NACA 8-H-12 AIRFOIL (n8h12-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 8-H-12 AIRFOIL (n8h12-il) Reynolds number: 200,000 Max Cl/Cd: 71.17 at α=7.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-n8h12-il-200000-n5.txt Download as CSV file: xf-n8h12-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.5066 0.08922 0.08542 0.0037 0.7239 0.0190
-9.000 -0.5040 0.08610 0.08230 0.0020 0.7166 0.0196
-8.750 -0.5156 0.08016 0.07637 -0.0022 0.7108 0.0193
-8.500 -0.5260 0.07537 0.07157 -0.0058 0.7047 0.0195
-8.250 -0.5369 0.07011 0.06624 -0.0084 0.6987 0.0196
-8.000 -0.5431 0.06438 0.06037 -0.0108 0.6936 0.0198
-7.750 -0.5462 0.05842 0.05422 -0.0124 0.6884 0.0199
-7.500 -0.5470 0.05217 0.04769 -0.0130 0.6831 0.0201
-7.250 -0.5478 0.04496 0.04003 -0.0126 0.6787 0.0200
-7.000 -0.5438 0.03865 0.03317 -0.0114 0.6741 0.0204
-6.750 -0.5351 0.03325 0.02712 -0.0097 0.6684 0.0210
-6.500 -0.5224 0.02867 0.02165 -0.0076 0.6631 0.0223
-6.250 -0.5015 0.02690 0.01958 -0.0068 0.6569 0.0232
-6.000 -0.4784 0.02567 0.01816 -0.0062 0.6501 0.0239
-5.750 -0.4551 0.02426 0.01646 -0.0054 0.6446 0.0246
-5.500 -0.4306 0.02281 0.01471 -0.0048 0.6381 0.0255
-5.250 -0.4054 0.02160 0.01315 -0.0041 0.6320 0.0269
-5.000 -0.3800 0.02051 0.01183 -0.0036 0.6262 0.0282
-4.750 -0.3540 0.01969 0.01094 -0.0032 0.6194 0.0292
-4.500 -0.3279 0.01891 0.01002 -0.0028 0.6138 0.0302
-4.250 -0.3014 0.01817 0.00916 -0.0024 0.6077 0.0315
-4.000 -0.2746 0.01759 0.00843 -0.0020 0.6019 0.0333
-3.750 -0.2490 0.01688 0.00764 -0.0015 0.5969 0.0348
-3.500 -0.2226 0.01633 0.00708 -0.0012 0.5907 0.0362
-3.250 -0.1964 0.01584 0.00653 -0.0007 0.5848 0.0378
-3.000 -0.1701 0.01547 0.00604 -0.0003 0.5798 0.0403
-2.750 -0.1440 0.01501 0.00559 0.0001 0.5739 0.0429
-2.500 -0.1176 0.01467 0.00520 0.0005 0.5687 0.0458
-2.250 -0.0912 0.01439 0.00480 0.0009 0.5645 0.0497
-2.000 -0.0645 0.01407 0.00453 0.0012 0.5590 0.0571
-1.750 -0.0379 0.01379 0.00426 0.0015 0.5539 0.0709
-1.500 -0.0117 0.01351 0.00400 0.0019 0.5495 0.0929
-1.250 0.0144 0.01319 0.00382 0.0022 0.5444 0.1329
-1.000 0.0387 0.01266 0.00367 0.0027 0.5396 0.2352
-0.750 0.0544 0.01143 0.00350 0.0046 0.5357 0.5186
-0.500 0.1403 0.01057 0.00386 -0.0058 0.5305 0.9356
-0.250 0.1842 0.01079 0.00398 -0.0086 0.5256 0.9654
0.000 0.2652 0.01097 0.00395 -0.0193 0.5202 0.9973
0.250 0.2977 0.01099 0.00383 -0.0204 0.5165 1.0000
0.500 0.3232 0.01101 0.00380 -0.0200 0.5121 1.0000
0.750 0.3486 0.01104 0.00378 -0.0196 0.5081 1.0000
1.000 0.3741 0.01109 0.00374 -0.0192 0.5047 1.0000
1.250 0.3995 0.01117 0.00372 -0.0188 0.5018 1.0000
1.500 0.4253 0.01124 0.00377 -0.0185 0.4983 1.0000
1.750 0.4510 0.01132 0.00383 -0.0182 0.4947 1.0000
2.000 0.4767 0.01141 0.00388 -0.0178 0.4912 1.0000
2.250 0.5023 0.01151 0.00392 -0.0175 0.4881 1.0000
2.500 0.5279 0.01163 0.00398 -0.0171 0.4853 1.0000
2.750 0.5539 0.01174 0.00414 -0.0168 0.4820 1.0000
3.000 0.5798 0.01187 0.00428 -0.0166 0.4789 1.0000
3.250 0.6056 0.01201 0.00441 -0.0162 0.4759 1.0000
3.500 0.6313 0.01214 0.00453 -0.0159 0.4730 1.0000
3.750 0.6569 0.01230 0.00465 -0.0155 0.4705 1.0000
4.000 0.6829 0.01246 0.00487 -0.0153 0.4674 1.0000
