NACA 8-H-12 AIRFOIL (n8h12-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 8-H-12 AIRFOIL (n8h12-il) Reynolds number: 100,000 Max Cl/Cd: 47.95 at α=8.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-n8h12-il-100000-n5.txt Download as CSV file: xf-n8h12-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 8-H-12 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
------ -------- --------- --------- -------- -------- --------
-9.250 -0.4719 0.09659 0.09204 -0.0021 0.7926 0.0419
-8.750 -0.4920 0.08258 0.07801 -0.0127 0.7778 0.0335
-8.500 -0.4932 0.07905 0.07444 -0.0137 0.7701 0.0333
-8.250 -0.4966 0.07510 0.07044 -0.0150 0.7620 0.0330
-8.000 -0.4994 0.07058 0.06580 -0.0166 0.7557 0.0327
-7.750 -0.5007 0.06558 0.06066 -0.0183 0.7481 0.0327
-7.500 -0.5036 0.05975 0.05452 -0.0194 0.7424 0.0331
-7.250 -0.5016 0.05444 0.04886 -0.0198 0.7358 0.0332
-7.000 -0.4973 0.04941 0.04337 -0.0192 0.7293 0.0334
-6.750 -0.4885 0.04530 0.03881 -0.0181 0.7237 0.0335
-6.500 -0.4764 0.04134 0.03433 -0.0171 0.7163 0.0336
-6.250 -0.4611 0.03849 0.03116 -0.0160 0.7101 0.0341
-6.000 -0.4410 0.03686 0.02938 -0.0155 0.7028 0.0351
-5.750 -0.4210 0.03516 0.02742 -0.0146 0.6959 0.0367
-5.500 -0.4010 0.03285 0.02464 -0.0134 0.6899 0.0382
-5.250 -0.3790 0.03045 0.02174 -0.0124 0.6828 0.0391
-5.000 -0.3561 0.02841 0.01917 -0.0112 0.6772 0.0401
-4.750 -0.3313 0.02686 0.01732 -0.0107 0.6700 0.0419
-4.500 -0.3063 0.02587 0.01620 -0.0102 0.6636 0.0441
-4.250 -0.2803 0.02467 0.01477 -0.0096 0.6578 0.0458
-4.000 -0.2533 0.02352 0.01340 -0.0092 0.6509 0.0475
-3.750 -0.2270 0.02260 0.01224 -0.0085 0.6455 0.0502
-3.500 -0.2007 0.02177 0.01144 -0.0083 0.6388 0.0532
-3.250 -0.1746 0.02101 0.01059 -0.0078 0.6327 0.0559
-3.000 -0.1491 0.02032 0.00975 -0.0070 0.6280 0.0591
-2.750 -0.1233 0.01972 0.00919 -0.0067 0.6213 0.0642
-2.500 -0.0979 0.01924 0.00861 -0.0060 0.6160 0.0712
-2.250 -0.0733 0.01868 0.00800 -0.0053 0.6112 0.0798
-2.000 -0.0474 0.01820 0.00757 -0.0049 0.6048 0.0975
-1.750 -0.0223 0.01765 0.00716 -0.0043 0.5998 0.1352
-1.500 0.0015 0.01670 0.00682 -0.0038 0.5955 0.2827
-1.250 0.0937 0.01493 0.00717 -0.0145 0.5885 0.9345
-1.000 0.1651 0.01514 0.00704 -0.0225 0.5831 0.9896
-0.750 0.2078 0.01512 0.00679 -0.0256 0.5782 1.0000
-0.500 0.2327 0.01518 0.00673 -0.0253 0.5726 1.0000
-0.250 0.2571 0.01523 0.00662 -0.0248 0.5682 1.0000
0.000 0.2813 0.01529 0.00650 -0.0241 0.5648 1.0000
0.250 0.3068 0.01544 0.00659 -0.0240 0.5598 1.0000
0.500 0.3319 0.01557 0.00663 -0.0236 0.5553 1.0000
0.750 0.3565 0.01568 0.00662 -0.0231 0.5515 1.0000
1.000 0.3811 0.01579 0.00660 -0.0225 0.5482 1.0000
1.250 0.4068 0.01601 0.00682 -0.0224 0.5431 1.0000
1.500 0.4320 0.01619 0.00695 -0.0221 0.5391 1.0000
1.750 0.4569 0.01635 0.00704 -0.0216 0.5359 1.0000
2.000 0.4817 0.01651 0.00711 -0.0210 0.5332 1.0000
2.250 0.5073 0.01682 0.00745 -0.0210 0.5288 1.0000
2.500 0.5325 0.01708 0.00771 -0.0207 0.5246 1.0000
2.750 0.5575 0.01729 0.00791 -0.0203 0.5211 1.0000
3.000 0.5823 0.01748 0.00805 -0.0198 0.5184 1.0000
3.250 0.6074 0.01780 0.00838 -0.0195 0.5153 1.0000
3.500 0.6326 0.01820 0.00887 -0.0195 0.5111 1.0000
