NACA CYH (nacacyh-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: NACA CYH (nacacyh-il) Reynolds number: 1,000,000 Max Cl/Cd: 110.41 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-nacacyh-il-1000000.txt Download as CSV file: xf-nacacyh-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.500 -0.9895 0.04458 0.04221 -0.0614 1.0000 0.0174
-14.250 -1.0079 0.04010 0.03752 -0.0627 1.0000 0.0175
-14.000 -1.0135 0.03766 0.03490 -0.0615 1.0000 0.0176
-13.750 -1.0127 0.03599 0.03309 -0.0594 1.0000 0.0177
-13.500 -1.0338 0.03146 0.02820 -0.0564 1.0000 0.0181
-13.250 -1.0202 0.03030 0.02698 -0.0551 1.0000 0.0184
-13.000 -1.0014 0.02970 0.02636 -0.0540 1.0000 0.0186
-12.750 -0.9817 0.02917 0.02579 -0.0530 1.0000 0.0188
-12.500 -0.9620 0.02859 0.02517 -0.0520 1.0000 0.0191
-12.250 -0.9420 0.02801 0.02454 -0.0510 1.0000 0.0194
-12.000 -0.9216 0.02743 0.02391 -0.0499 1.0000 0.0198
-11.750 -0.9024 0.02665 0.02304 -0.0488 1.0000 0.0202
-11.500 -0.8841 0.02570 0.02195 -0.0475 1.0000 0.0207
-11.250 -0.8657 0.02476 0.02087 -0.0462 1.0000 0.0211
-11.000 -0.8461 0.02411 0.02009 -0.0448 1.0000 0.0214
-10.750 -0.8257 0.02380 0.01968 -0.0434 1.0000 0.0216
-10.500 -0.8123 0.02076 0.01639 -0.0422 0.9972 0.0224
-10.250 -0.7791 0.02020 0.01581 -0.0435 0.9916 0.0228
-10.000 -0.7460 0.01973 0.01529 -0.0448 0.9830 0.0233
-9.750 -0.7156 0.01909 0.01459 -0.0454 0.9695 0.0238
-9.500 -0.6904 0.01844 0.01382 -0.0448 0.9483 0.0243
-9.250 -0.6685 0.01783 0.01306 -0.0434 0.9220 0.0248
-9.000 -0.6464 0.01738 0.01243 -0.0420 0.8929 0.0253
-8.750 -0.6225 0.01709 0.01198 -0.0409 0.8663 0.0257
-8.500 -0.5978 0.01685 0.01157 -0.0400 0.8444 0.0260
-8.250 -0.5747 0.01580 0.01030 -0.0391 0.8271 0.0264
-8.000 -0.5518 0.01455 0.00891 -0.0382 0.8127 0.0270
-7.750 -0.5265 0.01398 0.00827 -0.0377 0.8005 0.0276
-7.500 -0.5004 0.01361 0.00784 -0.0372 0.7902 0.0281
-7.250 -0.4742 0.01322 0.00737 -0.0367 0.7808 0.0287
-7.000 -0.4478 0.01279 0.00688 -0.0362 0.7725 0.0291
-6.750 -0.4214 0.01241 0.00642 -0.0357 0.7644 0.0296
-6.500 -0.3947 0.01202 0.00598 -0.0353 0.7568 0.0301
-6.250 -0.3680 0.01170 0.00557 -0.0349 0.7487 0.0306
-6.000 -0.3409 0.01141 0.00524 -0.0345 0.7410 0.0310
-5.750 -0.3135 0.01121 0.00498 -0.0342 0.7337 0.0314
-5.500 -0.2867 0.01085 0.00456 -0.0338 0.7275 0.0317
-5.250 -0.2609 0.01029 0.00394 -0.0333 0.7206 0.0325