4.250 0.7087 0.01264 0.00511 -0.0151 0.4644 1.0000
4.500 0.7345 0.01281 0.00532 -0.0148 0.4613 1.0000
4.750 0.7602 0.01298 0.00551 -0.0145 0.4584 1.0000
5.000 0.7858 0.01317 0.00571 -0.0142 0.4559 1.0000
5.250 0.8115 0.01338 0.00597 -0.0139 0.4531 1.0000
5.500 0.8372 0.01359 0.00629 -0.0137 0.4494 1.0000
5.750 0.8627 0.01377 0.00655 -0.0134 0.4452 1.0000
6.000 0.8881 0.01390 0.00669 -0.0130 0.4406 1.0000
6.250 0.9134 0.01409 0.00697 -0.0127 0.4352 1.0000
6.500 0.9386 0.01421 0.00719 -0.0124 0.4281 1.0000
6.750 0.9635 0.01429 0.00732 -0.0120 0.4180 1.0000
7.000 0.9882 0.01436 0.00741 -0.0116 0.4062 1.0000
7.250 1.0127 0.01449 0.00760 -0.0112 0.3935 1.0000
7.500 1.0369 0.01466 0.00783 -0.0109 0.3775 1.0000
7.750 1.0605 0.01490 0.00813 -0.0105 0.3546 1.0000
8.000 1.0827 0.01527 0.00846 -0.0101 0.3227 1.0000
8.250 1.0994 0.01621 0.00910 -0.0094 0.2626 1.0000
8.500 1.1084 0.01787 0.01040 -0.0083 0.2015 1.0000
8.750 1.1149 0.01954 0.01183 -0.0069 0.1564 1.0000
9.000 1.1184 0.02121 0.01333 -0.0053 0.1226 1.0000
9.250 1.1188 0.02296 0.01498 -0.0036 0.0996 1.0000
9.500 1.1122 0.02471 0.01669 -0.0009 0.0851 1.0000
9.750 1.1074 0.02666 0.01859 0.0010 0.0720 1.0000
10.000 1.1057 0.02867 0.02057 0.0024 0.0620 1.0000
10.250 1.1057 0.03071 0.02261 0.0034 0.0548 1.0000
10.750 1.1066 0.03499 0.02694 0.0050 0.0443 1.0000
11.000 1.1067 0.03727 0.02925 0.0055 0.0411 1.0000
11.250 1.1078 0.03953 0.03157 0.0060 0.0384 1.0000
11.500 1.1094 0.04178 0.03391 0.0064 0.0361 1.0000
11.750 1.1098 0.04419 0.03636 0.0067 0.0343 1.0000
12.000 1.1083 0.04684 0.03905 0.0069 0.0329 1.0000
12.250 1.1091 0.04930 0.04158 0.0071 0.0319 1.0000
12.500 1.1113 0.05169 0.04407 0.0072 0.0309 1.0000
12.750 1.1135 0.05415 0.04660 0.0072 0.0298 1.0000
13.000 1.1157 0.05664 0.04916 0.0072 0.0287 1.0000
13.250 1.1181 0.05915 0.05175 0.0070 0.0280 1.0000
13.500 1.1195 0.06180 0.05444 0.0069 0.0272 1.0000
13.750 1.1198 0.06459 0.05726 0.0067 0.0265 1.0000
14.000 1.1234 0.06703 0.05977 0.0067 0.0259 1.0000
14.250 1.1277 0.06939 0.06222 0.0066 0.0254 1.0000
14.500 1.1319 0.07176 0.06468 0.0065 0.0249 1.0000
14.750 1.1367 0.07409 0.06709 0.0064 0.0244 1.0000
15.000 1.1414 0.07643 0.06952 0.0064 0.0240 1.0000
15.250 1.1459 0.07884 0.07202 0.0062 0.0235 1.0000
15.500 1.1506 0.08121 0.07446 0.0060 0.0231 1.0000
15.750 1.1551 0.08364 0.07696 0.0058 0.0227 1.0000
16.000 1.1590 0.08623 0.07962 0.0054 0.0223 1.0000
16.250 1.1632 0.08872 0.08216 0.0051 0.0219 1.0000
16.500 1.1676 0.09117 0.08466 0.0049 0.0215 1.0000
16.750 1.1701 0.09396 0.08754 0.0044 0.0210 1.0000
17.000 1.1720 0.09701 0.09074 0.0037 0.0208 1.0000
17.250 1.1726 0.10033 0.09422 0.0029 0.0205 1.0000
17.500 1.1720 0.10389 0.09794 0.0018 0.0202 1.0000
17.750 1.1706 0.10763 0.10184 0.0006 0.0200 1.0000
18.000 1.1674 0.11174 0.10611 -0.0009 0.0198 1.0000
18.250 1.1628 0.11621 0.11074 -0.0027 0.0196 1.0000
18.500 1.1568 0.12101 0.11572 -0.0047 0.0194 1.0000
18.750 1.1492 0.12627 0.12115 -0.0073 0.0192 1.0000
19.000 1.1395 0.13205 0.12711 -0.0101 0.0190 1.0000
19.250 1.1282 0.13834 0.13357 -0.0135 0.0189 1.0000
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