacyh-il) Reynolds number: 200,000 Max Cl/Cd: 64.7 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-nacacyh-il-200000-n5.txt Download as CSV file: xf-nacacyh-il-200000-n5.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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 -0.5129 0.09005 0.08648 -0.0219 1.0000 0.0304
-10.750 -0.5242 0.08309 0.07956 -0.0266 1.0000 0.0306
-10.500 -0.5455 0.07375 0.07029 -0.0346 1.0000 0.0306
-10.250 -0.6151 0.05417 0.05044 -0.0486 1.0000 0.0302
-10.000 -0.6479 0.04483 0.04058 -0.0490 1.0000 0.0307
-9.750 -0.6578 0.03965 0.03492 -0.0471 1.0000 0.0316
-9.500 -0.6606 0.03588 0.03067 -0.0444 1.0000 0.0324
-9.250 -0.6444 0.03239 0.02659 -0.0446 0.9887 0.0331
-9.000 -0.6198 0.02960 0.02332 -0.0455 0.9746 0.0337
-8.750 -0.5925 0.02759 0.02114 -0.0465 0.9611 0.0346
-8.500 -0.5637 0.02636 0.01978 -0.0472 0.9465 0.0355
-8.250 -0.5362 0.02510 0.01829 -0.0475 0.9306 0.0363
-8.000 -0.5100 0.02377 0.01671 -0.0473 0.9141 0.0370
-7.750 -0.4846 0.02258 0.01528 -0.0469 0.8977 0.0376
-7.500 -0.4596 0.02153 0.01400 -0.0462 0.8822 0.0383
-7.250 -0.4348 0.02064 0.01289 -0.0454 0.8675 0.0391
-7.000 -0.4099 0.01988 0.01193 -0.0447 0.8542 0.0401
-6.750 -0.3847 0.01916 0.01103 -0.0439 0.8422 0.0408
-6.500 -0.3595 0.01848 0.01018 -0.0432 0.8313 0.0412
-6.250 -0.3347 0.01763 0.00923 -0.0424 0.8212 0.0419
-6.000 -0.3097 0.01696 0.00850 -0.0417 0.8116 0.0428
-5.500 -0.2586 0.01597 0.00739 -0.0405 0.7945 0.0446
-5.000 -0.2068 0.01520 0.00647 -0.0394 0.7790 0.0475
-4.750 -0.1807 0.01488 0.00606 -0.0389 0.7722 0.0493
-4.500 -0.1546 0.01452 0.00566 -0.0384 0.7645 0.0513
-4.250 -0.1286 0.01421 0.00531 -0.0379 0.7567 0.0538
-4.000 -0.1022 0.01394 0.00500 -0.0374 0.7480 0.0574
-3.750 -0.0760 0.01368 0.00469 -0.0369 0.7397 0.0629
-3.500 -0.0494 0.01342 0.00443 -0.0365 0.7303 0.0737
-3.250 -0.0233 0.01316 0.00418 -0.0360 0.7224 0.0911
-3.000 0.0029 0.01288 0.00399 -0.0356 0.7129 0.1167
-2.750 0.0286 0.01257 0.00382 -0.0352 0.7041 0.1580
-2.500 0.0542 0.01226 0.00370 -0.0347 0.6950 0.2126
-2.250 0.0800 0.01199 0.00359 -0.0343 0.6873 0.2706
-2.000 0.1052 0.01167 0.00349 -0.0339 0.6795 0.3350
-1.750 0.1279 0.01114 0.00339 -0.0330 0.6724 0.4500
-1.500 0.1478 0.00996 0.00366 -0.0302 0.6651 0.8404
-1.250 0.1851 0.01009 0.00378 -0.0314 0.6574 0.9062
-1.000 0.2230 0.01023 0.00386 -0.0329 0.6481 0.9360
-0.750 0.2674 0.01043 0.00396 -0.0358 0.6387 0.9621
-0.500 0.3161 0.01055 0.00397 -0.0399 0.6290 0.9764
-0.250 0.3586 0.01060 0.00395 -0.0430 0.6186 0.9856
0.000 0.4022 0.01064 0.00389 -0.0463 0.6076 0.9936
0.250 0.4463 0.01064 0.00380 -0.0499 0.5951 1.0000
0.500 0.4718 0.01067 0.00375 -0.0495 0.5830 1.0000
0.750 0.4972 0.01071 0.00373 -0.0492 0.5704 1.0000
1.000 0.5223 0.01076 0.00372 -0.0488 0.5578 1.0000
1.250 0.5472 0.01083 0.00373 -0.0483 0.5445 1.0000
1.500 0.5719 0.01092 0.00375 -0.0478 0.5301 1.0000
