NACA 11-H-09 AIRFOIL (n11h9-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 11-H-09 AIRFOIL (n11h9-il) Reynolds number: 500,000 Max Cl/Cd: 114.54 at α=6.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-n11h9-il-500000.txt Download as CSV file: xf-n11h9-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 11-H-09 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
------ -------- --------- --------- -------- -------- --------
-7.750 -0.3768 0.08829 0.08529 -0.0037 0.6986 0.0098
-7.500 -0.3770 0.08545 0.08247 -0.0046 0.6939 0.0100
-7.250 -0.3767 0.08275 0.07978 -0.0053 0.6893 0.0102
-7.000 -0.3719 0.07968 0.07666 -0.0069 0.6852 0.0106
-6.750 -0.3649 0.07654 0.07349 -0.0086 0.6814 0.0107
-6.500 -0.3559 0.07326 0.07019 -0.0104 0.6770 0.0112
-6.250 -0.3451 0.06998 0.06686 -0.0120 0.6730 0.0116
-6.000 -0.3319 0.06669 0.06347 -0.0136 0.6694 0.0121
-5.750 -0.3078 0.06370 0.06033 -0.0167 0.6654 0.0127
-5.500 -0.2895 0.06044 0.05696 -0.0177 0.6613 0.0127
-5.250 -0.2717 0.05733 0.05374 -0.0181 0.6575 0.0128
-5.000 -0.2533 0.05420 0.05046 -0.0182 0.6541 0.0128
-4.750 -0.2437 0.04971 0.04593 -0.0182 0.6506 0.0131
-4.500 -0.2277 0.04694 0.04310 -0.0181 0.6467 0.0133
-4.250 -0.2091 0.04435 0.04040 -0.0179 0.6432 0.0136
-4.000 -0.1892 0.04187 0.03777 -0.0176 0.6400 0.0141
-3.750 -0.1679 0.03936 0.03514 -0.0172 0.6366 0.0147
-3.500 -0.1454 0.03691 0.03254 -0.0165 0.6329 0.0153
-3.250 -0.1194 0.03461 0.03003 -0.0155 0.6295 0.0166
-3.000 -0.0900 0.03299 0.02810 -0.0139 0.6264 0.0172
-2.750 -0.0704 0.02949 0.02431 -0.0123 0.6235 0.0175
-2.500 -0.0518 0.02709 0.02186 -0.0118 0.6201 0.0183
-2.250 -0.0292 0.02551 0.02016 -0.0111 0.6168 0.0194
-2.000 -0.0035 0.02400 0.01843 -0.0099 0.6138 0.0219
-1.750 0.0268 0.02398 0.01802 -0.0083 0.6110 0.0234
-1.500 0.0452 0.02041 0.01435 -0.0075 0.6082 0.0256
-1.250 0.0706 0.01941 0.01324 -0.0069 0.6048 0.0283
-1.000 0.1003 0.01983 0.01342 -0.0060 0.6015 0.0320
-0.750 0.1236 0.01688 0.01018 -0.0049 0.5989 0.0340
-0.500 0.1498 0.01579 0.00902 -0.0046 0.5963 0.0362
-0.250 0.1771 0.01501 0.00810 -0.0041 0.5935 0.0394
0.000 0.2090 0.01297 0.00566 -0.0029 0.5906 0.0240
0.250 0.2361 0.01217 0.00488 -0.0028 0.5876 0.0266
0.500 0.2627 0.01149 0.00414 -0.0022 0.5849 0.0267
0.750 0.2885 0.01102 0.00362 -0.0016 0.5822 0.0277
1.000 0.3142 0.01074 0.00330 -0.0010 0.5794 0.0302
1.250 0.3396 0.01039 0.00296 -0.0004 0.5759 0.0344
1.500 0.3656 0.01014 0.00271 0.0001 0.5719 0.0403
1.750 0.3916 0.00993 0.00245 0.0006 0.5685 0.0556
2.000 0.5561 0.00804 0.00283 -0.0299 0.5637 1.0000
2.250 0.5819 0.00807 0.00284 -0.0295 0.5602 1.0000
2.500 0.6077 0.00810 0.00284 -0.0292 0.5569 1.0000
2.750 0.6334 0.00815 0.00285 -0.0288 0.5538 1.0000
3.000 0.6591 0.00824 0.00289 -0.0284 0.5506 1.0000
3.250 0.6850 0.00826 0.00296 -0.0281 0.5466 1.0000
3.500 0.7108 0.00829 0.00298 -0.0278 0.5422 1.0000
3.750 0.7365 0.00834 0.00300 -0.0274 0.5381 1.0000
4.000 0.7623 0.00839 0.00308 -0.0271 0.5336 1.0000
4.250 0.7881 0.00841 0.00314 -0.0268 0.5284 1.0000
4.500 0.8138 0.00847 0.00318 -0.0264 0.5238 1.0000
