NACA 11-H-09 AIRFOIL (n11h9-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 11-H-09 AIRFOIL (n11h9-il) Reynolds number: 100,000 Max Cl/Cd: 53.06 at α=8° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-n11h9-il-100000-n5.txt Download as CSV file: xf-n11h9-il-100000-n5.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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.3504 0.09772 0.09307 -0.0090 0.7614 0.0291
-7.750 -0.3502 0.09539 0.09074 -0.0114 0.7569 0.0295
-7.500 -0.3486 0.09325 0.08861 -0.0140 0.7507 0.0298
-7.250 -0.3427 0.09099 0.08627 -0.0169 0.7456 0.0301
-7.000 -0.3346 0.08876 0.08394 -0.0194 0.7415 0.0304
-6.750 -0.3230 0.08608 0.08119 -0.0216 0.7357 0.0305
-6.500 -0.3108 0.08351 0.07848 -0.0232 0.7311 0.0307
-6.250 -0.3037 0.07817 0.07315 -0.0235 0.7279 0.0312
-6.000 -0.2965 0.07309 0.06813 -0.0227 0.7232 0.0322
-5.750 -0.2863 0.06956 0.06459 -0.0224 0.7187 0.0339
-5.500 -0.2732 0.06656 0.06150 -0.0230 0.7149 0.0351
-5.250 -0.2580 0.06360 0.05843 -0.0239 0.7110 0.0366
-5.000 -0.2403 0.06062 0.05534 -0.0250 0.7059 0.0385
-4.750 -0.2209 0.05792 0.05246 -0.0258 0.7018 0.0406
-4.500 -0.1923 0.05703 0.05112 -0.0267 0.6985 0.0434
-4.250 -0.1686 0.05548 0.04918 -0.0267 0.6938 0.0438
-4.000 -0.1547 0.05042 0.04416 -0.0268 0.6899 0.0447
-3.750 -0.1395 0.04691 0.04062 -0.0263 0.6865 0.0462
-3.500 -0.1209 0.04434 0.03789 -0.0257 0.6836 0.0483
-3.250 -0.0985 0.04211 0.03549 -0.0255 0.6788 0.0510
-3.000 -0.0684 0.04201 0.03472 -0.0242 0.6746 0.0571
-2.750 -0.0513 0.03805 0.03079 -0.0238 0.6714 0.0588
-2.500 -0.0301 0.03587 0.02844 -0.0230 0.6688 0.0615
-2.250 -0.0072 0.03426 0.02665 -0.0227 0.6642 0.0746
-2.000 0.0137 0.03286 0.02512 -0.0222 0.6604 0.0996
-1.500 0.0799 0.02811 0.01909 -0.0180 0.6551 0.0297
-1.250 0.1066 0.02646 0.01718 -0.0175 0.6508 0.0292
-1.000 0.1342 0.02510 0.01554 -0.0169 0.6470 0.0291
-0.750 0.1622 0.02439 0.01448 -0.0162 0.6439 0.0307
-0.500 0.1897 0.02267 0.01261 -0.0160 0.6414 0.0335
-0.250 0.2183 0.02172 0.01153 -0.0159 0.6380 0.0347
0.000 0.2466 0.02098 0.01074 -0.0159 0.6337 0.0365
0.250 0.2736 0.02042 0.01010 -0.0156 0.6304 0.0416
0.500 0.3001 0.01976 0.00933 -0.0150 0.6277 0.0457
0.750 0.3287 0.01929 0.00870 -0.0149 0.6254 0.0524
1.000 0.3577 0.01918 0.00855 -0.0155 0.6204 0.0676
1.250 0.4893 0.01682 0.00819 -0.0371 0.6168 1.0000
1.500 0.5141 0.01695 0.00817 -0.0365 0.6137 1.0000
1.750 0.5387 0.01704 0.00810 -0.0358 0.6112 1.0000
2.000 0.5643 0.01743 0.00847 -0.0359 0.6058 1.0000
2.250 0.5892 0.01763 0.00861 -0.0355 0.6016 1.0000
2.500 0.6137 0.01771 0.00860 -0.0348 0.5983 1.0000
2.750 0.6385 0.01795 0.00882 -0.0344 0.5937 1.0000
3.000 0.6632 0.01824 0.00913 -0.0342 0.5884 1.0000
3.250 0.6878 0.01834 0.00920 -0.0335 0.5846 1.0000
3.500 0.7123 0.01844 0.00925 -0.0328 0.5813 1.0000
3.750 0.7368 0.01891 0.00982 -0.0329 0.5750 1.0000
4.000 0.7612 0.01904 0.00998 -0.0322 0.5707 1.0000