-5.000 -0.2343 0.00996 0.00355 -0.0328 0.7140 0.0333
-4.750 -0.2068 0.00969 0.00326 -0.0326 0.7080 0.0341
-4.500 -0.1793 0.00948 0.00302 -0.0323 0.7015 0.0349
-4.250 -0.1516 0.00930 0.00280 -0.0321 0.6949 0.0359
-4.000 -0.1238 0.00913 0.00260 -0.0319 0.6874 0.0369
-3.750 -0.0959 0.00900 0.00244 -0.0317 0.6809 0.0378
-3.500 -0.0680 0.00880 0.00221 -0.0315 0.6749 0.0394
-3.250 -0.0402 0.00863 0.00204 -0.0314 0.6689 0.0421
-3.000 -0.0122 0.00850 0.00190 -0.0312 0.6630 0.0453
-2.750 0.0153 0.00827 0.00177 -0.0311 0.6562 0.0669
-2.500 0.0426 0.00807 0.00166 -0.0309 0.6495 0.0977
-2.250 0.0702 0.00785 0.00157 -0.0308 0.6424 0.1327
-2.000 0.0970 0.00760 0.00149 -0.0306 0.6355 0.1889
-1.750 0.1243 0.00738 0.00144 -0.0305 0.6284 0.2450
-1.500 0.1515 0.00721 0.00140 -0.0303 0.6207 0.2931
-1.250 0.1784 0.00697 0.00136 -0.0302 0.6131 0.3596
-1.000 0.2035 0.00658 0.00131 -0.0298 0.6045 0.4769
-0.750 0.2191 0.00548 0.00127 -0.0274 0.5961 0.7939
-0.500 0.2430 0.00536 0.00134 -0.0262 0.5865 0.8771
-0.250 0.2693 0.00536 0.00139 -0.0255 0.5763 0.9109
0.000 0.2963 0.00542 0.00145 -0.0251 0.5663 0.9317
0.250 0.3235 0.00552 0.00152 -0.0247 0.5554 0.9489
0.500 0.3522 0.00564 0.00161 -0.0246 0.5435 0.9623
0.750 0.3815 0.00577 0.00168 -0.0247 0.5310 0.9712
1.000 0.4166 0.00591 0.00176 -0.0262 0.5163 0.9752
1.250 0.4521 0.00609 0.00186 -0.0279 0.4991 0.9804
1.500 0.4897 0.00628 0.00196 -0.0300 0.4798 0.9837
1.750 0.5283 0.00646 0.00203 -0.0325 0.4576 0.9853
2.000 0.5645 0.00669 0.00212 -0.0346 0.4286 0.9872
2.250 0.5994 0.00695 0.00224 -0.0363 0.3966 0.9894
2.500 0.6329 0.00721 0.00236 -0.0379 0.3715 0.9919
2.750 0.6672 0.00743 0.00249 -0.0395 0.3539 0.9941
3.000 0.7040 0.00759 0.00258 -0.0417 0.3412 0.9954
3.250 0.7373 0.00772 0.00267 -0.0432 0.3310 0.9965
3.500 0.7690 0.00787 0.00278 -0.0444 0.3218 0.9975
3.750 0.8011 0.00797 0.00287 -0.0456 0.3157 0.9986
4.000 0.8330 0.00813 0.00299 -0.0468 0.3084 0.9996
4.250 0.8612 0.00822 0.00309 -0.0472 0.3026 1.0000
4.500 0.8852 0.00835 0.00320 -0.0467 0.2966 1.0000
4.750 0.9088 0.00849 0.00332 -0.0462 0.2909 1.0000
5.000 0.9326 0.00859 0.00344 -0.0456 0.2837 1.0000
5.250 0.9555 0.00876 0.00357 -0.0450 0.2748 1.0000
5.500 0.9787 0.00890 0.00370 -0.0443 0.2657 1.0000
5.750 1.0014 0.00907 0.00384 -0.0437 0.2554 1.0000
6.000 1.0236 0.00928 0.00401 -0.0429 0.2418 1.0000
6.250 1.0454 0.00953 0.00420 -0.0420 0.2263 1.0000
