NACA CYH (nacacyh-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA CYH (nacacyh-il) Reynolds number: 500,000 Max Cl/Cd: 90.52 at α=6.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-nacacyh-il-500000.txt Download as CSV file: xf-nacacyh-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.4044 0.07917 0.07708 -0.0301 1.0000 0.0390
-10.500 -0.3982 0.07672 0.07464 -0.0301 1.0000 0.0395
-10.250 -0.3964 0.07335 0.07129 -0.0310 1.0000 0.0401
-10.000 -0.6651 0.04210 0.03880 -0.0482 1.0000 0.0318
-9.750 -0.6671 0.03841 0.03480 -0.0458 1.0000 0.0317
-9.500 -0.6684 0.03539 0.03152 -0.0425 1.0000 0.0317
-9.250 -0.6491 0.03006 0.02567 -0.0442 0.9918 0.0318
-9.000 -0.6254 0.02592 0.02116 -0.0456 0.9819 0.0324
-8.750 -0.5932 0.02489 0.02013 -0.0470 0.9703 0.0334
-8.500 -0.5645 0.02373 0.01886 -0.0475 0.9540 0.0342
-8.250 -0.5423 0.02209 0.01695 -0.0465 0.9317 0.0346
-8.000 -0.5216 0.02075 0.01534 -0.0450 0.9091 0.0351
-7.750 -0.5000 0.01966 0.01400 -0.0436 0.8879 0.0357
-7.500 -0.4769 0.01880 0.01291 -0.0425 0.8697 0.0364
-7.250 -0.4530 0.01794 0.01182 -0.0415 0.8546 0.0370
-7.000 -0.4282 0.01714 0.01082 -0.0406 0.8416 0.0373
-6.750 -0.4028 0.01649 0.01000 -0.0399 0.8298 0.0377
-6.500 -0.3767 0.01588 0.00925 -0.0393 0.8195 0.0381
-6.250 -0.3526 0.01450 0.00774 -0.0386 0.8107 0.0390
-6.000 -0.3268 0.01384 0.00704 -0.0381 0.8016 0.0400
-5.750 -0.3008 0.01336 0.00648 -0.0375 0.7935 0.0407
-5.500 -0.2744 0.01291 0.00598 -0.0370 0.7847 0.0414
-5.250 -0.2482 0.01253 0.00552 -0.0364 0.7763 0.0423
-5.000 -0.2218 0.01215 0.00509 -0.0359 0.7676 0.0432
-4.750 -0.1952 0.01184 0.00470 -0.0355 0.7602 0.0442
-4.500 -0.1682 0.01157 0.00438 -0.0351 0.7524 0.0453
-4.250 -0.1422 0.01118 0.00392 -0.0345 0.7452 0.0471
-4.000 -0.1153 0.01086 0.00361 -0.0342 0.7373 0.0492
-3.750 -0.0883 0.01067 0.00336 -0.0338 0.7304 0.0517
-3.250 -0.0339 0.01022 0.00290 -0.0331 0.7152 0.0638
-3.000 -0.0073 0.00986 0.00269 -0.0328 0.7080 0.0959
-2.750 0.0189 0.00952 0.00253 -0.0325 0.7014 0.1470
-2.500 0.0452 0.00920 0.00244 -0.0322 0.6951 0.2133
-2.250 0.0717 0.00893 0.00237 -0.0319 0.6882 0.2729
-2.000 0.0980 0.00870 0.00229 -0.0316 0.6820 0.3330
-1.750 0.1229 0.00825 0.00221 -0.0311 0.6745 0.4341
-1.500 0.1361 0.00701 0.00212 -0.0282 0.6679 0.7489
-1.250 0.1589 0.00682 0.00233 -0.0262 0.6605 0.8949
-1.000 0.1879 0.00690 0.00240 -0.0259 0.6530 0.9274
-0.750 0.2203 0.00703 0.00251 -0.0263 0.6453 0.9482
-0.500 0.2576 0.00721 0.00262 -0.0278 0.6369 0.9632
-0.250 0.3069 0.00741 0.00276 -0.0320 0.6275 0.9739
0.000 0.3493 0.00757 0.00282 -0.0349 0.6178 0.9821
0.250 0.4004 0.00765 0.00284 -0.0398 0.6058 0.9876
0.500 0.4446 0.00773 0.00286 -0.0433 0.5940 0.9940
0.750 0.4905 0.00775 0.00281 -0.0473 0.5812 0.9980
1.000 0.5259 0.00778 0.00277 -0.0491 0.5681 1.0000
1.250 0.5519 0.00783 0.00275 -0.0488 0.5544 1.0000
1.500 0.5778 0.00788 0.00275 -0.0486 0.5388 1.0000
1.750 0.6036 0.00796 0.00276 -0.0484 0.5217 1.0000