1.750 0.5963 0.01103 0.00379 -0.0473 0.5142 1.0000
2.000 0.6205 0.01116 0.00384 -0.0467 0.4978 1.0000
2.250 0.6445 0.01130 0.00391 -0.0461 0.4816 1.0000
2.500 0.6682 0.01146 0.00402 -0.0455 0.4653 1.0000
2.750 0.6916 0.01165 0.00413 -0.0449 0.4488 1.0000
3.000 0.7147 0.01185 0.00427 -0.0442 0.4326 1.0000
3.250 0.7376 0.01208 0.00443 -0.0434 0.4173 1.0000
3.500 0.7601 0.01233 0.00460 -0.0426 0.4016 1.0000
3.750 0.7823 0.01260 0.00480 -0.0418 0.3870 1.0000
4.000 0.8044 0.01287 0.00502 -0.0410 0.3741 1.0000
4.250 0.8263 0.01316 0.00525 -0.0401 0.3627 1.0000
4.500 0.8480 0.01346 0.00550 -0.0392 0.3506 1.0000
4.750 0.8699 0.01374 0.00576 -0.0384 0.3388 1.0000
5.000 0.8917 0.01404 0.00604 -0.0376 0.3289 1.0000
5.250 0.9135 0.01434 0.00633 -0.0367 0.3202 1.0000
5.500 0.9357 0.01461 0.00663 -0.0360 0.3127 1.0000
5.750 0.9575 0.01491 0.00696 -0.0352 0.3049 1.0000
6.000 0.9794 0.01520 0.00728 -0.0344 0.2967 1.0000
6.250 1.0007 0.01553 0.00761 -0.0335 0.2876 1.0000
6.500 1.0228 0.01581 0.00795 -0.0328 0.2778 1.0000
6.750 1.0442 0.01614 0.00833 -0.0320 0.2684 1.0000
7.000 1.0653 0.01648 0.00870 -0.0312 0.2570 1.0000
7.250 1.0858 0.01685 0.00908 -0.0304 0.2407 1.0000
7.500 1.1052 0.01729 0.00949 -0.0294 0.2171 1.0000
7.750 1.1216 0.01794 0.01001 -0.0281 0.1887 1.0000
8.000 1.1369 0.01870 0.01065 -0.0267 0.1656 1.0000
8.250 1.1525 0.01945 0.01134 -0.0254 0.1489 1.0000
8.500 1.1677 0.02021 0.01206 -0.0241 0.1342 1.0000
8.750 1.1823 0.02099 0.01281 -0.0227 0.1217 1.0000
9.000 1.1962 0.02178 0.01361 -0.0212 0.1114 1.0000
9.250 1.2085 0.02258 0.01441 -0.0196 0.1027 1.0000
9.500 1.2202 0.02336 0.01523 -0.0178 0.0957 1.0000
9.750 1.2301 0.02430 0.01618 -0.0161 0.0893 1.0000
10.000 1.2412 0.02522 0.01716 -0.0147 0.0819 1.0000
10.250 1.2503 0.02635 0.01833 -0.0133 0.0747 1.0000
10.500 1.2601 0.02751 0.01952 -0.0121 0.0664 1.0000
10.750 1.2674 0.02893 0.02093 -0.0110 0.0547 1.0000
11.000 1.2713 0.03070 0.02266 -0.0099 0.0392 1.0000
11.250 1.2701 0.03304 0.02491 -0.0088 0.0273 1.0000
11.500 1.2701 0.03539 0.02728 -0.0080 0.0234 1.0000
11.750 1.2704 0.03782 0.02977 -0.0074 0.0213 1.0000
12.000 1.2714 0.04027 0.03232 -0.0071 0.0201 1.0000
12.250 1.2721 0.04281 0.03501 -0.0069 0.0191 1.0000
12.500 1.2712 0.04561 0.03793 -0.0068 0.0182 1.0000
12.750 1.2682 0.04871 0.04115 -0.0069 0.0176 1.0000
13.000 1.2633 0.05215 0.04472 -0.0072 0.0170 1.0000
13.250 1.2562 0.05597 0.04868 -0.0078 0.0166 1.0000
13.500 1.2500 0.05982 0.05266 -0.0085 0.0163 1.0000
13.750 1.2445 0.06374 0.05673 -0.0094 0.0160 1.0000
14.000 1.2379 0.06795 0.06108 -0.0105 0.0158 1.0000
14.250 1.2304 0.07246 0.06574 -0.0119 0.0156 1.0000
14.500 1.2221 0.07720 0.07063 -0.0134 0.0154 1.0000
14.750 1.2132 0.08216 0.07573 -0.0151 0.0152 1.0000
15.000 1.2040 0.08727 0.08098 -0.0169 0.0150 1.0000
15.250 1.1945 0.09253 0.08636 -0.0188 0.0148 1.0000
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