6.500 1.0655 0.00990 0.00445 -0.0410 0.2030 1.0000
6.750 1.0839 0.01040 0.00480 -0.0396 0.1740 1.0000
7.000 1.1023 0.01090 0.00517 -0.0383 0.1507 1.0000
7.250 1.1211 0.01138 0.00555 -0.0371 0.1320 1.0000
7.500 1.1401 0.01186 0.00593 -0.0359 0.1141 1.0000
7.750 1.1593 0.01231 0.00632 -0.0348 0.1005 1.0000
8.000 1.1792 0.01273 0.00669 -0.0338 0.0907 1.0000
8.250 1.1991 0.01319 0.00709 -0.0328 0.0817 1.0000
8.500 1.2200 0.01357 0.00746 -0.0321 0.0749 1.0000
8.750 1.2404 0.01402 0.00787 -0.0313 0.0664 1.0000
9.000 1.2584 0.01464 0.00840 -0.0302 0.0526 1.0000
9.250 1.2668 0.01597 0.00946 -0.0278 0.0217 1.0000
9.500 1.2826 0.01672 0.01021 -0.0265 0.0175 1.0000
9.750 1.2998 0.01734 0.01087 -0.0254 0.0159 1.0000
10.000 1.3165 0.01795 0.01153 -0.0242 0.0150 1.0000
10.250 1.3291 0.01865 0.01227 -0.0224 0.0142 1.0000
10.500 1.3388 0.01954 0.01322 -0.0203 0.0134 1.0000
10.750 1.3512 0.02032 0.01406 -0.0188 0.0130 1.0000
11.000 1.3639 0.02114 0.01495 -0.0176 0.0126 1.0000
11.250 1.3754 0.02210 0.01597 -0.0163 0.0122 1.0000
11.500 1.3859 0.02319 0.01713 -0.0152 0.0118 1.0000
11.750 1.3953 0.02444 0.01844 -0.0143 0.0115 1.0000
12.000 1.4027 0.02593 0.02000 -0.0134 0.0112 1.0000
12.250 1.4067 0.02782 0.02198 -0.0126 0.0109 1.0000
12.500 1.4047 0.03037 0.02464 -0.0117 0.0105 1.0000
12.750 1.4100 0.03233 0.02669 -0.0114 0.0104 1.0000
13.000 1.4171 0.03417 0.02860 -0.0113 0.0102 1.0000
13.250 1.4221 0.03625 0.03076 -0.0111 0.0100 1.0000
13.500 1.4256 0.03853 0.03313 -0.0111 0.0098 1.0000
13.750 1.4270 0.04107 0.03575 -0.0112 0.0096 1.0000
14.000 1.4269 0.04385 0.03862 -0.0113 0.0094 1.0000
14.250 1.4249 0.04690 0.04176 -0.0116 0.0093 1.0000
14.500 1.4219 0.05014 0.04509 -0.0120 0.0092 1.0000
14.750 1.4172 0.05374 0.04879 -0.0126 0.0090 1.0000
15.000 1.4113 0.05760 0.05274 -0.0134 0.0089 1.0000
15.250 1.4043 0.06177 0.05700 -0.0144 0.0088 1.0000
15.500 1.3959 0.06624 0.06158 -0.0157 0.0087 1.0000
15.750 1.3858 0.07106 0.06649 -0.0170 0.0087 1.0000
16.000 1.3746 0.07615 0.07169 -0.0186 0.0086 1.0000
16.250 1.3620 0.08157 0.07721 -0.0203 0.0085 1.0000
16.500 1.3487 0.08713 0.08287 -0.0221 0.0085 1.0000
16.750 1.3346 0.09291 0.08875 -0.0241 0.0084 1.0000
17.000 1.3203 0.09877 0.09470 -0.0261 0.0083 1.0000
17.250 1.3056 0.10466 0.10069 -0.0281 0.0082 1.0000
|
Polar data table (+)
Polar graphs
<< Back to NACA CYH (nacacyh-il)