NACA 6-H-15 AIRFOIL (n6h15-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 6-H-15 AIRFOIL (n6h15-il) Reynolds number: 500,000 Max Cl/Cd: 82.96 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-n6h15-il-500000-n5.txt Download as CSV file: xf-n6h15-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 6-H-15 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.500 -0.3064 0.10716 0.10375 -0.0141 0.6011 0.0103
-10.500 -0.8122 0.02980 0.02453 -0.0201 0.6125 0.0112
-10.250 -0.7995 0.02806 0.02256 -0.0182 0.6104 0.0115
-10.000 -0.7805 0.02726 0.02164 -0.0170 0.6083 0.0117
-9.750 -0.7603 0.02648 0.02077 -0.0161 0.6060 0.0120
-9.500 -0.7391 0.02580 0.01999 -0.0152 0.6038 0.0123
-9.250 -0.7187 0.02480 0.01883 -0.0142 0.6015 0.0127
-9.000 -0.6987 0.02352 0.01730 -0.0132 0.5994 0.0132
-8.750 -0.6778 0.02210 0.01561 -0.0122 0.5974 0.0138
-8.500 -0.6549 0.02100 0.01426 -0.0116 0.5955 0.0145
-8.250 -0.6307 0.02072 0.01394 -0.0111 0.5936 0.0149
-8.000 -0.6058 0.02057 0.01376 -0.0107 0.5918 0.0153
-7.750 -0.5809 0.02024 0.01336 -0.0103 0.5900 0.0159
-7.500 -0.5557 0.01966 0.01266 -0.0100 0.5880 0.0166
-7.250 -0.5300 0.01881 0.01162 -0.0097 0.5860 0.0174
-7.000 -0.5039 0.01813 0.01079 -0.0095 0.5840 0.0182
-6.750 -0.4785 0.01799 0.01062 -0.0092 0.5820 0.0187
-6.500 -0.4528 0.01782 0.01041 -0.0089 0.5801 0.0194
-6.250 -0.4266 0.01750 0.01001 -0.0087 0.5783 0.0203
-6.000 -0.3997 0.01706 0.00944 -0.0086 0.5766 0.0213
-5.750 -0.3723 0.01662 0.00888 -0.0086 0.5749 0.0221
-5.500 -0.3452 0.01609 0.00830 -0.0086 0.5732 0.0230
-5.250 -0.3186 0.01584 0.00805 -0.0085 0.5715 0.0238
-5.000 -0.2917 0.01557 0.00775 -0.0085 0.5698 0.0247
-4.750 -0.2643 0.01522 0.00733 -0.0085 0.5681 0.0256
-4.500 -0.2369 0.01489 0.00693 -0.0085 0.5666 0.0266
-4.250 -0.2096 0.01467 0.00664 -0.0085 0.5651 0.0275
-4.000 -0.1823 0.01416 0.00607 -0.0085 0.5637 0.0283
-3.750 -0.1557 0.01378 0.00566 -0.0084 0.5623 0.0293
-3.500 -0.1290 0.01352 0.00541 -0.0083 0.5610 0.0304
-3.250 -0.1023 0.01326 0.00514 -0.0082 0.5596 0.0313
-3.000 -0.0758 0.01300 0.00486 -0.0081 0.5579 0.0322
-2.750 -0.0495 0.01276 0.00461 -0.0079 0.5563 0.0330
-2.500 -0.0232 0.01257 0.00439 -0.0077 0.5544 0.0339
-2.250 0.0031 0.01239 0.00418 -0.0075 0.5526 0.0347
-2.000 0.0284 0.01212 0.00389 -0.0071 0.5508 0.0359
-1.750 0.0542 0.01193 0.00369 -0.0068 0.5492 0.0371
-1.500 0.0801 0.01180 0.00352 -0.0065 0.5475 0.0385
-1.250 0.1062 0.01168 0.00340 -0.0063 0.5461 0.0401
-1.000 0.1325 0.01158 0.00329 -0.0061 0.5449 0.0421
-0.750 0.1586 0.01147 0.00321 -0.0059 0.5436 0.0455
-0.500 0.1845 0.01136 0.00314 -0.0057 0.5424 0.0526
-0.250 0.2092 0.01119 0.00310 -0.0053 0.5411 0.0840
0.000 0.2344 0.01106 0.00307 -0.0049 0.5399 0.1155
0.250 0.2591 0.01092 0.00305 -0.0045 0.5386 0.1516
0.500 0.2672 0.01005 0.00297 -0.0010 0.5375 0.4151
1.000 0.2702 0.00883 0.00320 0.0102 0.5354 0.8593
1.250 0.2951 0.00904 0.00340 0.0110 0.5343 0.8765
1.500 0.3224 0.00923 0.00357 0.0112 0.5332 0.8854
1.750 0.3496 0.00942 0.00373 0.0114 0.5320 0.8930
2.000 0.3767 0.00956 0.00387 0.0115 0.5308 0.8986
2.250 0.4085 0.00975 0.00408 0.0107 0.5295 0.9031
2.500 0.4363 0.00988 0.00422 0.0106 0.5284 0.9070
2.750 0.4616 0.00995 0.00429 0.0109 0.5271 0.9099
3.000 0.4860 0.01000 0.00433 0.0114 0.5257 0.9120