4.250 0.7858 0.01905 0.00997 -0.0314 0.5675 1.0000
4.500 0.8096 0.01957 0.01063 -0.0314 0.5603 1.0000
4.750 0.8340 0.01965 0.01077 -0.0307 0.5556 1.0000
5.000 0.8582 0.01980 0.01099 -0.0301 0.5502 1.0000
5.250 0.8819 0.02005 0.01135 -0.0296 0.5430 1.0000
5.500 0.9068 0.01989 0.01119 -0.0286 0.5383 1.0000
5.750 0.9297 0.02030 0.01182 -0.0283 0.5290 1.0000
6.000 0.9546 0.02012 0.01167 -0.0273 0.5232 1.0000
6.250 0.9772 0.02046 0.01220 -0.0269 0.5132 1.0000
6.500 1.0008 0.02056 0.01243 -0.0262 0.5045 1.0000
6.750 1.0248 0.02051 0.01253 -0.0253 0.4957 1.0000
7.000 1.0471 0.02072 0.01292 -0.0247 0.4833 1.0000
7.250 1.0697 0.02077 0.01313 -0.0238 0.4686 1.0000
7.500 1.0921 0.02076 0.01325 -0.0229 0.4515 1.0000
7.750 1.1121 0.02111 0.01383 -0.0222 0.4290 1.0000
8.000 1.1317 0.02133 0.01409 -0.0211 0.3987 1.0000
8.250 1.1467 0.02176 0.01424 -0.0195 0.3459 1.0000
8.500 1.1530 0.02310 0.01518 -0.0176 0.2881 1.0000
8.750 1.1555 0.02481 0.01664 -0.0158 0.2420 1.0000
9.000 1.1543 0.02671 0.01836 -0.0138 0.2068 1.0000
9.250 1.1473 0.02871 0.02024 -0.0111 0.1780 1.0000
9.500 1.1411 0.03065 0.02208 -0.0086 0.1547 1.0000
9.750 1.1358 0.03279 0.02411 -0.0065 0.1299 1.0000
10.000 1.1316 0.03504 0.02624 -0.0048 0.1070 1.0000
10.250 1.1282 0.03736 0.02846 -0.0033 0.0884 1.0000
10.500 1.1251 0.03976 0.03079 -0.0019 0.0743 1.0000
10.750 1.1236 0.04211 0.03313 -0.0007 0.0645 1.0000
11.000 1.1215 0.04457 0.03558 0.0003 0.0578 1.0000
11.250 1.1219 0.04686 0.03796 0.0012 0.0523 1.0000
11.500 1.1196 0.04947 0.04057 0.0020 0.0488 1.0000
11.750 1.1216 0.05168 0.04290 0.0028 0.0459 1.0000
12.000 1.1236 0.05392 0.04531 0.0036 0.0432 1.0000
12.250 1.1259 0.05618 0.04767 0.0043 0.0414 1.0000
12.500 1.1274 0.05855 0.05012 0.0050 0.0395 1.0000
12.750 1.1307 0.06071 0.05234 0.0058 0.0382 1.0000
13.000 1.1380 0.06243 0.05412 0.0071 0.0371 1.0000
13.250 1.1476 0.06410 0.05597 0.0083 0.0360 1.0000
13.500 1.1573 0.06588 0.05795 0.0094 0.0349 1.0000
13.750 1.1643 0.06807 0.06034 0.0103 0.0337 1.0000
14.000 1.1677 0.07065 0.06312 0.0106 0.0323 1.0000
14.250 1.1687 0.07355 0.06618 0.0106 0.0308 1.0000
14.500 1.1698 0.07651 0.06933 0.0106 0.0298 1.0000
14.750 1.1703 0.07965 0.07261 0.0107 0.0289 1.0000
15.000 1.1697 0.08310 0.07619 0.0107 0.0279 1.0000
15.250 1.1630 0.08753 0.08082 0.0102 0.0272 1.0000
15.500 1.1514 0.09254 0.08611 0.0085 0.0266 1.0000
15.750 1.1386 0.09800 0.09183 0.0064 0.0261 1.0000
16.000 1.1243 0.10400 0.09807 0.0039 0.0257 1.0000
16.250 1.1086 0.11055 0.10485 0.0011 0.0255 1.0000
16.500 1.0917 0.11766 0.11216 -0.0024 0.0254 1.0000
16.750 1.0726 0.12567 0.12037 -0.0067 0.0254 1.0000
17.000 1.0527 0.13433 0.12920 -0.0115 0.0256 1.0000
17.250 1.0305 0.14424 0.13923 -0.0171 0.0260 1.0000
17.500 1.0087 0.15485 0.14988 -0.0232 0.0266 1.0000
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Polar data table (+)
Polar graphs
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