3.750 0.6575 0.01851 0.00921 -0.0192 0.5074 1.0000
4.000 0.6823 0.01876 0.00947 -0.0187 0.5044 1.0000
4.250 0.7071 0.01899 0.00970 -0.0182 0.5021 1.0000
4.500 0.7316 0.01950 0.01033 -0.0181 0.4981 1.0000
4.750 0.7559 0.01997 0.01090 -0.0180 0.4939 1.0000
5.000 0.7804 0.02031 0.01132 -0.0176 0.4906 1.0000
5.250 0.8050 0.02059 0.01163 -0.0171 0.4878 1.0000
5.500 0.8295 0.02091 0.01201 -0.0166 0.4848 1.0000
5.750 0.8522 0.02162 0.01292 -0.0166 0.4796 1.0000
6.000 0.8760 0.02200 0.01341 -0.0162 0.4754 1.0000
6.250 0.9008 0.02214 0.01359 -0.0155 0.4719 1.0000
6.500 0.9235 0.02263 0.01422 -0.0151 0.4663 1.0000
6.750 0.9463 0.02301 0.01476 -0.0146 0.4602 1.0000
7.000 0.9717 0.02295 0.01474 -0.0138 0.4558 1.0000
7.250 0.9926 0.02344 0.01542 -0.0133 0.4472 1.0000
7.500 1.0193 0.02290 0.01488 -0.0122 0.4393 1.0000
7.750 1.0405 0.02290 0.01502 -0.0113 0.4257 1.0000
8.000 1.0618 0.02285 0.01510 -0.0104 0.4114 1.0000
8.250 1.0824 0.02289 0.01527 -0.0095 0.3958 1.0000
8.500 1.1020 0.02298 0.01544 -0.0084 0.3775 1.0000
8.750 1.1167 0.02356 0.01619 -0.0074 0.3530 1.0000
9.000 1.1294 0.02418 0.01683 -0.0062 0.3197 1.0000
9.250 1.1350 0.02520 0.01761 -0.0043 0.2687 1.0000
9.500 1.1257 0.02731 0.01940 -0.0020 0.2248 1.0000
9.750 1.1083 0.02989 0.02180 0.0008 0.1993 1.0000
10.000 1.0925 0.03296 0.02472 0.0024 0.1754 1.0000
10.250 1.0788 0.03624 0.02789 0.0035 0.1521 1.0000
10.500 1.0660 0.03969 0.03121 0.0041 0.1321 1.0000
10.750 1.0555 0.04307 0.03450 0.0045 0.1142 1.0000
11.000 1.0470 0.04637 0.03772 0.0048 0.0994 1.0000
11.250 1.0404 0.04954 0.04084 0.0050 0.0873 1.0000
11.500 1.0351 0.05264 0.04390 0.0052 0.0776 1.0000
11.750 1.0310 0.05566 0.04688 0.0053 0.0701 1.0000
12.000 1.0304 0.05839 0.04964 0.0054 0.0641 1.0000
12.250 1.0289 0.06126 0.05250 0.0054 0.0598 1.0000
12.500 1.0307 0.06377 0.05506 0.0056 0.0561 1.0000
12.750 1.0339 0.06615 0.05750 0.0057 0.0524 1.0000
13.000 1.0357 0.06870 0.06004 0.0058 0.0494 1.0000
13.250 1.0418 0.07069 0.06210 0.0061 0.0471 1.0000
13.500 1.0483 0.07267 0.06416 0.0064 0.0446 1.0000
13.750 1.0552 0.07462 0.06616 0.0067 0.0427 1.0000
14.000 1.0625 0.07648 0.06805 0.0071 0.0412 1.0000
14.250 1.0729 0.07777 0.06931 0.0080 0.0399 1.0000
14.500 1.0834 0.07933 0.07103 0.0086 0.0387 1.0000
14.750 1.0931 0.08108 0.07292 0.0092 0.0376 1.0000
15.000 1.1010 0.08314 0.07511 0.0094 0.0365 1.0000
15.250 1.1066 0.08557 0.07765 0.0093 0.0353 1.0000
15.500 1.1119 0.08804 0.08022 0.0091 0.0344 1.0000
15.750 1.1176 0.09045 0.08268 0.0089 0.0335 1.0000
16.000 1.1257 0.09251 0.08478 0.0092 0.0327 1.0000
16.250 1.1269 0.09587 0.08832 0.0086 0.0323 1.0000
16.500 1.1243 0.09992 0.09260 0.0074 0.0320 1.0000
16.750 1.1184 0.10457 0.09750 0.0058 0.0316 1.0000
17.000 1.1107 0.10963 0.10278 0.0039 0.0315 1.0000
17.250 1.0991 0.11553 0.10892 0.0012 0.0312 1.0000
17.500 1.0846 0.12218 0.11581 -0.0021 0.0311 1.0000
17.750 1.0680 0.12952 0.12337 -0.0060 0.0311 1.0000
18.000 1.0462 0.13837 0.13244 -0.0110 0.0312 1.0000
18.250 1.0182 0.14939 0.14366 -0.0176 0.0314 1.0000
18.500 0.9812 0.16411 0.15855 -0.0264 0.0318 1.0000
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