4.750 0.8396 0.00853 0.00328 -0.0261 0.5189 1.0000
5.000 0.8654 0.00856 0.00336 -0.0258 0.5134 1.0000
5.250 0.8910 0.00864 0.00345 -0.0255 0.5082 1.0000
5.500 0.9168 0.00865 0.00355 -0.0252 0.5002 1.0000
5.750 0.9422 0.00869 0.00360 -0.0248 0.4903 1.0000
6.000 0.9676 0.00872 0.00365 -0.0245 0.4771 1.0000
6.250 0.9930 0.00879 0.00377 -0.0242 0.4630 1.0000
6.500 1.0183 0.00889 0.00389 -0.0239 0.4417 1.0000
6.750 1.0425 0.00914 0.00406 -0.0235 0.4088 1.0000
7.000 1.0654 0.00964 0.00439 -0.0231 0.3653 1.0000
7.250 1.0870 0.01035 0.00493 -0.0227 0.3195 1.0000
7.500 1.1079 0.01117 0.00556 -0.0223 0.2740 1.0000
7.750 1.1273 0.01219 0.00632 -0.0219 0.2218 1.0000
8.000 1.1450 0.01336 0.00722 -0.0214 0.1684 1.0000
8.250 1.1599 0.01478 0.00832 -0.0207 0.1114 1.0000
8.500 1.1696 0.01662 0.00978 -0.0197 0.0539 1.0000
8.750 1.1814 0.01799 0.01104 -0.0185 0.0347 1.0000
9.000 1.1938 0.01921 0.01230 -0.0174 0.0297 1.0000
9.250 1.2061 0.02027 0.01344 -0.0163 0.0278 1.0000
9.500 1.2148 0.02145 0.01471 -0.0148 0.0266 1.0000
9.750 1.2119 0.02275 0.01608 -0.0116 0.0257 1.0000
10.000 1.2094 0.02424 0.01763 -0.0088 0.0247 1.0000
10.250 1.2096 0.02585 0.01931 -0.0067 0.0241 1.0000
10.500 1.2066 0.02788 0.02143 -0.0047 0.0233 1.0000
10.750 1.2020 0.03017 0.02381 -0.0028 0.0224 1.0000
11.000 1.2077 0.03170 0.02543 -0.0016 0.0221 1.0000
11.250 1.2128 0.03330 0.02712 -0.0004 0.0216 1.0000
11.500 1.2166 0.03507 0.02897 0.0007 0.0211 1.0000
11.750 1.2207 0.03684 0.03083 0.0018 0.0206 1.0000
12.000 1.2257 0.03857 0.03264 0.0027 0.0197 1.0000
12.250 1.2297 0.04040 0.03455 0.0036 0.0192 1.0000
12.500 1.2337 0.04227 0.03649 0.0044 0.0185 1.0000
12.750 1.2369 0.04425 0.03852 0.0053 0.0180 1.0000
13.000 1.2391 0.04635 0.04069 0.0061 0.0174 1.0000
13.250 1.2384 0.04867 0.04309 0.0078 0.0165 1.0000
13.500 1.2413 0.05080 0.04534 0.0093 0.0159 1.0000
13.750 1.2464 0.05285 0.04751 0.0092 0.0155 1.0000
14.000 1.2506 0.05504 0.04982 0.0094 0.0149 1.0000
14.250 1.2535 0.05738 0.05229 0.0098 0.0145 1.0000
14.500 1.2562 0.05983 0.05484 0.0099 0.0139 1.0000
14.750 1.2577 0.06249 0.05758 0.0094 0.0132 1.0000
15.000 1.2581 0.06529 0.06047 0.0093 0.0128 1.0000
15.250 1.2575 0.06824 0.06352 0.0092 0.0125 1.0000
15.500 1.2526 0.07167 0.06701 0.0095 0.0116 1.0000
15.750 1.2423 0.07610 0.07164 0.0095 0.0113 1.0000
16.000 1.2386 0.07992 0.07561 0.0081 0.0110 1.0000
16.250 1.2335 0.08410 0.07996 0.0066 0.0106 1.0000
16.500 1.2248 0.08883 0.08486 0.0054 0.0104 1.0000
16.750 1.2177 0.09342 0.08960 0.0037 0.0102 1.0000
17.000 1.2060 0.09893 0.09527 0.0019 0.0101 1.0000
17.250 1.1946 0.10460 0.10110 -0.0004 0.0098 1.0000
17.500 1.1836 0.11036 0.10701 -0.0029 0.0097 1.0000
17.750 1.1726 0.11627 0.11305 -0.0056 0.0095 1.0000
18.000 1.1700 0.12074 0.11757 -0.0080 0.0091 1.0000
18.250 1.1462 0.12963 0.12667 -0.0121 0.0092 1.0000
18.500 1.1237 0.13878 0.13602 -0.0168 0.0093 1.0000
18.750 1.1029 0.14801 0.14541 -0.0218 0.0094 1.0000
19.000 1.0803 0.15833 0.15588 -0.0276 0.0095 1.0000
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