3.250 0.5147 0.01005 0.00440 0.0109 0.5242 0.9136
3.500 0.5426 0.01007 0.00442 0.0106 0.5224 0.9141
3.750 0.5698 0.01005 0.00437 0.0105 0.5190 0.9144
4.000 0.5968 0.01006 0.00435 0.0103 0.5154 0.9147
4.250 0.6238 0.01008 0.00441 0.0101 0.5125 0.9151
4.500 0.6508 0.01010 0.00447 0.0099 0.5097 0.9154
4.750 0.6777 0.01012 0.00450 0.0097 0.5063 0.9158
5.000 0.7044 0.01015 0.00451 0.0095 0.5028 0.9162
5.250 0.7308 0.01018 0.00457 0.0094 0.4980 0.9167
5.500 0.7571 0.01022 0.00465 0.0093 0.4927 0.9172
5.750 0.7829 0.01027 0.00470 0.0093 0.4876 0.9177
6.000 0.8088 0.01034 0.00481 0.0092 0.4827 0.9183
6.250 0.8342 0.01041 0.00492 0.0092 0.4762 0.9189
6.500 0.8588 0.01050 0.00503 0.0093 0.4685 0.9195
6.750 0.8819 0.01063 0.00515 0.0097 0.4568 0.9203
7.000 0.9009 0.01088 0.00536 0.0107 0.4310 0.9214
7.250 0.8927 0.01195 0.00613 0.0158 0.3675 0.9246
7.500 0.8750 0.01297 0.00706 0.0224 0.3446 0.9284
7.750 0.8621 0.01464 0.00870 0.0267 0.3263 0.9323
8.000 0.8596 0.01617 0.01021 0.0293 0.3113 0.9358
8.250 0.8551 0.01788 0.01189 0.0319 0.2923 0.9397
8.750 0.8243 0.02372 0.01738 0.0364 0.1994 0.9501
9.000 0.8257 0.02613 0.01969 0.0363 0.1702 0.9540
9.250 0.8239 0.02890 0.02226 0.0361 0.1239 0.9582
9.500 0.8244 0.03184 0.02497 0.0352 0.0809 0.9614
9.750 0.8424 0.03333 0.02647 0.0338 0.0743 0.9632
10.000 0.8610 0.03476 0.02791 0.0324 0.0701 0.9651
10.250 0.8800 0.03612 0.02931 0.0310 0.0672 0.9671
10.500 0.8997 0.03744 0.03068 0.0296 0.0657 0.9689
10.750 0.9187 0.03876 0.03206 0.0284 0.0644 0.9710
11.250 0.9538 0.04169 0.03508 0.0260 0.0616 0.9754
11.500 0.9704 0.04320 0.03664 0.0248 0.0605 0.9781
11.750 0.9856 0.04478 0.03825 0.0239 0.0589 0.9814
12.000 0.9983 0.04659 0.04009 0.0230 0.0567 0.9854
12.250 1.0120 0.04831 0.04186 0.0222 0.0548 0.9896
12.500 1.0293 0.04962 0.04324 0.0213 0.0539 0.9936
12.750 1.0461 0.05113 0.04478 0.0207 0.0524 1.0000
13.000 1.0533 0.05251 0.04621 0.0215 0.0517 1.0000
13.250 1.0619 0.05385 0.04760 0.0222 0.0507 1.0000
13.500 1.0705 0.05525 0.04902 0.0228 0.0492 1.0000
13.750 1.0790 0.05672 0.05051 0.0233 0.0480 1.0000
14.000 1.0862 0.05834 0.05216 0.0238 0.0463 1.0000
14.250 1.0922 0.06011 0.05395 0.0242 0.0446 1.0000
14.500 1.1041 0.06133 0.05523 0.0245 0.0434 1.0000
14.750 1.1148 0.06268 0.05664 0.0247 0.0417 1.0000
15.000 1.1241 0.06422 0.05822 0.0249 0.0394 1.0000
15.250 1.1325 0.06587 0.05986 0.0250 0.0368 1.0000
15.500 1.1425 0.06735 0.06138 0.0251 0.0326 1.0000
15.750 1.1493 0.06916 0.06315 0.0253 0.0248 1.0000
16.000 1.1519 0.07144 0.06535 0.0254 0.0189 1.0000
16.250 1.1542 0.07378 0.06769 0.0256 0.0158 1.0000
16.500 1.1569 0.07612 0.07006 0.0257 0.0140 1.0000
16.750 1.1604 0.07842 0.07241 0.0257 0.0130 1.0000
17.000 1.1656 0.08052 0.07458 0.0257 0.0123 1.0000
17.250 1.1695 0.08283 0.07697 0.0256 0.0114 1.0000
17.500 1.1736 0.08516 0.07936 0.0255 0.0109 1.0000
17.750 1.1755 0.08771 0.08196 0.0253 0.0101 1.0000
18.000 1.1769 0.09044 0.08476 0.0250 0.0098 1.0000
18.250 1.1821 0.09271 0.08711 0.0247 0.0093 1.0000
18.500 1.1847 0.09529 0.08977 0.0243 0.0091 1.0000
18.750 1.1865 0.09803 0.09259 0.0238 0.0088 1.0000
19.000 1.1878 0.10085 0.09549 0.0233 0.0083 1.0000
19.250 1.1878 0.10390 0.09862 0.0227 0.0082 1.0000
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