2.000 0.6292 0.00805 0.00278 -0.0482 0.5032 1.0000
2.250 0.6545 0.00818 0.00282 -0.0479 0.4819 1.0000
2.500 0.6795 0.00835 0.00288 -0.0476 0.4568 1.0000
2.750 0.7039 0.00857 0.00297 -0.0472 0.4308 1.0000
3.000 0.7280 0.00878 0.00307 -0.0467 0.4079 1.0000
3.250 0.7517 0.00900 0.00320 -0.0462 0.3892 1.0000
3.500 0.7754 0.00921 0.00334 -0.0457 0.3747 1.0000
3.750 0.7989 0.00941 0.00349 -0.0451 0.3630 1.0000
4.000 0.8219 0.00963 0.00365 -0.0444 0.3523 1.0000
4.250 0.8452 0.00981 0.00382 -0.0438 0.3438 1.0000
4.500 0.8682 0.01001 0.00400 -0.0431 0.3368 1.0000
4.750 0.8913 0.01018 0.00418 -0.0425 0.3296 1.0000
5.000 0.9136 0.01042 0.00438 -0.0417 0.3224 1.0000
5.250 0.9369 0.01057 0.00457 -0.0410 0.3152 1.0000
5.500 0.9588 0.01083 0.00479 -0.0402 0.3082 1.0000
5.750 0.9822 0.01097 0.00497 -0.0396 0.3006 1.0000
6.000 1.0040 0.01122 0.00520 -0.0388 0.2913 1.0000
6.250 1.0270 0.01139 0.00539 -0.0381 0.2809 1.0000
6.500 1.0495 0.01160 0.00560 -0.0374 0.2693 1.0000
6.750 1.0717 0.01184 0.00583 -0.0367 0.2560 1.0000
7.000 1.0934 0.01212 0.00607 -0.0360 0.2402 1.0000
7.250 1.1140 0.01248 0.00635 -0.0350 0.2193 1.0000
7.500 1.1330 0.01298 0.00672 -0.0339 0.1924 1.0000
7.750 1.1500 0.01365 0.00723 -0.0326 0.1647 1.0000
8.000 1.1673 0.01430 0.00778 -0.0313 0.1436 1.0000
8.250 1.1854 0.01491 0.00831 -0.0302 0.1268 1.0000
8.500 1.2038 0.01550 0.00885 -0.0292 0.1136 1.0000
8.750 1.2223 0.01608 0.00939 -0.0282 0.1035 1.0000
9.250 1.2587 0.01723 0.01051 -0.0262 0.0865 1.0000
9.500 1.2763 0.01782 0.01109 -0.0252 0.0785 1.0000
9.750 1.2919 0.01851 0.01174 -0.0239 0.0675 1.0000
10.000 1.3022 0.01942 0.01254 -0.0219 0.0508 1.0000
10.250 1.3030 0.02084 0.01378 -0.0188 0.0287 1.0000
10.500 1.3087 0.02210 0.01503 -0.0166 0.0234 1.0000
10.750 1.3164 0.02333 0.01631 -0.0149 0.0214 1.0000
11.000 1.3231 0.02473 0.01778 -0.0135 0.0199 1.0000
11.250 1.3317 0.02607 0.01922 -0.0124 0.0191 1.0000
11.500 1.3386 0.02765 0.02089 -0.0115 0.0182 1.0000
11.750 1.3432 0.02951 0.02284 -0.0107 0.0176 1.0000
12.000 1.3445 0.03177 0.02519 -0.0101 0.0170 1.0000
12.250 1.3417 0.03454 0.02806 -0.0095 0.0165 1.0000
12.500 1.3426 0.03703 0.03066 -0.0092 0.0162 1.0000
12.750 1.3443 0.03952 0.03325 -0.0091 0.0159 1.0000
13.000 1.3438 0.04228 0.03613 -0.0091 0.0156 1.0000
13.250 1.3419 0.04529 0.03925 -0.0092 0.0154 1.0000
13.500 1.3384 0.04854 0.04260 -0.0094 0.0151 1.0000
13.750 1.3338 0.05202 0.04619 -0.0099 0.0149 1.0000
14.000 1.3282 0.05572 0.04999 -0.0104 0.0147 1.0000
14.250 1.3219 0.05965 0.05401 -0.0112 0.0145 1.0000
14.500 1.3153 0.06375 0.05822 -0.0122 0.0143 1.0000
14.750 1.3079 0.06804 0.06260 -0.0132 0.0142 1.0000
15.000 1.3003 0.07246 0.06710 -0.0144 0.0140 1.0000
15.250 1.2926 0.07694 0.07167 -0.0156 0.0138 1.0000
15.500 1.2845 0.08146 0.07627 -0.0169 0.0137 1.0000
15.750 1.2765 0.08593 0.08080 -0.0180 0.0135 1.0000
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